info.aiaa.org · MESSENGER Propulsion System Cruise and MOI ... Michael Trela Johns Hopkins...
Transcript of info.aiaa.org · MESSENGER Propulsion System Cruise and MOI ... Michael Trela Johns Hopkins...
InteractiveEducationalToolforSim
ulation
and
Visualization
ofFluid
Flows
Sow
mitra
Singh
Dyn
aflow,Inc.
An
impro
ved
understa
nding
ofth
efu
ndamenta
lco
nce
pts
inFluid
Mech
anicslaysth
efoundation
forpursuingeithercu
ttingedgeaca
demic
rese
arch
orta
cklingindustry
relate
dpro
blems.
ThebasicprinciplesofFluid
Mech
anics,
dueto
their
math
ematica
lco
mplexities,
are
often
tough
togra
spforbeginners.Thepre
sentwork
introduce
san
innovativeeduca
-tionalso
ftware
thathelpsalearn
erbypro
vidinginte
ractively
aphysica
lpictu
re(v
isualiza
-tion,anim
ation,andillustra
tion)ofanunderlyingflow
phenomenonandth
eco
rresp
onding
math
ematica
lform
ulation
itse
rvesasalink
betw
een
themath
ematics
and
thephysics
of
Fluid
Mech
anics.
The
software
toolhas
an
inte
ractive
GUI(G
raphicalUse
rIn
terface
)th
atfacilita
tesstudents
examination
ofth
ee!ectsofch
anging
variousflow
para
mete
rsin
agiven
flow
set-up.TheGUIalsoallowsth
elearn
erto
saveth
ere
sultsand
anim
ationsin
filesth
atca
nbeexaminedlate
r.This
inte
ractiveto
olis
expectedto
serv
easavirtu
alfluids
labora
tory
formillionsofengineeringstudents
acr
oss
variousdisciplinesand
isexpected
totremendously
pro
mote
activese
lf-learn
ing.
Inth
epre
sentwork
theto
olis
applied
tostudyafew
case
ssu
chasth
eflow
aro
und
sin-
gle/multiple
cylinders,hydro
foils,
Rankinebodies,..
etc.Theto
ol’sca
pabilitiesin
captu
r-inginviscid
flow
aro
und
hydro
foilsand
inca
ptu
ringflow
pattern
sgenera
ted
byinte
racting
singularitiesis
alsosh
owca
sed.
1of1
AmericanInstituteofAeronauticsandAstronautics
Resp
onse
ofabubble
cloud
toacoustic
pressure
variations
Ti!anyFourm
eau,Sow
mitra
Singh
Dyn
aflow,Inc
Itis
well
known
thatca
vitation
occ
urring
on
apro
pellerca
nca
use
significa
ntero
sion
damage
toth
epro
pellerovertime.T
he
high
pre
ssure
socc
urring
ina
cavitation
field
are
dueto
theco
llapse
ofindividualbubblesand
bubble
clouds.
There
fore
,understa
ndingth
ebehaviorofbubble
cloudsand
the
pre
ssure
sth
ey
create
iscr
ucialto
understa
nding
and
controlling
thephenomenon
ofca
vitation
ero
sion.Furtherm
ore
,labora
tory
investigations
ofca
vitation
ero
sion
are
usu
ally
perform
ed
atsm
allerscalesin
length
and
timeand
itis
notalw
aysclearasto
how
thecloud
resp
onse
and
theco
rresp
onding
cavitating
pre
ssure
field
scale
with
length
and
time.
Inth
epre
sentstudy,
there
sponse
ofa
bubble
cloud
toan
impose
daco
ustic
field
isstudied
inord
erto
understa
nd
the
scaling
laws.
The
study
wasco
nducted
atDYNAFLOW
using
theco
dePHANTOM
CLOUD,which
solvesforth
edynamicsandmotionofallth
ebubblesbyacc
ountingforth
epre
sence
ofth
eoth
erbubbles.
This
reveals
both
individualbubble
dynamicsand
overa
llbubble
cloud
dynamics.
The
firstpart
ofth
estudy
focu
sed
on
bubble
cloud
resp
onse
toasinuso
idalaco
ustic
pre
ssure
variation.
Forsm
all
magnitudesofth
eapplied
pre
ssure
oscillations,
the
highest
bubble
cloud
amplitu
de
oscillationswere
ach
ieved
when
the
frequency
ofth
eim
pose
daco
ustic
field
wasclose
toth
ebubble
cloudfrequency
.There
sultsobta
inedsh
owedgoodagre
ement
with
analytic
resu
ltsavailable
inth
elite
ratu
re,which
are
usu
ally
linearize
d.
For
larg
emagnitudesofth
eapplied
aco
ustic
pre
ssure
oscillations,
however,
itwasobse
rved
thatth
eamplitu
de
ofth
ecloud
oscillationsincr
ease
dwith
decr
easing
frequenciesofth
eim
pose
daco
ustic
field.In
these
cond
part
ofth
estudy,
there
sponse
ofbubble
cloudsofdi!
ere
nt
initialvoid
fractions
near
arigid
wall,to
astro
ng
step
pre
ssure
was
investigate
d.
Itwasfound
thata
decr
ease
inth
eso
und
speed
ofth
emedium
(with
incr
easing
cloud
void
fraction)decr
ease
sth
epeak
and
incr
ease
sth
eperiod
ofth
epre
ssure
wave
reach
ing
the
wall.
Itwasalso
found
thatincr
easing
the
numberofbubblesin
the
cloud,orre
ducing
the
size
ofth
ebubblesin
the
cloud
resu
lted
inhigherpeaksand
smallerperiodsofth
epre
ssure
waveappearing
on
thebottom
plate
.Someofth
ere
sultsobta
ined
were
verified
against
numerica
lre
sultsavailable
inth
elite
ratu
re.
1of1
AmericanInstituteofAeronauticsandAstronautics
MESSENGER
Pro
pulsion
System
Cru
iseand
MOI
Perform
ance
Marc
Wilson,CarlEngelbrecht,Michael
Trela
JohnsHopkinsUniversity
Applied
PhysicsLaboratory
The
MErc
ury
Surface
,Space
ENvironment,
GEoch
emistry,
and
Ranging
(MESSEN-
GER)mission
wasdesigned
tounlock
the
secr
ets
ofourso
larsy
stemsinnerm
ost
planet,
revealing
clues
toth
eplanets
enigmatic
geologicalhisto
ry,unusu
ally
high
density,and
radar-re
flective
mate
rials
atth
epoles,
among
many
oth
erdeca
des-old
unansw
ere
dques-
tions.
MESSENGER
began
itsjourn
ey
on
3August
2004,when
itwaslaunch
ed
from
the
CapeCanavera
lAir
Forc
eSta
tion
inFlorida,and
thesp
ace
craft
wassu
ccessfu
lly
inse
rted
into
itsdestination
orb
itaboutM
erc
ury
on
18
March
2011.
On
itsway
toM
erc
ury
,th
eM
ESSENGER
space
craft
complete
d12
trajectory
-correction
maneuvers,five
deep-space
maneuvers,and
onecr
iticalM
erc
ury
orb
it-inse
rtion
maneuver.
This
paperdescribesth
eopera
tion
and
perform
ance
ofth
epro
pulsion
system
duringth
eM
ESSENGER
space
crafts
inte
rplaneta
rycr
uisephase
and
thro
ugh
itsinse
rtion
into
orb
itaboutM
erc
ury
.
1of1
AmericanInstituteofAeronauticsandAstronautics
Developmentofan
AdaptiveLeadingEdgeDro
op
Mech
anism
toReduceTake-O
!and
Landing
Casu
altieson
LightSport
Aircra
ft
MarioChris,JohnReidy,
Je!
Witz
Xavier
HighSchool
Sta
lling
isoneofth
elarg
est
dangers
whileflying
an
aircr
aft.Sta
lling
occ
urs
when
the
separa
tion
ofairflow
going
overand
underth
ewing
beco
mesto
osignifica
ntand
resu
lts
inth
eloss
oflift
and
controloverth
eaircr
aft.
Aircr
aft
Owners
and
Pilots
Association
reports
that
stalling
acc
ounts
for
13.7The
goalofth
ispro
ject
isto
design
an
adaptive
leadingedgecu
!forlightsp
ort
aircr
aft
whichwilldecr
ease
dra
gbyutilizingafu
ele"cient
wingcu
!angle
atallco
nditions,
whileincr
easingstallangle
byadaptingwingcu
!angle
for
this
purp
ose
when
high
anglesofattack
are
appro
ach
ed.Thedesign
willbecr
eate
dusing
compute
raided
design
(CAD)
software
and
willth
en
be
analyze
dusing
computa
tional
fluid
dynamics(C
FD)so
ftware
.Sta
tics
equationswillbe
use
dto
calculate
the
required
actuato
rforc
esforth
emech
anism
ofth
eadaptive
wing
cu!.
Ultim
ate
ly,th
epurp
ose
of
this
design
isto
notonly
incr
ease
fuele"ciency
butalso
incr
ease
safety
by
reducing
the
risk
ofstalling
inflight.
Analysisofdra
gre
sultsfrom
CFD
studiesofth
evariousleading
edge
dro
op
configura
tionsatth
edi!
ere
ntclim
b,cr
uise,and
descentco
nditionsofflight
indicate
sth
atinco
rpora
tion
ofth
edesigned
mech
anism
on
all
lightsp
ort
aircr
aft
willsa
ve
appro
xim
ate
ly170
thousa
nd
gallonsoffu
el,
corresp
onding
tosa
vingsofover1.04
million
dollars,peryear.
This
correlate
sto
reductionsin
over3million
poundsofCO2emissions,
which
isaboutth
eamountabso
rbed
by
64th
ousa
nd
trees,
peryear.
1of1
AmericanInstituteofAeronauticsandAstronautics
InterfaceRedesign
forGeoCam
Pro
ject
TyTrapps
CapitolCollege
TyTrapps,
CapitolCollegeNASA
AmesAcademyRese
arch
Associate
-Undergraduate
Inte
rn
Mento
r:
Dr.
Terry
Fong
Code:
TIBranch:
Inte
lligent
Robotics
Group,In
telligent
SystemsDivision
Clean,consistentdesign
isone
ofth
ekey
attribute
sofany
well
thoughtoutso
ftware
inte
rface.Even
moreso
forapplicationsuse
dby
rescueworkers,
theuse
rmust
beable
to
quickly
navigate
thesite
.TheGeoCam
Project,
which
isaweb-b
ase
dmappinglocato
rfor
rescuecrews,
hasasimple
enoughte
mplate
,yetth
edesignis
somewhatoutofdate
andnot
asintu
itiveasit
could
beforbasiccompute
ruse
rs.
Theta
skwassimple:M
akeit
easierfor
resp
ondersto
collaborate
during
acrisis
by
sharing
geosp
atialdata
.In
addition,anoth
er
goalwasto
utilizeth
eAndroid
DevelopmentEnvironmentto
create
mobileapplicationsfor
thedisasterreliefcommunity.
Rese
arch
wasconducte
dasto
how
tointe
grate
EmberJS
into
thecurrentJQueryframework.Onceproto
typesweredrawn
out,
developmentbegan
on
changing
the
currentinte
rface,using
MapsAPI,
KM
LM
ap
Layers,
JQuery
and
Ember.Thenew
design
willbetteraid
NASA
emergency
perso
nneland
state
orcity
rescueunitsin
quickly
accessingmap
locationsin
theeventofan
emergencyand
empower
citizensto
actively
participate
inrescuee!orts
on
their
mobiledevices.
1of1
AmericanInstituteofAeronauticsandAstronautics
NumericalSim
ulation
ofBubble
Flow
Interactions
ArvindJayap
rakash
Dyn
aflow
Inc.
Stu
dyofca
vitationince
ptionte
ach
esusth
atliquidsra
rely
existunderapure
monopha-
sicform
andth
atbubble
nucleiare
omnipre
sent.
Whileformanyapplica
tionsth
ese
bubble
nucleihavenoim
pact
and
can
beignore
din
CFD
simulations,
there
are
flow
fieldswhere
thepre
sence
anddynamicsofth
ese
bubblespro
foundly
a!ect
thephysics
athand.W
hena
micro
scopic
bubble
nucleusenco
unte
rsalarg
enegativepre
ssure
gra
dientin
theliquid
flow,
itexpands.
Depending
on
the
dynamic
balance
betw
een
the
pre
ssure
sgenera
ted
by
the
inertia
ofth
eliquid,th
ebubble
gasco
nte
nt,
andth
esu
rface
tension,th
ebubble
maygro
wexplosively,exce
edingitsequilibrium
volume,and
then
collapse
violently,
genera
tinghigh
aco
ustic
and
dynamic
pre
ssure
s.These
could
resu
ltin
hydro
dynamic
noise,mate
rials
ero
-sion,anddegra
dationofperform
ance
.W
henco
ntrolled,th
eyca
nalsobeexploitedfordra
gre
duction,ch
emicalre
action
enhance
ments,disinfection,pro
pulsion
impro
vements,mate
-rials
cleaning,cu
tting,and
noise
reduction.
Where
bubblesa!ect
the
flow
significa
ntly,
treatingth
em
asdiscr
ete
entitiesand
track
ingth
eir
motion
and
deform
ation
may
pro
vide
importantinsightto
the
design
engineer.
One
example
where
adiscr
ete
bubble
model
isvery
use
fulis
thedete
rmination
ofca
vitation
ince
ption
on
advance
dequipmentdesign,
such
astu
rbomach
inery
.In
aCFD
flow
field,aco
mmonly
use
dcr
iterion
isth
atca
vitation
occ
urs
where
verth
eliquid
pre
ssure
dro
psbelow
the
vapourpre
ssure
.This
assumption
failsif
the
liquid
isnotsu
persatu
rate
dwith
nucleiand
isparticularly
pro
blematic
fora
designth
ataim
sto
avoid
cavitationco
mplete
ly.Usingre
sultsofpre
viousexte
nsivestudies
on
non-spherica
lbubble
dynamicsand
their
inte
ractionswith
vorticalflow
stru
cture
sand
oth
erbubbles,
asimplified
Surface
Avera
ged
Pre
ssure
(SAP)sp
herica
lbubble
dynamics
modeland
aLagra
ngian
bubble
track
ing
scheme
hasemerg
ed.
Inth
eSAP
scheme,th
epre
ssure
and
velocity
ofth
esu
rrounding
flow
field
are
avera
ged
on
the
bubble
surface
,and
then
use
dforca
lculationsofth
ebubble
motion
and
volumedynamics.
This
pro
duce
sa
remark
ably
acc
ura
tesimulation
ofth
ebubble
dynamics,
which
acc
ounts
for
the
non-
uniform
ityofth
eliquid
flow
filed
inwhich
thebubble
isevolving.This
wasdeveloped
and
implemente
dasa
Use
rDefined
Function
(UDF)in
Fluentand
enablesco
mputa
tionsin
reaso
nable
CPU
timesofa
realnucleifield
distribution.Pre
sente
dhere
isth
edeveloped
appro
ach
and
someexamplesofapplica
tionsto
engineeringapplica
tions.
1of1
AmericanInstituteofAeronauticsandAstronautics
Optimizingth
eDesign
ofan
InertialElectrostatic
ConfinementSystem
JoshuaSloane
University
ofMarylandCollegePark
An
inertialelectrostaticconfinementsy
stem
compose
dofmultiple
dodecahedralgrids,
aswell
aselectron
core
neutralization,is
considered
asa
meansofim
proving
e!ciency.
The
first
step
ofth
erese
arch
was
todete
rmine
the
electrostatic
properties
ofa
single
dodecahedralgrid
withuniform
pote
ntial.
This
includedcalculatingth
echargedistribution
on
thegrid,and
thepote
ntialdueto
thecharged
grid.
Using
theparaxialray
equation,
themotionofbeamsofproto
nandboronionsdueto
amulti-grid
configurationis
modeled.
From
this,th
efu
sionpowergenerate
dbyaparticularconfigurationis
dete
rmined.Finally,a
gradientroutineandsimulate
dannealingroutineareuse
dto
findth
eoptimalconfiguration
thatmaxim
izesth
efu
sion
outp
utofth
esy
stem.
Thefu
sion
powergenerate
dfrom
theoptimized
configurationsis
unexpecte
dly
low,on
theorderof10-8
Watts.
This
ispossibly
dueto
amiscalculation
orbugin
thesimulation,
and
willbeconsidered
inmoredepth
asIcontinuemy
rese
arch.Futu
rerese
arch
willalso
includeusingth
eCOM
SOL
Multiphysicsso
ftwareto
analyzese
veralmechanismsbywhich
theelectronscan
beconfined,su
ch
aselectrostaticallyaswell
aswith
permanentmagnets.
1of1
AmericanInstituteofAeronauticsandAstronautics
Tra
jecto
ryCalculationsand
theJupiterSystem
MarioChris
Xavier
HighSchool
Essentialto
the
planning
ofany
space
mission
isth
eprocess
ofcalculating
required
velocitiesandtrip
times,
andresu
ltantmass
ratios,
ofth
edesiredtrajecto
rybetw
eenEarth
and
the
inte
nded
destination.
These
necessary
calculationswere
conducte
dto
design
a
frameworkforasp
acemission
toanyofth
ese
veralplanets
and
moonsin
theSolarSystem
thatmay
be
capable
ofsu
staining
life.
Jupiterand
itsmoons,
Europa,Ganymede,and
Callisto
,are
among
the
most
plausible
environments
for
life.
However,when
planning
apilote
dmission
toJupiter,th
eharmfu
lradiation
field
wasa
major
concern
thatwas
addressed,asit
isim
porta
ntto
take
note
ofany
risksto
the
crew’s
health.
Inaddition,
scenarioswereconsidered
such
thatoneofth
emoons,
preferably
safe
tohumans,
may
be
use
dasabase
tocontrolinvestigationofth
eoth
ertw
omoons.
TheenvironmentofJupiter
and
itsmoonswerealsostudied
foradiscussion
ofpossible
utilization
forlife
supportand
in-situ
propellant.
Taken
asa
whole,th
ese
examinationsofpossibilitiesoffu
turepilote
d
missionsto
Jupiterand
itsicymoons,
alongwith
calculationsforcorresp
ondingtrajecto
ry
requirements,may
provebeneficialin
these
arch
forextrate
rrestriallife.
1of1
AmericanInstituteofAeronauticsandAstronautics
STEM
Educa
tion
atth
eNationalAeroSpace
Tra
ining
And
Resea
rch
(NASTAR)Cen
ter,
AM
odel
for
Corp
ora
teSustainability
Gregory
Kennedy
NASTAR
Center
Loca
ted
inSouth
ampto
n,PA,th
eNationalAero
Space
Tra
ining
And
Rese
arch
(NAS-
TAR)Cente
ris
aco
mmerc
ialfacility
thatco
nductssp
ace
flighttraining,advance
dpilot
training,re
search,and
K-12
inform
aleduca
tionalpro
gra
ms.
The
NASTAR
Cente
ris
awholly
owned
subsidiary
ofETC,a
manufacture
rofaero
medicaltraining
and
rese
arch
equipment.
TheNASTAR
Cente
ris
anA!liate
Memberofth
eNASA
Pennsy
lvania
Space
Gra
ntConso
rtium
and
wasth
efirstfacility
tore
ceive
safety
appro
valfrom
the
FAA
for
commerc
ialsp
ace
flighttraining.
In2009,th
edecision
was
made
tota
ke
apro
active
position
on
STEM
educa
tion
toinsp
ire
students
topursue
care
ers
inscience
and
engineering.
Components
ofth
isef-
fort
includeschoolfield
trips,
asu
mmerday
camp
and
teach
erpro
fessionaldevelopment
pro
gra
msth
atta
keadvanta
geofNASTAR
equipmentand
curricula
topro
videhands-on
experience
sforstudents
and
teach
ers.Since
January
2010,more
than
1,100students
have
visited
NASTAR;274students
haveattended
NASTAR
Camp;and
150te
ach
ers
havepar-
ticipate
din
pro
fessionaldevelopmentpro
gra
ms.
In2012,th
eNASTAR
Cente
rpro
vided
STEM
conte
ntforanoth
er100
students
thro
ugh
NASTAR
Camp
EX
o"-site
pro
gra
ms.
Teach
erpro
gra
msinclude
opportunitiesto
fly
a3-G
suborb
italsp
ace
flightsimulation
inth
eNASTAR
Cente
rce
ntrifuge
and
experience
the
GasLawsin
the
NASTAR
altitude
chamber.
NASTAR
Camp
participants
flyNASTAR
aircr
aft
simulato
rsand
participate
innon-m
otion
suborb
italsp
ace
flightsimulationsin
thece
ntrifugesp
ace
trainingco
ckpit.
In2012,NASTAR
CampEX,asu
mmerca
mpin
aboxpro
duct
debute
d.TheNASTAR
CampEX
kit
includesallsu
pplies,
classro
om
mate
rials,lessonplans,
powerpointslides,
and
videonece
ssary
foraweek-longpro
gra
m.In
itspilotyear,
4NASTAR
CampEX
pro
gra
ms
were
pre
sente
d,which
serv
ed
113
students
inand
aro
und
Philadelphia.Forte
ach
ers,tw
onew
pro
gra
ms,
500
Years
ofFlight,
and
Rock
et
Science
,were
introduce
d.
The
Flight
Physiology
pro
gra
mforte
ach
ers
wasre
vised
using
NASA
SummerofIn
novation
conte
nt,
which
gaveit
more
ofasp
ace
medicineflavor.
NASTAR
STEM
pro
gra
mmingis
pre
sente
dasan
example
ofaprivate
-sectorinitiative
tocr
eate
asu
stainable
educa
tion
initiativeth
atre
inforc
esclassro
om
instru
ction.
1of1
AmericanInstituteofAeronauticsandAstronautics
Geometry-b
ased
ObservabilityM
etric
forAuto
nomous
Navigation
ColinEaton,BoNaasz
NASA
-Goddard
Space
FlightCen
ter
Goddard
sNatu
ralFeatu
reIm
ageReco
gnition
(GNFIR
)so
ftware
supportsauto
nomous
navigationin
pro
xim
ityopera
tionsbyutilizinganedge-b
ase
dmodelofata
rgetvehicle
and
fitting
this
modelto
camera
imagery
togenera
tea
relativepose
estim
ate
.Theacc
ura
cyand
reliability
ofth
epose
estim
ate
sare
highly
dependenton
the
chose
nmodelfeatu
res,
which
histo
rica
llyhavebeen
chose
nmanuallyand
refined
usingtrial-and-error.
Acc
ord
ing
tolinearestim
ation
theory
,th
einverseofth
epro
jection
matrix
(use
din
theleast-square
soptimization)
and
the
standard
deviation
ofth
eestim
ation
error
are
correlate
d.
This
relationsh
ipca
nbeexploited
toobta
inametric
ofth
estate
obse
rvability
simply
from
the
modelgeometry
and
targ
ettrajectory
,withoutre
quiring
imagery
tobe
pro
cessed.
The
new
metric
facilita
tesra
pid
modeland
trajectory
design,and
pro
videsan
impro
ved
real-
timepose
quality
metric.
Asimplified
3-d
egre
e-of-freedom
(3DOF)study
demonstra
ting
thebasicobse
rvability
principlesis
explore
din
deta
il.In
itialre
sultsfrom
applying
these
principlesto
full
6DOF
hard
ware
-in-the-loop
test
data
are
pre
sente
d.
1of1
AmericanInstituteofAeronauticsandAstronautics
Perceived
Realism
AssessmentofSynth
esized
Aircra
ft
EngineFan
Noise
SelenOkcu
NationalInstitute
ofAerospace
Sim
ulation
ofaircr
aft
flyoverevents
can
facilita
tepsy
choaco
ustic
studiesexploring
the
e!ectsofnoisegenera
ted
by
futu
reaircr
aft
designs.
Theperc
eived
realism
ofasimulate
dflyovereventmaybeim
pacted
byth
eperc
eived
realism
ofth
esy
nth
esize
dfan
noiseofth
eaircr
aft
engine.
Short-term
fluctuationsin
tonalamplitu
de
and
frequency
are
important
cuesco
ntributing
toth
atperc
eption
ofre
alism
,butare
notacc
ounte
dforby
pre
dictions
base
don
long-term
avera
ges.
Anew
synth
esis
meth
od
has
been
developed
at
NASA
Langley
Rese
arch
Cente
rto
genera
tere
alistic
aircr
aft
engine
fan
noise
using
pre
dicte
dso
urc
enoisedirectivitiesin
combination
with
short-term
fluctuations.
Inth
enew
meth
od,
fluctuationsin
amplitu
deand
frequency
are
included
base
dupon
analysisofstaticengine
test
data
.Thro
ugh
psy
choaco
ustic
testing,th
isstudy
assessed
perc
eived
e!ectiveness
of
thenew
synth
esismeth
od
ingenera
ting
realistic
fan
noiseso
urc
e.Realism
wasindirectly
assessed
by
judging
the
similarity
ofsy
nth
esize
dso
unds(w
ith
and
withoutfluctuations)
with
reco
rdingsoffan
noise.
Resu
ltsofANOVA
analyse
sindicate
dth
atsu
bjectsju
dged
synth
esize
dfannoisewithfluctuationsasbeingmore
similarto
reco
rdingsth
ansy
nth
esize
dfan
noisewithoutfluctuations.
1of1
AmericanInstituteofAeronauticsandAstronautics
UsingSolarCellsand
SolarTherm
alCollection
to
Captu
reSolarEnerg
y
LaurenWagner
MarriottsRidge
HighSchool
The
purpose
ofth
isexperim
entwasto
dete
rmine
ifa
solarelectric
orso
larth
ermal
panelwould
collectth
emost
solarenergy.
Itwashypoth
esized
thatif
solarenergy
was
collecte
dby
aso
larth
ermaland
aso
larelectric
panelwith
equalsu
rfaceareas,
then
the
solarelectric
panelwould
collectth
emost
energy
because
itwasprofessionally
made
to
collectso
larenergy.In
this
experim
ent,
oneso
larelectric
andoneso
larth
ermalpanelwere
filled
with
equalamounts
ofwate
rand
placed
nextto
each
oth
eroutside.They
werese
t
toth
esa
meangle
which
would
allow
them
tocollectth
eoptimum
amountofso
larenergy.
Throughoutth
eday,th
ete
mperatu
reofth
ewate
rin
both
deviceswasrecorded.From
this
information
itwascalculate
dwhich
devicecollecte
dth
emost
energy.
Theso
larth
ermal
panelconsistentlycollecte
dmoreenergyth
anth
eso
larelectric
panel.
Theaverageamount
ofenergy
gained
from
the
solar
thermalpanelafter
five
trials
was
1,168,032.2
Joules.
Theaverageamountofenergy
gained
from
theso
larelectric
panelwas477,736.4
Joules.
Asy
stematic
errorth
atpossibly
a!ecte
dth
edata
wasth
atboth
panels
were
setto
the
optimum
angle
forenergy
collection
during
summer,and
this
wasmainta
ined
even
into
thefall
soasnotto
introduceanew
variable.Thedata
refu
ted
thehypoth
esis.
Theso
lar
thermalpanelcollecte
dmoreenergyth
anth
eso
larelectric
panel.
Thedata
suggestedth
at
solarth
ermalpanels
would
bemoree!ectiveth
an
solarelectric
panels
tosu
pply
powerto
homes.
1of1
AmericanInstituteofAeronauticsandAstronautics
An
Experimentto
Assess
theM
icro
meteoro
idand
Orb
italDebrisEnvironment
JosephHussey,AlbertSad
ilek
United
StatesNavalAcadem
y
An
Experimentto
Assess
theM
icro
mete
oro
idand
Orb
italDebrisEnvironment
Jose
ph
Hussey(1
),Alb
ert
Sadilek(1
),Robert
Bru
ninga(1
),Chris
Anderson(1
),Hau
Ngo(1
),Fra
nk
Giovane(2
),Robert
Corsaro
(2),
J.C.Liou(3
),Gene
Sta
nsb
ery
(3),
Mark
Burchell(4
),(1
)United
Sta
tesNavalAca
demy,
AnnapolisM
D,21412,USA
(2)NavalRe-
search
Labora
tory
Aco
usticsDivision
(3)NASA
Johnso
nSpace
Cente
rOrb
italDebris
O!ce
(4)University
ofKent
Cente
rofAstro
physics
&Planeta
ryScience
Orb
italdebrisis
an
issu
eofgre
atco
nce
rnforcu
rrentsp
ace
opera
tions.
Space
debris
can
collideand
ruin
space
craft
and
isasa
fety
conce
rnforhuman
space
flight.
Whiledebris
gre
ate
rth
an
ten
centimete
rsis
track
ed
by
the
Department
ofDefense
(DoD),
smaller
micro
-debrisis
notcu
rrently
being
track
ed.Desp
iteitssm
all
size
,micro
-debristraveling
atupward
sofse
ven
kilomete
rsperhourca
nstilldamagesp
ace
craft.
TheDebrisResistive/Aco
ustic
Grid
Orb
italNavy
Senso
r(D
RAGONS)willpro
videa
capability
tomonitororb
italdebrisassm
all
as50
m.
Itwillmeasu
reth
evelocity,mass,
size
,position
inorb
it,im
pact
loca
tion,and
impact
angle
with
thepurp
ose
ofupdatingth
ecu
rrentorb
italdebrismodel(O
RDEM
).Pro
vidingsu
chdata
isth
efirststep
toward
shelp-
ingth
esp
ace
community
betterdefineitsobjectivesformeth
odsto
mitigate
oreliminate
risk
from
micro
-debrisin
orb
it.
DRAGONSis
essentiallyaninstru
mentco
mpose
dofth
reesu
bsy
stems:
anaco
ustic
grid
subsy
stem
(ACS),
resistivegridsu
bsy
stem
(RGS),
andco
mmandanddata
stora
ge(C
DSS).
TheACS
willdete
ctdebrisbyca
ptu
ringth
eaco
ustic
wavesth
atth
eparticle
create
supon
impact
withth
einstru
ment.
TheRGSwillhelp
validate
these
impactsbyta
kingadvanta
ge
ofOhm’s
Law.Using
aco
nstantcu
rrentand
stringsofpara
llelre
sistors
only
75
mwide,
DRAGONS
willmeasu
reth
evoltagevariation
cause
dby
aparticle
impactsbre
aking
one
ormultiple
resistors.Thedata
from
theACS
and
RGS
willbestore
din
theCDSS
until
late
rtransferto
thehost
space
craft
and
downlink
toan
Earth
gro
und
station.
Thedesign
forth
eDRAGONS
flightpro
toty
pehasbeen
complete
d,and
itis
currently
beingbuiltatth
eUnited
Sta
tesNavalAca
demy(U
SNA)mach
inesh
op.Upon
completion
offabrica
tion,it
willbeputth
rough
vibra
tion,aco
ustic,and
therm
alte
ststo
ensu
reth
at
itis
pre
pare
dfor
the
launch
and
space
environments.
Hyperv
elocity
particleswillalso
be
fire
datth
einstru
mentatUSNA
and
atth
eUniversity
ofKentin
ord
erto
calibra
teit
toco
llect
impact
data
from
orb
italdebris.
Afterte
sting,any
changeswillbemadeto
theinitialmodel.
DRAGONS
iscu
rrently
scheduled
tolaunch
toth
eIn
tern
ationalSpace
Sta
tion
(ISS)in
March
of2014.
1of1
AmericanInstituteofAeronauticsandAstronautics
Aero
dynamicsAirfoil
Configura
tion
MannySantana,Jennifer
Vasquez
VaughnCollegeofAeronautics
&Technology
Thesu
rfaceconfiguration
on
agolf
ball
isuniquein
itsdrag
reduction.In
theprese
nt
work,th
eapplication
ofth
isconfiguration
willbeincorporate
dto
apropose
daerodynamic
wingto
investigate
theabilityto
promote
lift
and
reducedrag;investigatingif
therecould
possibly
beadelayin
stallangle
ofanaircraft
wing.This
workwillreconfigureth
einitially
smooth
surfaceatth
eairplanewing
and
apply
adim
pled
surfaceasth
atofth
egolf
ball
while
rese
arching
the
e!ect
on
the
propose
dairfoils
flight
characte
ristics.
An
aircrafts
wingis
considered
tobeth
eheartofan
aircraft;a!ectingcruisesp
eed,ta
keo!
and
landing
dista
nces,
handling
qualitiessu
ch
asstall
speed
and
overall
aerodynamicsofth
eaircraft
duringflight;
this
wingconsistingofan
airfoil
shapeasse
en
initscross-section,producing
aerodynamic
forcesoflift,drag
and
moment.
Asth
eleading
edgeis
rounded
o!
and
the
trailingedgeis
sharp,th
esu
rfaceis
alw
ayssm
ooth
.On
theoth
erhand,th
esciencebehind
itsreduction
indrag
ingolf
ball
comesfrom
thedelay
inse
paration
ofitsboundary
layer
ofair
overitssu
rface;creating
alow
narrowerwaketh
an
thatofa
smooth
surfaced
ball.
Importa
ntasp
ects
ofan
airfoil
design
consist
ofairfoil
geometry,airfoil
selection,sp
eed
range,winggeometry,asp
ectratio,wingsw
eep,ta
perratio,tw
ist,
wingincidence,dihedral,
wingtips,
and
numberofwings.
With
an
exte
nsivenumberofvariablesto
consider,it
has
been
decided
toconcentrate
this
propose
ddesign
and
rese
arch,on
only
theaerodynamic
forcesassociate
dwithflight.
Whilefocusingth
eobjectiveofth
eoutcomeonth
eresu
rfaced
structu
re,an
actu
alaircraft
NACA
airfoil
willbe
use
d.
As
AeronauticalEngineering
students,a
good
aerodynamic
airfoil
willbe
carefu
lly
selecte
dand
incorporate
din
the
design
by
creating
a3-D
modelusing
SolidW
orks.
ItsCFD
Solidworksflow
simulation
packagewillbeutilizedto
gath
errealistic
flightdata
forourpropose
dconfigurationandan
AOA
willbeincorporate
dto
close
lyreflectrealistic
flight.
With
utilizingaCAD
program,
we
willbe
able
toreposition
and
resh
ape
ourpropose
ddesign
togetth
ebest
resu
ltsof
theincorporate
ddesign
on
thesu
rfaceatdi!
erentairsp
eeds,
asair
becomescompressible
and
incompressible
inrelation
toM
ach
number.This
intu
rn
willa!ectth
estall
angle
of
thewingin
conclusion
ofapositivemeansbya!ectingth
eair
within
itsboundarylayeras
thatofgolf
ball.
1of1
AmericanInstituteofAeronauticsandAstronautics
LiftForcePerform
anceofaCarSpoileratCurvatu
res
Dom
inic
Elrington
,Joh
nAndon
VaughnCollegeofAeronautics
andTechnology
Aero
dynamicsis
essentially
importantforan
aircr
aft
and
iscr
ucialforan
auto
mobile.
Aero
dynamic
stru
cture
use
din
the
auto
motive
industry
thatis
on
the
rearofan
auto
-mobileis
called
an
auto
motivewing
butis
popularly
known
asasp
oiler.
Theauto
motive
wingis
similar,
inte
rmsofstru
cture
,to
an
aircr
aft
wingasboth
pro
duce
lift
toitsstru
c-tu
re.
However
inauto
mobiles,
the
auto
motive
wing
pro
duce
snegative
lift
toact
as
adownforc
eto
help
keep
an
auto
mobilestability
when
opera
ting
athigh
speedsparticular
incu
rved
roadsand
turn
s.W
hen
auto
mobilesare
opera
ting
athigh
speedsand
go
into
sharp
turn
s,often
timesth
ey
enco
unte
rover-steering
and
may
lose
control.
With
thatin
mind
installing
the
wing
stru
cture
with
an
airfoil
thatpro
duce
sth
eneeded
negative
lift
and
also
doesn
tpro
duce
larg
edra
gis
crucialto
attain
high
aero
dynamic
chara
cteristics
forourapplica
tion.Thepre
sentwork
involvesru
nning
afluid
analysison
an
auto
motive
wingth
atwasdevelopedfrom
theNACA
63210airfoil.It
willbemounte
donth
eback
ofa
thre
edim
ensionalco
mpute
rsp
ortsca
rmodel.
This
modelwillbeuse
dto
pro
videre
alistic
airflow
chara
cteristicsto
thewingstru
cture
inth
eCFD
simulation.It
willalsoinvestigate
and
chara
cterize
showing
thee!ectsofth
edi!
ere
nttu
rnra
diusand
carsp
eed
on
thelift
genera
ted.Thro
ugh
this
analysisan
obse
rvation
willbemadeofth
eairflow
resp
onse
with
thesp
oilerand
solid
body
(car)
inte
rmsofperform
ance
chara
cteristicsdete
rmining
dif-
fere
ntangle
ofattack
with
di!
ere
nttu
rnsand
speed.Theobse
rved
willbemanipulate
dto
study
thee!ectsit
hason
aso
lid
body
(car).Thro
ugh
this
adevelopmentofasp
oilerca
nbemadeth
atwillpro
duce
thedesire
ddownforc
eto
pre
serv
eth
evehicle
stabilityin
turn
s.
1of1
AmericanInstituteofAeronauticsandAstronautics
Chara
cterization
ofEnerg
yDeposition
forDra
g
Reduction
MonaGolbabaeiAsl
Rutgers,
theState
University
ofNew
Jersey
Theobjectiveofth
ispre
senta
tionis
todescribedra
gmitigationin
supersonic
flightusing
energ
ydeposition
tech
nique.Overth
epast
severa
ldeca
des,
publicdemand
forsu
personic
transp
ortationhasre
ceivedsignifica
ntattention.There
searchin
this
are
ahasalw
aysbeen
challenged
by
e!ciency
,perform
ance
,and
environmenta
lissu
es.
High
dra
gis
oneofth
emajorpro
blemswhich
considera
bly
impact
the
e!ciency
insu
chflights.
Awave
dra
gis
genera
teddueto
existe
nce
ofsh
ock
wavesin
thesu
personic
flight.
Hence
,it
isvery
impor-
tantto
develop
an
e!cientmeth
od
tore
solveth
eadversee"ect
from
high
dra
g.
Energ
ydeposition
hasre
centlybeen
known
asaro
bust
meth
od
fordi"
ere
ntflow
controlpurp
ose
s.The
actuation
time
ofth
iste
chnique
isvirtu
ally
instanta
neousand
compara
ble
with
the
very
small
timescalesinvolved
inhigh
speed
flow.Energ
ydeposition
isach
ieved
thro
ugh
avariety
ofmeth
ods:
RF,electrica
l,micro
waveand/orlase
rdisch
arg
e.
Aplasm
are
gion
plasm
oid
isgenera
ted
upon
disch
arg
ein
the
flowfield
which
inte
racts
with
the
existing
shock
system
and
alters
flow
para
mete
rsre
sultingin
changesin
dra
gbehavior.
Depending
on
the
disch
arg
ety
pe
variousplasm
aco
nfigura
tionsca
nbe
create
d.
Experimenta
land
computa
tionalstudieshavebeen
perform
ed
toinvestigate
thee"ect
from
di"
ere
ntplasm
aco
nfigura
tions.
Saso
hetal.
perform
ed
experiments
tostudy
the
inte
raction
offocu
sed
lase
rpulsewith
shock
wave.Kandala
and
Candleruse
da
therm
o-chemicalmodelforair
tostudy
loca
llase
rdisch
arg
ein
supersonic
flow.
Sch
ulein
etal.
studied
the
e"ect
ofa
lase
rdisch
arg
ein
supersonic
flow
using
aperfect
gasmodel.
Lash
kov
etal.
perform
ed
experiments
toexamine
the
resu
ltofmicro
wave
disch
arg
eahead
ofsu
personic
AD
bod-
ies.
Knightetal.
haveperform
ed
computa
tionsfora
realgasmodelto
study
micro
wave
disch
arg
einte
raction
with
shock
wave.
Bro
vkin
etal.
(2006)im
plemente
dexperiments
tostudy
the
inte
raction
ofco
mbined
micro
wave
and
lase
rdisch
arg
ewith
flowfield.
This
rese
arch
focu
seson
computa
tionalch
ara
cteriza
tion
ofdra
gmodifica
tion
dueto
form
ation
ofan
instanta
neousplasm
asp
ike
genera
ted
by
combined
lase
rand
micro
wave
disch
arg
eahead
ofa
bluntcy
linderatM
ach
3.
Aperfect
gasmodeland
axisymmetric
flowfield
isassumed.Theperfect
gasassumption
helpssimulate
theplasm
asp
ikewith
ahigh
temper-
atu
refilament.
Ase
tofdim
ensionless
para
mete
rsis
defined
toinsp
ect
both
thefilament
length
and
tempera
ture
e"ect
on
dra
gcu
rve.Thehigh
tempera
ture
filamentis
introduce
dinstanta
neously
ahead
ofth
ecy
linder
inpre
sence
ofth
eexisting
bow
shock
.The
flow
conto
urs
pre
sentth
eform
ation
ofa
toro
idalvortex
behind
the
shock
upon
initiation
of
filamentinte
raction
with
the
bluntcy
linder.
The
circ
ulation
region
expandsasit
moves
o"
theaxis
and
reduce
sth
efronta
lpre
ssure
.There
sultsindicate
amaxim
um
momenta
rydra
gre
duction
of90
1of1
AmericanInstituteofAeronauticsandAstronautics
Reusable
ArchitectureforM
anned
MarsM
ission
RyanSchmidt,HongraeKim
,EricTran
United
StatesNavalAcadem
y
Eversince
theacc
omplish
mentofth
eApollo
lunarlandings,
thenextstep
forNASAs
mannedsp
ace
pro
gra
mhasbeenamissionto
Mars.Thoughth
eUnitedSta
tesgovern
ment
hasse
ta
goaldate
fora
manned
mission
launch
inth
e2030s,
eco
nomic
unce
rtainty
and
persiste
ntbudgetcu
tsmaketh
efinancialback
ingforsu
chamission
unce
rtain.There
fore
,co
ste!ectiveness,ormaxim
izingscientificre
turn
on
investment,
isofprimary
importance
inany
pote
ntialmission
design.
The
objective
ofth
isre
search
pro
ject
isto
investigate
the
benefits
ofa
multi-part
reusa
ble
mission
architecture
thatca
nsu
pport
multiple
manned
missionsto
Mars.
The
inte
ntbehind
this
e!ort
isto
ach
ieve
gre
ate
rscientific
retu
rnwith
many
missions,
each
individualonebeing
lowerin
cost
dueto
thelarg
erinitialinvestmenton
reusa
ble
infras-
tructure
.W
hile
the
tota
lco
stofth
ispro
gra
mmay
be
higher
than
one
base
daro
und
single-u
semission
architecture
,th
emuch
gre
ate
rre
turn
ofscientificknowledgewould
jus-
tify
thegre
ate
rexpense
.Thegro
undse
gmentwould
consist
ofEarthgro
undinfrastru
cture
and
C3infrastru
cture
.Thelaunch
segmentwould
beNASAsSpace
Launch
System
(SLS).
Thesp
ace
segmentwould
consist
offourre
usa
ble
parts:
apro
pulsion
module
fortransfer
tomars,aM
ars
landingmodule,aM
ars
surface
habitatmodule,andanEarth-M
ars
cycler
space
station.Each
part
would
beco
nstru
cted
and
stationed
initsappro
priate
place
prior
toth
efirstmanned
mission
launch
and
would
remain
there
afterth
ere
turn
ofth
efirst
crew
foruse
by
futu
remissions.
The
pre
senta
tion
willco
ver
the
conce
ptu
aldesign
ofth
eentire
mission
architecture
,from
thefirstlaunch
ofth
esu
pport
infrastru
cture
toth
ere
turn
ofth
efirstcr
ew
toEarth.
The
majority
ofre
search
tobe
done
willfocu
son
tech
nicalfeasibility
and
cost/benefit
analysis.
1of1
AmericanInstituteofAeronauticsandAstronautics
FlightTestingSenso
rsforRPAs
MarisaLockhart
JohnPaultheGreatCatholicHighSchool
Remote
lyPilote
dAircr
afts(R
PAs)
are
unmanned
airborn
emach
inesth
atare
use
dby
theUS
govern
mentand
military
tota
kepictu
res,
surv
ey
land,and
communicate
inform
a-
tion,re
cord
data
,and
oth
eruse
fulpurp
ose
s.Beca
use
ofth
eir
unique
abilities,
they
are
inhigh
demand
insu
rveillance
,co
mmunications,
and
weaponsdelivery
.However,
these
missionsca
nbeco
me
compro
mised
by
unexpected
weath
er.
With
every
mission
costing
millionsofdollars,every
lost
RPA
isvery
devastating
toth
epeople
who
opera
te,fly
and
invest
much
toth
eexpedition.Realtimeknowledgeofatm
osp
hericte
mpera
ture
and
rela-
tivehumidityca
nbeuse
dto
betterpre
pare
theco
ntrollerandpilots
ofth
eRPAsandenable
them
toavoid
dangero
usweath
erco
nditionssu
chasicing,tu
rbulence
,winds,
aco
usticsand
thundersto
rmactivity.
This
isbeca
use
knowing
thete
mpera
ture
and
relativehumidity
of
theatm
osp
here
can
pre
dictth
epre
sence
ofcloudsand
moistu
re.
Ase
nso
rwasdesigned
and
manufacture
dto
work
on
aRPA
and
measu
rete
mpera
ture
and
relative
humidity.
Ascientifica
lly
base
dflightte
stpro
gra
mhad
tobe
designed
toevaluate
these
nso
rforitsacc
ura
cyin
measu
ringre
lativehumidityandte
mpera
ture
.Since
no
RPA
wasavailable
forte
sting,a
suitable
altern
ativeaircr
aft
had
tobefound
toca
rry
outth
eairborn
ete
sts.
Asu
itable
civilian
lightairplane,Cessna340,wasmadeavailable
forth
ete
sting.This
airplanewasse
lected
base
don
itsnorm
alopera
tingweight,
speed,and
altitude,which
all
rese
mbledth
estandard
RPAs.
Themanufacture
dse
nso
rwasattach
edto
thefrontwindow
ofth
eaircr
aft
andflownin
ase
riesofflightmaneuvers
inHouston,Texasin
June2012.The
senso
rco
llected
there
adingsofte
mpera
ture
,re
lativehumidity,
and
GPS
and
transm
itte
dth
em
toan
on-b
oard
lapto
pco
mpute
r.Thedata
wasth
en
plotted
realtimeto
allow
the
test
crew
toevaluate
the
atm
osp
heric
conditionswhile
they
flew.
The
transm
itte
ddata
wasco
mpare
dto
NationalW
eath
erServ
iceweath
erballoon
data
from
thesa
meloca
tion
and
time.
These
nso
rwase!ectivein
readingte
mpera
ture
and
pre
ssure
on
thegro
und
and
inth
eair.
The
plotted
data
showed
thatth
ete
mpera
ture
sduring
flightch
anged
asexpected.
However,
thedata
acc
ura
cywassu
spicious.
There
adingsforte
mpera
ture
and
relativehu-
miditydid
notalw
aysmatchth
ere
adingsfrom
theNationalW
eath
erServ
iceoraircr
aft.It
isbelieved
thatth
emeta
lca
singofth
ese
nso
rco
llected
heatfrom
sunlightorinte
rnalelec-
tronicsand
sentco
nductiveheatth
rough
themeta
lsto
these
nso
rsslightly
compro
mising
these
nso
rse!ectiveness.
The
flightte
stssh
owed
thatth
ese
nso
rswere
overa
llsu
ccessfu
l,butre
quire
design
of
anew
and
di!
ere
ntca
sing
toeliminate
the
heatco
nta
mination
from
sunlightand
oth
er
sourc
es.
Furtherdesign
work
and
flightte
stswillth
en
benece
ssary
toach
ieveth
egoalof
usingase
nso
rto
measu
rete
mpera
ture
and
relativehumidity
from
aRPA.
Marisa
A.Lock
hart
Junior,
John
Paulth
eGre
atHigh
Sch
ool
1of1
AmericanInstituteofAeronauticsandAstronautics
Steady-S
tate
Compressible
Flow
ComputationalFluid
DynamicsAnalysisofTra
ilingEdgeHigh-L
iftDevices
Agastya
Parikh
Howard
HighSchool
The
purp
ose
ofth
isexperiment
was
toim
pro
ve
the
design
oftrailing-edge
high
lift
deviceson
theAirbusA330-300in
ord
erto
explore
feasible
waysto
impro
vefu
ele!ciency
on
midsize
aircr
aft.Experimenta
tion
wasco
nducted
thro
ugh
use
ofco
mputa
tionalsteady-
state
meth
odsin
ANSYSCFX,andpost-p
roce
ssinganalysiswasco
nductedin
AvizoW
ind.
Thedesignste
stedwere
thestandard
A330-300sy
stem,afu
ll-spansy
stem
derivedfrom
the
A330sy
stem,and
amodifica
tion
ofth
efu
ll-span
system.Themodels
create
dwere
tested
inta
keo"
and
landing
configura
tionsbase
don
Airbus-pro
vided
data
.The
data
obta
ined
wasanalyze
din
term
soflift,dra
g,and
L/D
ratio,and
wasth
en
post-p
roce
ssed
forvisual
analysis.
Thehypoth
esisstate
dth
atth
emodified
fullsp
an
system
would
perform
thebest
inboth
configura
tions.
Itwasnotsu
pportedbyth
edata
.Thestandard
wingperform
edth
ebest
inboth
takeo"
and
landingco
nditions,
pro
ducingL/D
ratiosof7.81998and
7.50963,
resp
ectively.
The
modified
fullsp
an
followed,genera
ting
7.23719
and
7.36081
asitsL/D
ratios.
The
fullsp
an
flap
perform
ed
worst,
with
L/D
ratiosof7.23627
and
7.31575.
The
standard
wingpro
duce
dth
ebest
perform
ance
byo"se
ttingitsdra
gpro
duction
su!ciently
with
lift
pro
duction.Themodified
fullsp
an
waslimited
severe
lyby
reduce
dwingare
a,as
itslack
oflift
pro
duction
wasth
eca
use
oflow
L/D
ratio.Thefu
llsp
an
flap
waslimited
by
dra
g,asitshigh
lift
pro
duction
led
tohigh
dra
gpro
duction.Theco
nclusion
thatca
nbe
dra
wnfrom
thedata
isth
atth
estandard
flapse
ctionre
pre
sents
thebest
designformidsize
aircr
aft.There
sultsofth
isexperimentwould
best
beapplied
inord
erto
impro
veth
efu
el
e!ciency
ofaircr
aft
duringta
keo"
and
landing.
1of1
AmericanInstituteofAeronauticsandAstronautics
Establish
ingCapabilitiesforParticle
Image
Velocim
etryofPlasm
aActu
ato
rFlow
Pattern
s
NicholasZarbo
University
ofMaryland
Plasm
aactuato
rsare
thin
sheets
ofwireth
an
can
induce
low
wind
speedsormainta
inattach
ed
flow
on
high
angle
ofattack
airfoils.
Plasm
asare
well
understo
od
on
amacr
o-
scopic
scale,butth
eflow
pro
pertiesinsideth
em
are
notwell
understo
od.Thegoalofth
ispro
ject
isto
establish
an
e!ective
Particle
Image
Velocimetry
(PIV
)se
tup
todete
rmine
velocity
vectors
thro
ughoutaplasm
aactuato
r.This
pre
senta
tion
deta
ilsth
einitialdesign
considera
tionsand
pre
liminary
stepsto
ward
scr
eatingate
stbed
forth
eexperiment.
Fur-
therdeta
ilis
pro
vided
on
the
challengesand
some
solutionsofth
edesign
pro
cess.
The
futu
restepsofth
epro
ject
are
described
and
pote
ntialexperiments
are
discu
ssed
aswell.
1of1
AmericanInstituteofAeronauticsandAstronautics
MLIE!ectiveness
Stu
dy
RegisVenti,JuanRodriguez
UMBC
Thee!ectiveemissivity
(*)ofmulti-layerinsu
lation
(MLI)
isdependenton
theoptica
l,th
erm
al,
and
physica
lpro
pertiesofth
eindividuallayers,which
comprise
MLI.
Therm
al
modeling
pra
ctice
ofsp
ace
born
eobjects
with
MLI
typically
use
sa
default
value
of*
base
don
pre
viousre
search,herita
ge,and
legacy
.A
math
solver
typically
constru
ctsa
radiation
coupling
using
this
*value
and
doesnotacc
ountforco
nductive
heattransfer.
This
pro
ject
focu
seson
thee!ect
of*
fordi!
ere
ntM
LIco
nfigura
tions.
Therm
alvacu
um
testing
ofa
therm
ally
isolate
dsh
eetmeta
lbox,re
pre
senta
tive
ofa
common
electro
nics
box
on
asp
ace
craft,wasco
mplete
dto
exemplify
the
a!ectsofM
LIco
nfigura
tion
on
its
e!ectiveness.TwoM
LIco
nfigura
tionswere
tested:1)form
fitted
and
2)te
nte
d.Thebox
utilize
dth
esa
meM
LIforeach
configura
tion
and
wasexpose
dto
thesa
meenvironmentof
-150C
(10C)and
5x
10-5
torr.Therm
alDesk
top
5.5
correlate
dte
stdata
toso
lveforth
e*.
Pro
viding
1W
ofpowerto
the
box,th
ere
sultsyield
an
*of0.036
forth
eform
fitted
case
and
an
*of0.021forth
ete
nte
dca
se.There
sultsindicate
thatate
nte
dco
nfigura
tion
ofM
LImay
pro
videbetterinsu
lation
than
form
fitting.Oth
erte
sted
powerse
ttingssh
ow
thatth
ere
isate
mpera
ture
dependence
of*,with
higherte
mpera
ture
syieldingalower*.
1of1
AmericanInstituteofAeronauticsandAstronautics
MM
SPro
pellantTankTherm
alCapacitanceM
odel
Stephen
McK
im,AmandaSteckel
NASA
TheM
agneto
sphericM
ultiSca
le(M
MS)M
ission
seeksto
understa
nd
how
theSunsand
Earthsmagneticfieldsinte
ract
thro
ugh
an
energ
eticphenomenon
called
magneticre
con-
nection.Tohelp
acc
omplish
this,aform
ation
of4sp
ace
craft,each
with
amonopro
pellant,
blow
down
pro
pulsion
system,willbeuse
dto
raiseth
eapogeeofeach
space
craft,enabling
scientiststo
study
magneticphenomena
atboth
thebow
shock
and
magneto
-tail
regions
aro
und
Earth.Acc
ura
teknowledgeofth
epro
pellantload
ineach
space
craft
iscr
iticalto
execu
teth
ismaneuver,
perform
station
keepingduringth
etw
o-yearmission,and
plan
for
end-of-life
disposa
l.This
pre
senta
tiondiscu
ssesath
erm
alca
pacita
nce
modelofth
eM
MSpro
pulsionsy
stem
pro
pellantta
nksth
atwascr
eate
dto
estim
ate
thepro
pellantload
on
thesp
ace
craft
near
end-of-life,a
phase
inth
emission
where
high-acc
ura
cyknowledge
ofth
ere
maining
pro
-pellantis
importantto
dete
rmineth
eend
ofscience
opera
tions.
Theth
erm
alca
pacita
nce
meth
od
isuniquein
thatth
eacc
ura
cyofth
epro
pellantestim
ate
incr
ease
sasth
eamount
ofpro
pellantin
theta
nk
decr
ease
s.This
contrastswith
thetraditionalpro
pellantgauging
meth
odsofbook
keeping
and
pre
ssure
-volume-tempera
ture
,which
are
more
acc
ura
teat
thebeginning-of-life
and
less
acc
ura
teatend-of-life.
The
therm
alca
pacita
nce
modelwascr
eate
dby
developing
adeta
iled,transientth
er-
malmodelofth
eM
MS
pro
pellantta
nk
using
the
ANSYS
finite
elementso
ftware
pack
-age.Boundary
conditionswere
obta
ined
from
theM
MS
therm
alte
amssp
ace
craft
therm
al
model.
Opera
tion
ofth
erm
ostatica
lly
controlled
heate
rs,th
eappro
xim
ate
shape
ofth
epro
pellantco
nta
ined
within
thediaphra
gm
tank,busvoltage,and
actualinte
gra
ted
heate
rre
sistance
swere
each
added
toth
eANSYS
model.
This
pro
pellant
gauging
tech
nique
was
initially
validate
dagainst
the
MM
Sth
erm
al
teamsindependentth
erm
alanalysisofth
eM
MS
pro
pulsion
system
and
tanks.
Pro
pellant
loadsof10,15,and
20
kilogra
mswere
simulate
din
the
modelto
pro
duce
tempera
ture
versustimecu
rvesbase
dupon
tempera
ture
data
.Thepre
senta
tion
willalsodiscu
ssfu
ture
work
tovalidate
themodelusingsp
ace
craft
therm
alvacu
um
test
data
,aswell
ase!ectsof
thesy
stemsinitialte
mpera
ture
and
time-vary
ingboundary
conditions.
1of1
AmericanInstituteofAeronauticsandAstronautics
Real-Tim
eEstim
ationofAircra
ftFrequencyResp
onses
JaredGrauer,EugeneMorelli
NASA
Langley
ResearchCen
ter
Frequency
resp
onse
sdescrib
eth
erelativemagnitudeand
phase
angle
steady-sta
tere-
sponse
ofadynamic
system
subjectto
harmonic
excitation.Frequencyresp
onse
sestim
ation
via
Welch’s
Meth
od
isoften
use
dforidentifying
aircraft
dynamic
models
from
measu
red
flight
data
for
severalreaso
ns.
For
instance,estim
ating
frequency
resp
onse
sis
anon-
parametric
technique
thatrequiresno
previousknowledge
ofth
efu
ndamenta
ldynamics,
e.g.from
aCFD
analysisorawind-tunnelte
st.Furth
ermore,linearmodels
resu
lt,which
facilitate
abroad
toolsetofstandard
stability
analysisand
controlsy
nth
esiste
chniques.
However,th
ere
are
severaldrawbacksto
this
approach.
Frequency
sweepsare
typically
use
dto
exciteth
eaircraft,andlongdata
recordsof90to
120se
condsperinputareneeded
forgoodresu
lts.
Thewindowingproceduresrequireth
eanalyst
tomakeengineeringju
dge-
ments
thatim
pactth
eresu
lts,
such
aswindow
length
,sh
ape,and
overlap.Finally,th
ere
isnodirectquantification
ofuncerta
inty
toqualify
theresu
lts.
This
work
prese
nts
anew
meth
od
forestim
ating
frequency
resp
onse
sand
their
uncer-
taintiesin
realtime.Previously
developed
orth
ogonalphase
-optimized
multi-sineexcita-
tionsareemployed
toexciteall
theaircraft
inputs
simultaneously,th
erebysh
orte
ningte
st
durations.
AFouriertransform
isuse
dto
thenconvertmeasu
rements
atth
eexcitationfre-
quenciesinto
thefrequencydomain,whereth
emagnitude,phase
angle,and
uncerta
inty
of
thefrequency
resp
onse
sareextracte
d.A
recursiveformulation
ofth
isprocess
and
adata
forgetting
algorithm
give
the
meth
od
areal-time
and
adaptive
capability.
This
meth
od
providesan
accurate
and
computa
tionally-e!cientmeth
od
ofestim
atingpote
ntially
time-
varyingfrequencyresp
onse
sand
their
uncerta
intiesusingrelatively
briefamounts
ofdata
.
This
meth
od
can
be
use
dto
identify
pote
ntially
time-varying
dynamicsmodels,sh
orte
n
wind
tunnelte
stdurations,
and
supply
first
orderstability
marginsforadaptivenonlinear
controlalgorithms.
1of1
AmericanInstituteofAeronauticsandAstronautics
Design
and
Manufactu
reofth
eCock
pit
and
Tra
nsm
ission
foraHuman
Powered
Helicopter
CodyKarcher
University
ofMaryland
This
prese
nta
tionwilldeta
ilth
eprocess
ofdesigningandmanufactu
ringth
ecockpit
and
transm
issionofth
eworld
recordse
ttingGameraII
humanpoweredhelicopte
r.Since2008,
Team
Gamera
atth
eUniversity
ofM
aryland
hasbeen
dedicate
dto
building
ahuman-
powered
helicopte
rcapable
ofattaining
theAmerican
Helicopte
rSociety
sSikorsk
yPrize.
To
claim
the
prize,th
ete
am
must
design
and
build
ahuman
powered
helicopte
rth
at
demonstrate
sasu
stained
duration
inhoverof60se
conds,
atso
mepointduringth
atflight
reachesanaltitudeof3mete
rs,
andstayswithin
a10mete
rby10mete
rboxforth
eentirety
ofth
eflight.
Currently,th
ete
am
hasbuilta
vehicle,Gamera
II,which
hasachieved
65
secondsofduration
inhoverand
inase
parate
flightreached
over9feetin
altitude.Atth
e
coreofth
isfeatofengineeringis
thecockpit
and
transm
ission.Thecockpit
ofGameraII
wasdesigned
toplaceth
epilotin
arecumbentposition
and
allow
him
orherto
pedalwith
both
handsand
feet.
Sinceth
epilotoutp
uts
energyin
acycle,th
ecockpit
wasdesigned
to
berigid
undercyclicloadingconditions,
whilestillbeinglightw
eight.
This
goalwasmetby
designingth
ecockpit
asan
assembly
oftw
o-d
imensionaland
three-d
imensionalcomposite
trusses.
Each
ofth
ese
truss
memberswasmanufactu
red
by
acontinuousfilamentwinding
process,allowingtrusseswithdozensofelements
tobeconstructe
din
atimely
fash
ion.The
transm
ission
ofGamera
IIwasdesigned
asa
two
stagesy
stem.
Thefirst
stageconsisted
ofth
epilotpedaling
inth
ecockpit.
Unlike
prior
human
powered
aircraft,th
epilotof
Gamera
IIuse
dboth
hand
cranksand
footpedals
topowerth
evehicle.
Aflywheelwas
also
included
into
this
phase
ofth
etransm
ission
ina
furth
ere!ortto
smooth
the
time
varying
poweroutp
utofth
epilot.
Inth
ese
cond
stage,a
pulley
atth
epilots
feetth
en
droveawinch
system
thatreels
instring
from
largerpulleyslocate
don
theroto
rblades.
Inboth
stages,
itwascritically
importa
ntto
cutweightwhilestillmainta
iningth
equality
ofth
eperformance
ofeach
component.
This
provided
many
unique
challenges,
which
included
thedevelopmentofa
chain
tensioning
system,th
emanufactu
ring
oflightw
eight
roto
rpulleys,
and
theoptimization
ofth
eflywheeldesign.
1of1
AmericanInstituteofAeronauticsandAstronautics
Lincoln
Labora
tory
RadarIn
troduction
ForStu
dent
Engineers
RaoulOuedraogo
MIT
Lincoln
Laboratory
TheM
ITLinco
lnLabora
tory
RadarIn
troduction
forStu
dentEngineers
(LLRIS
E)pro
-gra
mis
anew
two-w
eek,re
sidential,
pro
ject-b
ase
d,enrich
mentpro
gra
mwhich
wasco
n-
ducted
for
the
firsttime
during
July
2012
for
outsta
nding
students
from
New
England
who
are
ente
ring
their
senioryearofhigh
school.
Thegoalofth
epro
gra
mis
topro
mote
students
inte
rest
inscience
,te
chnology,
engineeringand
math
.Participatingstudents
gain
anin-d
epth
experience
inra
dararchitecture
,signalpro
cess-
ing,and
ora
lpre
senta
tion
thro
ugh
ase
riesofinte
ractivelecture
s.Stu
dents
are
challenged
tobuildalow-cost,2.4
GHz,
frequency
-modulate
dco
ntinuouswave(F
MCW
)Dopplerand
rangera
dar,
andto
demonstra
teitsfu
nctionality
usingcr
eativepro
blem-solvingstra
tegies.
This
hands-onpro
gra
mallowsstudents
towork
inastate
-of-th
e-art
labora
tory
withhighly
talente
dscientistsand
engineers.
Duringth
etw
o-w
eek
course,students
are
house
din
an
MIT
campusre
sidence
hall
and
pro
vided
with
transp
ortation
toLinco
lnLabora
tory
for
their
lecture
sand
radar
pro
to-
typing.
Instru
ction
ispro
vided
atM
ITLinco
lnLabora
tory
inLexingto
n,M
assach
use
tts,
by
Labora
tory
tech
nicalsta!
and
underg
raduate
and
gra
duate
students
from
MIT
.The
pro
gra
m,including
room
and
board
and
expense
sforth
epro
toty
pera
dars,is
freeto
all
participating
students.
Beca
use
ofth
esu
ccess
ofth
eLLRIS
Epro
gra
m,th
eLabora
tory
plansto
expand
thepoolofapplica
nts
tohigh
schoolstudents
acr
oss
thenation.Deta
ils
ofth
ese
lection
pro
cess
ofth
eparticipants,th
evariousco
urses,
the
architecture
ofth
eFM
CW
radar,
and
thefu
ture
ofth
epro
gra
mwillbepre
sente
d.
1of1
AmericanInstituteofAeronauticsandAstronautics
SuperconductingReso
nantlyCoupled
Wireless
Power
Tra
nsfer
Matthew
Marcus,Tim
Russell,RaymondSedwick
University
ofMaryland,CollegePark
Reso
nantinductivepowertransferhassh
ownpro
miseasameth
odofsu
pplyingelectrica
lpowerwirelessly
oversh
ort
dista
nce
s.Such
systemshavemanyapplica
tionsin
space
flight,
such
as
powering
lunar
rovers
from
are
mote
power
plant,
allowing
for
more
versatile
travel.
Reducing
losses,
such
as
those
due
toohmic
(resistive)
losses,
inth
einductive
coilsofth
ese
systemsca
nallow
forsignifica
ntlyhigherpowertransfer,
andgre
ate
rra
ngeof
powertransfer.
Pre
viouswork
use
daco
ilco
nstru
ctedwithsu
perc
onductingwirefabrica
ted
with
abismuth
stro
ntium
calcium
copperoxideco
re(1
G)in
theinductivepowertransfer
system.However,
this
typeofco
ilsh
owed
little
impro
vementoveraco
nventionalre
sistive
coil.
We
believe
this
isdue
toth
esk
ine!ect,which
cause
selectricity
totravelonly
along
theoute
rlayerofth
ewire,traveling
entire
lyth
rough
there
sistiveoute
rlayer,
and
bypassing
thesu
perc
onducting
core
.To
test
this
theory
,weare
developing
asy
stem
that
willutilize
aco
ilco
nstru
cted
ofa
new
type
ofsu
perc
onducting
wire
(2G),
inwhich
the
superc
onductinglayeris
close
toth
eoute
redgeofth
ewire.W
henco
mplete
,re
sultswillbe
compare
dwith
perform
ance
inform
ation
from
a1G
high
tempera
ture
superc
onductorco
iland
anon-superc
onducting
coil.This
talk
willpro
videan
overv
iew
ofre
sonantinductive
powersy
stemsand
there
late
dsp
ace
applica
tionsofth
iste
chnology,
and
theim
portance
ofre
ducing
lossesin
thesy
stemsinductiveco
ilin
ord
erto
impro
veperform
ance
.Then
itwilldiscu
ssth
edi!
ere
nce
betw
een
1G
and
2G
wire,highlighting
theanticipate
dbenefits
ofth
e2G
wire,and
describean
experimenta
lse
tup
thatwillbedeveloped
toco
mpare
the
perform
ance
ofa
system
using
aco
ilco
nstru
cted
from
1G
wire
toa
system
with
aco
ilusing2G
wire.
1of1
AmericanInstituteofAeronauticsandAstronautics
Investigation
on
WingFuselageofUnmanned
Mini-Air
Vehicle
usingSTAR-C
CM
+
Bharath
Madduri,Dr.ThundilKaruppaRaj
University
AtBu!alo
Micro
Air
Vehicles(M
AVs)
are
catchingmore
and
more
attention
forth
eir
applica
tions
incivilian
and
military
fields.
Unmanned
air
vehiclesin
the
same
class
are
exte
nsively
use
dforsu
rveillance
purp
ose
s.Demand
forhigh
altitude,low
cost,lightweightUM
AVsis
continuously
incr
easingfrom
variousse
ctors.Thelow
speed
and
thesm
all
asp
ect
ratio
of
wingsofth
ese
vehiclesgenera
teaparticularflow
regim
eth
atis
stillnotwell
understo
od.
Since
theth
eorieson
theaero
dynamicsoflow
Reynoldsnumberflowsare
yetto
beunder-
stood
and
wind
tunnelexperiments
cost
long
periodsand
gre
atexpense
s,th
enumerica
lsimulation
base
don
computa
tionalfluid
dynamics(C
FD)is
agood
appro
ach
toadopt.
This
investigation
focu
seson
theinte
rfere
nce
e!ectsth
atocc
uron
basicth
reety
pesof
Wing-F
use
lagegeometriesth
atare
considere
dsu
itable
foradesign
ofan
airplaneinte
nded
toopera
teatlow
subso
nic
speedsathigh
altitude.Thefollowingpaperwould
conce
ntrate
on
flow
chara
cteristicsacr
oss
di!
ere
ntwing-fuse
lagegeometriesofM
AV
thatwould
assist
indeveloping
aUM
AV
suitable
tomaneuverathigh
altitudes.
The
main
conce
ntration
would
bedealt
upon
on
Inte
rfere
nce
Dra
gacr
oss
thewing-fuse
lageinte
gra
tion’s
subjected
todi!
ere
ntpara
mete
rs.
Wing-F
use
lage
sizing
playsa
majorro
lein
designing
and
ispre
sente
din
deta
il.
Air-
foil
and
wing
analysisare
work
ed
inXFLR5
(Airfoil
Work
Bench
)th
atpro
duce
alm
ost
exact
resu
ltsforlow
Reynoldsnumberflightco
nditions.
CFD
(Sta
rCCM
+)simulations
usingvariousco
mputa
tionalmodels
are
inte
nsively
doneon
these
geometriesand
thebest
configura
tion
thatpro
duce
shigh
lift
among-stth
eentriesis
identified.
1of1
AmericanInstituteofAeronauticsandAstronautics
TheIm
plementation
ofVortexGenera
tors
forGro
und
Vehicles
Jose
Mondragon
University
ofMaryland,CollegePark
This
pre
senta
tion
willdescribeth
eim
plementa
tion
ofvortexgenera
tors
(VGs)
inord
er
tore
duce
pre
ssure
dra
gon
gro
und
vehicles.
So
far,
vortex
genera
tors
have
been
widely
use
don
aircr
aftsto
inhibit
flow
separa
tion
and
incr
ease
themaxim
um
lift
coe!cient.
On
the
oth
er
hand,when
VGs
are
implemente
dfor
cars,th
ey
willpro
vide
are
duction
on
pre
ssure
dra
g.
This
experimentis
conducted
inord
er
toco
ver
certain
factors
thatwillallow
us
todete
rmine
the
e"ectiveness
ofvortex
genera
tors.
These
factors
include
the
heightofth
eboundary
layer,
theangle
ofattack
with
there
spect
toth
eupco
mingflow
and
thenumber
ofVGsneeded
.Theheightofth
eboundary
layerwillpro
videinform
ation
on
how
farth
eVGswillbe
place
dfrom
the
frontofth
eca
r.In
addition
toth
at,
itwillenable
usto
dete
rmine
the
criticalloca
tion
where
the
VGsare
no
longere"ective
inord
erto
reduce
dra
g.Thech
angingangle
ofattack
isanoth
erim
portantexperimenta
lfactorth
atallowsus
tose
eth
edevelopmentofth
evortex
inth
einco
ming
flow.This
pro
videsqualita
tiveand
quantita
tiveinform
ation
on
how
thesize
ofth
ewakebehind
thevehicle
isa"ected.
The
numberofVGsneeded
isanoth
erco
nstra
inth
atneedsto
be
explore
d.
These
elements
ofth
eexperimentwilldete
rminehow
e"ectiveth
eVGsare
inaform
ation
and
how
those
form
ationssh
ould
be
arranged.
The
pre
liminary
resu
ltsfrom
this
experimentare
being
dete
rmined
thro
ugh
SolidW
ork
sFlow
Sim
ulation,in
ord
erto
eliminate
theleast
e"ective
configura
tions.
Afterw
ard
s,windtu
nnelte
stingwillbeco
nductedin
ord
erto
obta
invalida-
tionfrom
theflow
simulationdata
.In
additionto
that,
flow
visualiza
tionwillbeco
nducted
inord
erto
obse
rveth
evortex
form
ation
and
thesize
ofth
ewake.
With
theim
plementa
tion
ofth
evortexgenera
tors,it
isexpected
tore
duce
theamount
ofdra
gforc
eactingon
gro
und
vehicles.
1of1
AmericanInstituteofAeronauticsandAstronautics
Chara
cterization
ofBistable
TapeasaGravity
Gra
dientBoom
Jin
Kan
g,Joh
nKelly,Austin
Kelly,Ethan
Albrecht,ZacharyGri!tt
United
StatesNavalAcadem
y
One
ofth
emany
pro
blemsassociate
dwith
launch
ing
sate
llitesinto
orb
itis
orienting
these
nso
rsco
rrectly
with
theEarth.Past
pro
jectshavetried
tore
medy
this
pro
blem
by
installing
agra
vity
gra
dientboom
into
the
body
ofth
esa
tellite.
The
conce
ptbehind
agra
vity
gra
dientboom
isth
atonce
thesa
telliteexitsth
eEarthsatm
osp
here
,a
weighte
dboom
would
deploy
and
the
di!
ere
nce
sbetw
een
the
gra
vitationalstre
ngth
acting
on
the
mass
ofeach
side
ofth
eboom
would
orientth
esa
tellite
inre
lation
toth
ece
nte
rofth
eEarth.
Oth
er
universities,
such
asDre
xelUniversity,
use
da
tape
measu
reasa
gra
vity
gra
dientboom.
The
tape
measu
reboom,th
ough
e!ective
inorienting
the
sate
llite,had
many
faultsin
itsdesign.
The
deploymentofth
eta
pe
measu
reca
use
da
gre
atdealof
vibra
tion
and
shock
which
can
adversely
a!ect
the
sate
llite
components
and
opera
tion.
Additionally
theforc
eca
use
dby
thedeploymentofth
eboom
haspote
ntialto
damageth
ebody
ofth
esa
tellite.
Weinte
nd
tote
stabista
ble
tapepro
vided
tousby
Air
Forc
eRese
arch
Lab
(AFRL)as
amore
e!ectivegra
vity
gra
dientboom.Thebista
ble
tapein
contrast
toth
eavera
geta
pe
measu
reis
both
stable
inth
erigid
deployedstageandth
estowedstage.Ourstudyinte
nds
toch
ara
cterize
thedeploymentofth
ebista
ble
tapebymeasu
ringth
eforc
e,vibra
tions,
and
acc
elera
tion
ofth
eta
pesdeploymentand
toestablish
asy
stem
todampen
these
e!ects
on
thesa
tellite.In
ord
erto
dampen
theforc
eand
vibra
tion
cause
dby
thebista
ble
tapes
deployment,
weinte
nd
toattach
an
80gcy
linderfilled
with
asp
ecificliquid.This
demon-
stra
tion
willsh
ow
thedeploymentofth
ebista
ble
gra
vity
gra
dientboom
and
ourmeth
od
ofdampeningth
eforc
edueto
itsdeployment.
1of1
AmericanInstituteofAeronauticsandAstronautics
Mappingfrom
theUnmanned
Vehicle
GabrielLadd
AdvancedConcepts
Consulting
Mapping
from
any
aircraft
ischallenging
tostartwith.M
apping
from
aUAS
bring
a
uniquese
tofproblems.
Tocreate
agood
unmanned
mappingsy
stem
you
haveto
consider
manytradeo!s.
Thechiefconstraintafterweightandpoweris
data
application.This
make
theta
skofageosp
atialengineerin
aremote
sensingcompanyis
tobridgeth
egap
betw
een
application
and
hardware.
Itis
the
translation
betw
een
needsofpeople
who
may
know
noth
ing
ofaircraft
and
engineerswho
need
deta
iled
specificationsfora
very
constrained
world.This
talk
willcoverso
meofth
eessentials
thingsto
think
aboutwhen
designing
a
UAS
mappingsy
stem.
1of1
AmericanInstituteofAeronauticsandAstronautics
FreeFlightTestingTech
niqueforAvianScale
Flapping
WingUn-m
anned
Air
Vehicle
Aim
yW
issa
,Jared
Grauer
,NelsonGuerreiro,Yashwan
thTummala,
Cornelia
Altenbuchner,Dr.
Jam
esHubbardJr.
,Dr.
MaryFrecker
University
ofMaryland
Unmanned
AerialVehicles(U
AVs)
are
pro
lifera
tingin
both
thecivil
and
military
mar-
kets.
Flapping
wing
UAVsororn
ithopte
rshaveth
epote
ntialto
combineth
eagility
and
maneuvera
bilityofro
tary
wingaircr
aft
withexce
llentperform
ance
inlow
Reynoldsnumber
flightre
gim
es.
These
traitspro
miseoptimized
perform
ance
overmultiple
mission
scenar-
ios.
The
objective
ofth
ispre
senta
tion
isto
pre
senta
novelfree
flightte
sting
tech
nique
foravian
scale
flappingwingun-m
anned
air
vehicles.
Theflightte
stto
ok
place
atW
right
Patterson
Air
Forc
eBase
inth
eAir
Forc
eRese
arch
Labora
tory
MAV
indoorflightfacility.
This
facility
conta
insth
elarg
est
Vicon
motion
track
ing
facility
inth
eU.S.A
and
maybe
theworld.53Reflectivetrack
ingmark
ers
were
place
don
theorn
ithopte
r’swings,
tail
and
fuse
lage.
The
orn
ithopte
rwashung
from
ate
ther
and
wasflown
diagonally
acr
oss
the
room.
The
x,y
and
zpositionsofth
ese
53
mark
ers
were
track
ed
and
post
pro
cessed
togive
deta
iled
time
histo
ryforth
eorn
ithopte
r’skinematics
and
dynamics.
Variouswings
configura
tionswere
tested
during
theafore
mentioned
flightte
steach
formultiple
flights.
Resu
ltspre
sente
dsh
owsth
atfreeflightwasindeed
ach
ieved
forall
thete
sted
wing
con-
figura
tions.
Alsoth
ete
stdata
show
thatacc
ura
temark
ertrack
ing
wasach
ieved
and
that
consistentand
repeata
ble
kinematics
were
obta
ined,th
usabro
ad
spectru
mofhigh
fidelity
flightdata
isnow
readilyavailable
forfu
ture
modeling.This
flightte
stse
tsnew
pre
cedent,
asit
washeld
inth
elarg
est
indoorflightfacility
inth
eU.S.A
.M
ore
over,
theorn
ithopte
rth
atflew
during
this
test
wasth
elarg
est
flapping
wing
vehicle
tobe
everte
sted
inth
isfacility
and
itca
rried
themost
numberoftrack
ingmark
ers.
1of1
AmericanInstituteofAeronauticsandAstronautics
ACommonExplora
tionArchitectu
reforth
eDetection
ofLifein
theSolarSystem
MarioChris,ColinHow
ard,Michael
Starr,VictorTrofimov,James
James
Xavier
HighSchool,AvonHighSchool,GreaterHartford
Academ
yofMath
andScien
ce
Inconsidering
the
search
for
extrate
rrestriallife
asone
ofth
eprim
ary
objectivesof
conducting
inte
rplaneta
ry
spaceexploration,many
planets
and
corresp
onding
moonscan
be
cate
gorized
asfeasible
environments
forlife.
Inparticular,M
ars,
and
the
icy
moons
ofJupiter
and
Satu
rn,are
worth
examining.
The
moonsofmost
inte
rest
toth
escien-
tificcommunity
and
specifically
addressed
inourrese
arch
areEuropa,Titan,Enceladus,
Ganymede,andCallisto
.W
hendesigninganoverarchingframeworkforane!cientpilote
d
spaceexploration
program
tostudyth
eaforementioned
regionsofinte
rest,it
isim
porta
nt
tota
ke
into
accountsp
acecraft
components
and
maneuversaswell
asmission
scenarios
once
adestination
ischose
n.
Some
asp
ects
ofth
emission
trajecto
ry
thatare
evaluate
d
include
the
usa
ge
ofa
trailing
toroidalballute
toslow
the
spacecraft
and
decrease
con-
vectiveheatingaswell
asaerocaptu
remaneuvers.
Hohmann
transfersand
therecognition
ofcorridor
width
when
landing
are
also
explored
asuniform
frameworksfor
trajecto
ry
calculations.
Inte
rmsofpropulsion,abim
odalnuclearth
ermalrocketis
propose
dasth
e
most
practicable
solution.Thepurpose
ofth
ebim
odalrocketis
tomaxim
izee!ciency
by
utilizing
thenuclearth
ermalpowerplantasa
sourceofboth
high
thrust
and
low
thrust
propulsion
via
atraditionalnuclear
rocketand
aXenon
Ion
thruster
resp
ectively.
The
nuclearreacto
ris
tobe
constructe
dso
thatth
epoweroutp
utcan
be
modified
betw
een
thetw
oformsofpropulsion,aswell
asto
providepowerforth
emiscellaneousneedsofth
e
crew
and
spacecraft.Additionalfu
elis
tobegath
ered
atth
edestination
site
via
theuse
ofin-situ
propellantcreate
dfrom
the
reso
urcesavailable.
Inorderto
ensu
re
the
pilots’
safety,riskfacto
rswillbeaddressedbymeansofachievingartificialgravitywhennecessary
and
radiation
prote
ction.
According
toth
einte
nsity
ofth
eradiation
area,variousmod-
ulesto
bringth
eastronauts
toth
edestinationandbacke"ectively
areconsidered.M
ission
scenariosarealsoexaminedwithcombinationsoffeatu
ressu
chashabitat-hopping,icepen-
etrating
cryobots,and
surface
sample
collection.
Itis
explored
how
coordinate
drobotic
exploration
can
most
e"ectively
precedepilote
dmissionsand
establish
abase
ofinforma-
tion.Thesu
rfacecollection
reflects
ase
arch
forlife
and
reso
urceson
thedestination
and
a
common
instrumenta
tion
and
collection
framework
isexplored.Forpilote
dmissions,
the
conceptofhabitat-hopping
considersth
eestablish
mentofvarioushabitats
on
thesu
rface
ofth
edestination
which
would
serve
astransitionalpoints
fora
traveling
mission
team.
The
variousmeth
odsexplored
share
the
common
purpose
ofincreasing
the
e!ciency
of
the
mission
and
allow
for
amaxim
um
exploration
area.
An
asp
ectofth
emission
also
discussed
isth
euse
ofth
eflightcraft
on
unmanned
missionsasa
reconnaissa
nceorbiter,
vastly
increasingth
einformationgath
eringlifetimebeyondth
atofso
lely
thesu
rfaceexplo-
ration
and
reducing
mass
waste.This
iscomplemente
dby
variousoth
erinstrumenta
tion
tobeleft
on
ornearth
esu
rfaceafterth
ecompletion
ofth
eprim
ary
objectiveswhich
will
transm
itvariousinformation
toearth
via
thecommunication
infrastructu
recreate
dbyth
e
initialmission.Overall,by
employingth
ese
innovative,yetviable
design
attribute
sin
lieu
ofth
econventionalmeth
odscurrently
employed
by
unmanned
spacecraft,th
eth
orough
design
and
exploration
structu
recreate
dwillallow
thescientificobjectivesoffu
turesp
ace
exploration
missionsto
bebeoptimally
achieved
and
thepossibility
ofextrate
rrestriallife
tobemorefu
lly
tested.
Theauth
orswould
liketo
acknowledgeth
esu
pportofProfessorBriceCassenti
and
the
University
ofConnecticutforth
eir
help
inth
epreparation
ofth
ispaper.
1of1
AmericanInstituteofAeronauticsandAstronautics
ACommonExplora
tionArchitectu
reforth
eDetection
ofLifein
theSolarSystem:Tra
jecto
ryCalculations
and
theJupiterSystem
MarioChris
Xavier
HighSchool
Essentialto
the
planning
ofany
space
mission
isth
eprocess
ofcalculating
required
velocitiesandtrip
times,
andresu
ltantmass
ratios,
ofth
edesiredtrajecto
rybetw
eenEarth
and
the
inte
nded
destination.
These
necessary
calculationswere
conducte
dto
design
a
frameworkforasp
acemission
toanyofth
ese
veralplanets
and
moonsin
theSolarSystem
thatmay
be
capable
ofsu
staining
life.
Jupiterand
itsmoons,
Europa,Ganymede,and
Callisto
,are
among
the
most
plausible
environments
for
life.
However,when
planning
apilote
dmission
toJupiter,th
eharmfu
lradiation
field
wasa
major
concern
thatwas
addressed,asit
isim
porta
ntto
take
note
ofany
risksto
the
crew’s
health.
Inaddition,
scenarioswereconsidered
such
thatoneofth
emoons,
preferably
safe
tohumans,
may
be
use
dasabase
tocontrolinvestigationofth
eoth
ertw
omoons.
TheenvironmentofJupiter
and
itsmoonswerealsostudied
foradiscussion
ofpossible
utilization
forlife
supportand
in-situ
propellant.
Taken
asa
whole,th
ese
examinationsofpossibilitiesoffu
turepilote
d
missionsto
Jupiterand
itsicymoons,
alongwith
calculationsforcorresp
ondingtrajecto
ry
requirements,may
provebeneficialin
these
arch
forextrate
rrestriallife.
1of1
AmericanInstituteofAeronauticsandAstronautics
ACommonExplora
tionArchitectu
reforth
eDetection
ofLifein
theSolarSystem:M
ission
toth
eJovian
Icy
Moons,
Euro
paand
Enceladus
Michael,ColinStarr,How
ard
AvonHighSchool,GreaterHartford
Academ
yofMath
andScien
ce
Acr
ucialasp
ect
ofanymissionis
theexplora
tionofth
edestinationplanetormoon.On
thesu
rface
ofth
eJovian
IcyM
oons,
theprimary
objectiveis
todete
rmineth
eexiste
nce
of
an
underg
round
oce
an,itsexte
nt,
and
itspote
ntialforth
edevelopmentofpast,pre
sent,
orfu
ture
exta
ntextrate
rrestriallife.
On
Euro
pa,scientificanalysishasdete
rmined
that
there
islikely
tobean
enorm
ousliquid
seaunderro
ughly
10milesofice.W
hilepre
vious
investigation
ofEnce
ladushasbeen
less
conclusive,and
the
moon
ismuch
smallerth
an
itsco
usin,th
epre
sense
oficegeyse
rslikewiseindicate
sacr
yolayerto
somedegre
eactive.
On
both
Euro
paand
Ence
ladus,
icemelting
cryobots
should
beuse
dto
melt
thro
ugh
the
froze
ncr
ust
andre
ach
thewate
rundern
eath
.Powerforth
ese
devicessh
ould
comefrom
on
board
nuclearre
actors
and
thepro
duction
ofin-situ
pro
pellant(themost
feasible
option
ishydro
gen
and
oxygen
from
ice).
The
explora
tion,both
unmanned
and
manned,oficy
moonswillbea
long
term
endeavor,
and
willinvolvemultiple
obse
rvationalto
ols
from
ase
lection
ofth
seavailable.M
issionsto
both
Euro
paand
Ence
laduswillleavemultiple
base
modulesandre
connaissa
nce
orb
iters
thatwillco
ntinuepro
vidinginform
ationanddata
over
alongperiod
oftime.This
willse
rveto
best
pre
pare
forapossible
manned
mission
inth
efu
ture
.Ofall
thebodiesin
theso
larsy
stem,th
eicy
moonsofJupiterpro
videth
ehighest
pro
babilityoflife,butare
stillte
nsofyears
away,
and
thussh
ould
beth
oro
ughly
explore
dsa
fely
priorto
any
manned
mission.
*NOTE:This
isth
eth
ird
offourpre
senta
tionsby
HS
students
mento
red
by
Pro
fessor
Brice
Cassenti
ofth
eUniversity
ofConnecticut.
1of1
AmericanInstituteofAeronauticsandAstronautics
GPGPU
implementation
and
bench
mark
ingofth
e
unsteadyvortexlatticemeth
od
Christopher
Chabalko,BalakumarBalachandran
University
ofMaryland
Theunsteady
vorte
xlatticemeth
od
iswidely
known
foraccuracy
undercerta
incondi-
tionsand
robustness
inmodeling
theaerodynamicsofdi!
erentbodiesincluding
flapping
systemsin
unsteady
flows.
Thecomputa
tionalsu
broutinesin
this
formulation
can
beex-
pressed
aslinearalgebra
base
droutines.
Whilelinearalgebra
may
bea
convenientform
ofnota
tion,th
ememoryrequirements
aredetrim
enta
lto
computa
tionalperformance.Ex-
pressingth
eroutinesasnested
forloopsmitigate
sunnecessarymemoryaccess
whilemain-
tainingfidelity
inth
ecalculations.
Twodi!
erentim
plementa
tionsofasu
broutineuse
din
thevorte
xlatticecalculationsareconsidered.Oneis
aM
atlabim
plementa
tionwhichta
kes
advanta
geofvecto
roperations,
and
theoth
eris
an
implementa
tion
nVidiasCUDA
frame-
work.Thetw
oim
plementa
tionsarevalidate
dandcomparedin
benchmarkingapplications.
Asanexample
applicationconsiderth
einfluenceofanundulatinggroundonanairfoilata
fixed
angle
ofattackin
an
unsteadysy
stem.Thelargesp
an
bodyreprese
ntingth
eground
requiresa
high
levelofcomputa
tion,and
asignificantincrease
incomputa
tionalsp
eed
is
expecte
din
theCUDA
implementa
tion.
1of1
AmericanInstituteofAeronauticsandAstronautics
ACommonExplora
tionArchitectu
reforth
eDetection
ofLifein
theSolarSystem
Segment4:Piloted
Explora
tion
toTitan
and
Mars
Victor,James
Trofimov,Wang
GreaterHartford
Academ
yofMath
andScien
ce
The
identification
ofplanets
and
moonswithin
ourso
larsy
stem
asconta
ining
life
or
beingcapable
ofsu
pportinghuman
life
hasbecomeparticularly
importantaswebegin
toask
keyquestionsaboutth
ecapabilityoflife.In
particular,
Mars
and
Titan
o!erinte
rest-
ing
case
studiesofpossible
life-conta
ining
environments.Thedesigning
ofan
overa
rching
framework
forapilote
dmission
toth
ese
planets,among
oth
ers,could
facilitate
spaceex-
plora
tionofth
ere
gion.It
isim
portantto
takeinto
accountdi!
ere
ncesin
these
twoplanets
and
the
arising
di!
ere
ncesin
design
faced
by
each
,and
recognize
similaritiesth
atcould
resu
ltin
asp
ects
being
developed
thatcould
beuse
dto
travelto
both
destinations.
Such
asp
ects
ofth
emission
include
aero
captu
re,bim
odalnuclear
therm
alro
cketpro
pulsion,
multiple
habitation
modules,
in-situ
pro
pellantpro
duction,and
long-rangebuggies.
Some
asp
ects
ofth
emission
willhaveto
beta
ilore
dto
each
destination.Among
these
are
des-
tination
selection,investigation
and
access,and
post-retu
rndata
collection.In
Titan,th
epossible
investigation
are
aswillhave
tobe
keptopen,asth
ere
are
partsofTitan
whose
surfaceis
notwell-d
ocumente
d,work
thatwillbedoneon
themission.Points
ofinte
rest
includeth
enorthern
hemisphere
,which
conta
insmany
hydro
-carb
on
lakes,
someofwhich
seem
tohavech
anged
sizesoverth
eyears.In
addition,th
eso
uth
ern
hemisphere
ofTitan
sportsaperm
anenthurricane,which
would
beofprimemete
oro
logicalinte
rest.Further-
more
,se
ismologicaland
geologicalinvestigationssh
ould
beta
ken
on
Sinlap
Cra
ter,
oneof
thefourconfirm
edim
pactcra
ters
ofTitan.This
considera
ble
bre
adth
ofinvestigationsite
scallsforth
epro
duction
ofnumero
ushabitats
and
cre
wtransp
ortation
vehiclesto
shuttle
thecre
wfrom
destination
todestination.Anoth
erfeatu
reofTitan
underinvestigation
isitsmete
oro
logicalactivity.Forth
ispurp
ose
,aswell
asto
documentth
esu
rfaceofTitan
and
changesth
ere
of,
itwould
bebeneficialto
mainta
inpro
besin
orb
itaro
und
Titan
and
on
lander
site
safter
mission
completion.
Mars
exhibitsth
ebest
explora
tory
targ
etfor
pilote
dsp
aceexplora
tionin
thenearfu
ture
.Theprimary
objectiveforapilote
dM
ars
mis-
sion
isto
search
forsignsoflife
on
theplanetutilizinghuman
analytical-capabilities.
The
rationale
forse
nding
humansinto
space,asoppose
dto
robots,is
simply
because
humans
can
accomplish
more
than
any
robotcan.
Robots
have
been
continuously
exploring
and
monitoringth
eplanetforth
elast
few
decades,
soth
enextlogicalstep
isforhumansto
be
sentto
Mars.Themission
toM
ars
isdesigned
inaway
thatastro
nauts
willhaveenough
time
toe!ectively
explore
avast
range
ofth
eplanet.
Itis
expensive
tose
nd
astro
nauts
into
spaceand
bringth
em
back
,th
usit
isvitalto
utilizeasmuch
outofonetrip
toM
ars
aspossible.An
explora
tion
ofM
ars
willincludeastudy
ofth
egeologicaland
atm
osp
heric
conditionsofdi!
ere
ntre
gions,
and
most
importantly,heavy
sample
collecting
forfu
rther
analysisupon
there
turn
toEarth.
Thekey
toth
esu
ccess
ofa
Mars
mission
involving
along-term
stay
and
vast
explora
tion
are
ais
theuse
ofnumero
ushabitatmodules.
*NOTE:This
isth
elast
offourpre
senta
tionsby
HS
students
mento
red
by
Pro
fessor
BriceCassenti
ofth
eUniversity
ofConnecticut.
1of1
AmericanInstituteofAeronauticsandAstronautics
Low-E
arth
Orb
itReliabilityand
Maintainability
Para
digmsand
Their
Application
toDeep-S
pace
Explora
tion
Mariel
Rico,Melissa
Flores
TheGeorgeWashingtonUniversity
AsNASA
developsmore
inte
rest
inDeep-S
pace
(DS)explora
tion,th
ere
are
avariety
of
Reliability,
Mainta
inability,
and
Supportability(R
MS)co
nce
rnsth
atneed
tobeaddre
ssed
tolowerth
erisk
sofloss
ofcr
ew
orloss
ofmission.Low-E
arthOrb
it(L
EO)RM
Spara
digms
are
no
longer
valid
beca
use
ofth
enatu
reofDS
missions.
Environmenta
lfactors
that
need
tobe
acc
ounte
dforinclude
elongate
dtime
periodsin
space
and
gre
ate
rdista
nce
sfrom
the
Earth.
Aco
mpre
hensive
rese
arch
e!ort
hasbeen
putforw
ard
toidentify
RM
Spra
cticesfrom
past
space
flightpro
gra
ms,
and
then
re-evaluate
and
apply
them
into
DS
explora
tion
craft
design
and
pro
cesses.
Thedesign
considera
tionsinvestigate
dincludeth
ero
leofmanagementin
thedesign
pro
cess,overa
llhard
ware
considera
tions,
and
thee!ect
ofhumanfactors
onaDScr
aft.Primary
conclusionsmadeincludedesigningRM
Ssu
pport
along
side
the
space
craft
design
toim
pro
ve
e"ciency
,re
ducing
specialize
dco
mponents
and
tools
tocr
eate
redundancy
,and
designing
hard
ware
toenable
planned
mainte
nance
over
unplanned
mainte
nance
.This
inform
ation
willhelp
space
craft
designers
prioritize
subsy
stemsfordesign
and
mainte
nance
,which
decr
ease
sth
elikelihood
offailure
s.
1of1
AmericanInstituteofAeronauticsandAstronautics
Linco
lnIn
itiativeforThermalLinks(L
ITL)
RonEfromson,AllisonMoore
MIT
Lincoln
Laboratory
Meta
lfoil
stra
psare
currently
use
dto
pro
videstru
ctura
lly
deco
upled
heatco
nduction
path
sin
aero
space
payloads.
The
mass
ofco
pper
or
aluminum
foil
stra
ps
required
tomeetincr
easingheatdissipation
demandshasdesign
engineers
lookingforim
pro
ved
ther-
malmanagementso
lutions.
New,advance
d,lightw
eightmate
rials
can
pro
videmech
anical
flexibility
and
higher
heat
transfer
perform
ance
.M
anufacture
rsofKapto
nand
copper
enca
psu
late
dannealed
pyro
lyticgra
phite(A
PG)stra
pshavepro
mised
conductivity
thre
etimesth
atofco
pperwithaquarterofth
edensity.Heatpip
eswithflexible
bellowsse
ctions
pro
misesimilarbenefits.Thegoalofth
ispaperis
toch
ara
cterize
theth
erm
alre
sistance
and
mech
anicalsti!
ness
ofth
ese
advance
dso
lutions,
compare
them
tomanufacture
rsclaim
s,and
tote
chnologiescu
rrentlyuse
din
designs.
Itwasfound
thatth
eco
nfigura
tionsofAPG
stra
pand
flexible
heatpip
ete
sted
perform
ed
betterth
erm
ally
butare
up
toan
ord
erof
magnitudesti!
erth
an
copperfoil
heatstra
ps.
Ifdesignsca
nto
lera
teso
mesti!
ness,it
isre
commended
thatAPG
stra
psand
flexible
heatpip
esbeco
nsidere
d.
1of1
AmericanInstituteofAeronauticsandAstronautics
Reconstru
ctingth
eF4-U
CorsairsEngineM
ountusing
Modern
Tech
nology
Helen
Zhao,ZhangLiu,Ben
Staniewicz,
ThomasMeehan,MingZhao
AmityRegionalHighSchool
TheChance-V
oughtF4U
Corsa
ir,th
eo!cialstate
aircraft
ofConnecticut,
iscurrently
beingrestoredbyConnecticutCorsa
ir,avolunte
erorganizationdedicate
dto
educatinghigh
schoolstudents
inmath
,science,engineering,andte
chnology.Theobjectiveofth
isproject
isto
use
modern
mate
rialformsto
design
and
restore
the
Corsa
irsengine
mount.
The
website
CT
iHubwasuse
dto
communicate
withSikorsk
yengineersactingasmento
rsonth
e
project.
Toconstructath
reedim
ensionalmodel,aso
ftwareprogram
calledSolidW
orkswas
implemente
d.First,th
erequirements
thatneededto
beadheredto
beforeconstructingth
e
mount,
includingFAA
requirements
and
specificationslaid
outin
thechallengestate
ment,
such
aste
mperatu
rerequirements
and
ultim
ate
load
specificationswererese
arched.After
thatweanalyzed
theoriginalschematicsofth
eenginemountand
theactu
almounts
itse
lf
tomeasu
re,whichwasinputto
SolidW
orks.
Afterrese
archingdi"
erentdesigningmeth
ods,
an
alternativedesign
wasproduced
toim
proveth
eload
distribution
ofth
estructu
re.
In
addition,th
emate
rialwasupdate
dfrom
steel4130
tosteel4340,which
isstrongerand
moreresistantto
fatigue.
1of1
AmericanInstituteofAeronauticsandAstronautics
Accelera
tingth
eair
transp
ortation
systems
transform
ation:asy
stemsengineering,sy
stems
thinkingand
complexitysciencebased
rational
framework
tounifyhereto
fore
disso
ciated
linesof
inquiry
Liviu
Nedelescu
CrownConsulting
Ifth
enextgenera
tion
air
transp
ortation
system
(NextG
en)had
tobech
ara
cterize
din
only
twoword
s,th
elikely
candidate
swould
besy
stemsandco
mplexity.
Whilesy
stemsare
genera
lly
overt
and
explicit,
complexity
isan
implicitpro
perty
ofadvance
dsy
stems.
To
date
systemsare
unquestionably
betterundersto
odth
anco
mplexity,
forwhichaco
mmonly
agre
ed
definition
stilllack
s.Even
so,th
ere
isa
gro
wing
body
ofknowledgeaim
ed
atun-
dersta
ndingand
managingboth
.This
paperpro
pose
sanovelpara
digm
atth
einte
rsection
ofsy
stemsandco
mplexityforacc
elera
tingth
edevelopmentofadvance
dairsp
ace
conce
pts.
Thro
ugh
the
lensofth
epro
pose
dSystemic-O
pera
tional-Phenomenological(S
OP)frame-
work
,end
state
system
traitsare
identified
from
initialco
nce
ptdefinition
phase
s,which
pro
videsinsightinto
thesy
stem
complexity.
TheSOP
meth
odologyaim
sto
reco
ncile
thre
eofth
edisciplinesnece
ssary
and
likely
su!cientforundersta
nding
systemsth
atare
com-
plex:sy
stemsengineering,sy
stemsth
inkingand
complexityscience
.Ofth
eth
ree,sy
stems
engineeringhashad
thebest
reco
rdandhighest
acc
epta
nce
withth
eair
tra!cco
mmunity.
SOP
assertsth
eopera
tionalperspectivehasto
beexpanded
toca
ptu
resy
stemic
traitsand
complexity.
SOP
isdefined
inte
rmsofth
reedisciplinesth
us:
Thesy
stemic
perspective
refers
tosy
stemic
implica
tionsofopera
tionalmech
anismsasgleaned
thro
ugh
theapplica
-tion
ofsy
stemsth
inking;
The
traditionalopera
tionalperspective
remainsth
edominant
conce
ptdefinition
space
with
systems
engineering
as
the
pre
vailing
meth
odology;
The
phenomenologicalperspective,usingco
mplexity
science
,aim
sto
unco
verundesira
ble
con-
tentin
thegeneticmake-u
pofopera
tionalmech
anisms.
Theback
gro
und
section
pro
vides
theore
tica
lco
nsidera
tionsasnece
ssary
conte
xt.
The
subse
quentse
ctionspro
vide
aSOP
definition
developed
from
applica
tion
tose
vera
lNextG
en
conce
pts
and
one
opera
tional
conce
ptcu
rrently
inuse
.SOP
isth
en
use
dasath
eore
tica
lappro
ach
tounify
appare
ntly
orthogonalface
tsofth
eNextG
en
challenge:
rese
arch,modeling
and
simulation,sa
fety,
metrics.
Finally
aco
nstru
ctforair
tra!conto
logy
ispro
pose
d.
1of1
AmericanInstituteofAeronauticsandAstronautics
ExperimentalCalculation
ofAero
dynamic
Forceson
a
FlappingRigid
Wing
David
Coleman
University
ofMaryland,CollegePark,MD
Since
thedevelopmentofth
efirstairplane,fixed-w
ingsandro
tary
-wingshavebeenuse
don
mostly
all
conventionalaircr
aft
togenera
teth
ere
quired
lift.However,
this
isnotth
emech
anism
thatbiologicalorg
anismssu
chasbirdsand
inse
cts,
use
tofly;instead,th
ey
utilize
repeate
dflapping
ofa
pair
oflight-weight,
flexible
wingsto
genera
teth
ere
quired
lift
and
pro
pulsiveforc
es.
The
question
we
are
trying
toansw
er
inth
isre
search
iswhat
advanta
ges
does
the
flapping
wing
ofan
inse
ctor
bird
have
over
the
fixed
or
rota
ting
wings
ofman-m
ade
airplanesand
helico
pte
rs?
Answ
eringth
isquestion
involvesre
plica
tingth
eflappingwings
ofbirdsand
inse
cts,
and
experimenta
llymeasu
ringth
eaero
dynamic
forc
esoflift
and
dra
gth
atare
genera
ted
asth
ewingflapsforw
ard
and
back
thro
ugh
theair.
To
imitate
this
flapping
wing
conce
pt,
aplanar,
rigid
carb
on
fiberwing
ofsize
3x
6x
1/16wasco
nstru
cted
and
mounte
donto
aholderwhich
allowsfreero
tation
alongth
elong
axis
ofth
ewing.Thewingca
nflip
insu
chawayasto
striketh
eair
stre
am
at+40angle
of
attack
travellingeitherforw
ard
orback
ward
.Thewingholderis
mounte
dto
aminiatu
re6
degre
e-of-freedom
balance
atth
ewingro
otca
pable
ofmeasu
ringall
thre
eaxialforc
esand
moments.
Mech
anically,
thewingmust
beflappedforw
ard
andback
ward
tosimulate
thebiological
flightpro
cedure
,andth
isis
donebymeansofanelectrica
lmoto
randdrivech
ain
mech
anism
consistingofamain
gearandtw
olinkages.
Thefinallinkagenotonly
movesback
andforth
inre
sponse
toth
ere
volving
gearwheel,
butholdsasu
pport
stru
cture
towhich
theforc
ebalance
,wingholderand
wingare
mounte
d.Thusth
ero
tatingmotion
ofth
edrivemoto
ris
converted
toaflapping
motion,co
mpelling
thewing
toflip
betw
een
opposing
anglesof
attack
.During
aflapping
test
pro
cedure
,data
from
theforc
ebalance
and
shaft
enco
ders
pro
-vidingforc
es,
moments,pitch
angle
and
flap
position
isre
cord
ed
byLABVIE
W.Thedata
isth
en
analyze
din
MATLAB
and
all
forc
esand
flap
positionsare
plotted
versustime.
However,
theforc
esmeasu
red
by
theforc
ebalance
conta
inboth
aero
dynamic
and
inertial
forc
eco
mponents.In
ord
erto
obta
inpure
lyaero
dynamic
forc
es,
thete
stis
repeate
dwith
theassembly
inavacu
um
chamber,
inwhich
case
only
inertialloadsare
pre
sent,
and
these
inertialforc
esca
nbesu
btracted
from
theto
tal,
leavingju
staero
dynamic
lift
and
dra
g.
Atth
isstagein
theexperiment,
thetimehisto
ryoflift
anddra
gofarigid
flappingwing
hasbeendete
rminedforgivenanglesofattack
,andvariesacc
ord
ingto
thegenera
lexpected
behavior.
Dra
galw
ayspoints
inth
edirection
opposite
oftravel,
and
thusis
negativefor
one
half
ofth
ecy
cle
and
positive
forth
eoth
erhalf.
Lift,
however,
ispositive
forboth
anglesofattack
,and
goesto
zero
asth
ewing
flipsfrom
one
position
toth
eoth
er,
thus
oscillatingfrom
positiveto
negativetw
iceeach
wingflap.This
isasignifica
ntmilestonein
ultim
ate
lyco
mparing
aero
dynamicsofaflexible,flapping
wing
and
those
ofarigid,fixed
wing.
1of1
AmericanInstituteofAeronauticsandAstronautics
ComputationalAnalysisofth
ee!ects
ofPoro
sity
Gra
phitePro
perties
Edwin
Gaddis,RamanaPidaparti
Virginia
CommonwealthUniversity
Gra
phite
due
toits
extraord
inary
mate
rialpro
perties
has
been
use
das
astru
ctura
lmate
rialaswell
asa
key
componentofnuclearre
actors.Athigh
tempera
ture
s,gra
phite
underg
oesincr
ease
dporo
sity
dueto
oxidation
thatch
angesth
emicro
stru
cture
ofth
ema-
terial.
Itis
importantto
acc
ura
tely
chara
cterize
themate
rialpro
pertiesofgra
phiteunder
high
tempera
ture
conditions,
initspristine
condition
and
atvariousinte
rvals
during
its
serv
icelife,and
todevelop
failure
pre
diction
models.Oneofth
emost
widely
use
dch
ar-
acteriza
tion
tools
forgra
phiteis
x-ray
tomogra
phy,
which
pro
duce
sim
agesofth
einte
rnal
stru
cture
ofth
emate
rial.
These
imagesca
nth
en
be
use
dto
reco
nstru
ctCAD
models,
which
intu
rnca
nbe
analyze
dusing
finite-element
meth
ods
(FEM
).This
pre
senta
tion
discu
sseste
chniquesforco
nstru
cting
CAD
models
ofto
mogra
phic
images,
and
forusing
FEM
topre
dictth
ee!ectsofincr
ease
dporo
sity
on
mech
anicaland
therm
alpro
pertiesof
gra
phite.
Resu
ltsobta
ined
from
the
computa
tionalanalysissh
ow
thatYoungsmodulus
decr
ease
swith
incr
easing
poro
sity
and
this
relation
isverified
both
experiments
from
the
lite
ratu
reaswell
asanalytica
lso
lutions.
1of1
AmericanInstituteofAeronauticsandAstronautics
WillPROFAC
and
PHARO
Tra
nsform
Space
Economicsand
Mission
Design?
BlairCapriotti,Derek
Montalvan,NatashaPeake
WorcesterPolytechnic
Institute
Space
travelbeyondearthorb
it,dueto
thecu
rrentnece
ssityforliftingfarmore
fuelmass
than
payload,is
exponentially
expensive.
Orb
iting
fueldepots
are
aviable
solution,but
refillingth
em
would
requireeitherbringingre
sourc
esup
from
Earthssu
rface
oracq
uiring
them
insp
ace
.If
theneed
forliftingre
sourc
esfrom
Earth
could
bere
duce
doreliminate
dwithoutth
ere
quiringamassiveextraction
and
delivery
infrastru
cture
on
themoon
oran
astero
id,th
ere
sult
would
bea
bre
akth
rough.It
would
transform
theeco
nomicsofsp
ace
activity
and
have
massive
implica
tionsforboth
space
craft
and
mission
design.
Atleast
two
tech
nicalpro
posa
lsexistin
the
currentlite
ratu
reth
atfocu
son
the
gath
ering
ofgas
reso
urc
esin
low
earthorb
it(L
EO).
Thefirst,
byatleast
50years,is
PROFAC,invente
dby
Ste
rgeDemetriades(p
ublish
ed
in1959),
butth
isideaso
mehow
dro
pped
outofsightfora
genera
tion.It
wasn
tuntilan
independentre
invention
ofagasgath
eringsy
stem
known
as
PHARO
(byate
am
ledbyAlanW
ilhite)wasente
redinto
aRASCAL
conte
standaward
ed
seco
nd
place
thatth
isideawasre
introduce
d.Both
PROFAC
(in
itsmost
stra
ightforw
ard
andim
mediate
applica
tionin
LEO)andPHARO
requireth
eco
llectionofatm
osp
hericgase
sin
ord
erto
overc
omedra
gto
mainta
inorb
itand
fuelhigh
impulseand
chemicalro
ckets.
Demetriades(J
BIS
,1959)describesPROFAC
asfollows,
”It
isa
deviceth
atorb
itsatan
altitudeofro
ughly
110km,co
llectsatm
osp
hericgase
s,store
sth
eoxygen
tore
fueldevices
for
high-thru
stsp
ace
missions,
thuseliminating
the
need
tolift
oxidizer
toorb
it,while
using
thenitro
gen
inan
Electro
magneticth
ruster(p
owere
dby
solarce
lls,
nuclearpower
oroth
ermeans)
tooverc
omedra
gand
mainta
inorb
itand/oruse
forpro
pulsion
insp
ace
where
highersp
ecificim
pulseis
required.”
Heenvisaged
ord
erofmagnitudere
ductionsof
takeo!
weightand
oth
erlarg
eadvanta
gesforsp
ace
travel.
Wewillco
nte
nd
thatth
efield
isfinally
ready
forth
iste
chnology.
PROFAC/PHARO
isnow
inth
eopen
lite
ratu
reand
Wilhiteclaim
sth
athewaspro
mpte
dto
lookinto
theco
nce
ptbyNASAsChiefTech
nologist.
While
the
majority
position
inth
efield
isstillth
atin-situ
reso
urc
eutiliza
tion
inLEO
isim
possible,clearly
that
view
isbre
aking
down
or
at
least
being
questioned
inso
me
importantplace
s.Significa
ntpro
gre
sshasbeen
madein
developing
theco
mponents
that
would
make
up
such
agas-gath
ering
system
inth
elast
few
deca
des,
which
could
lead
toitsre
aliza
tion
fasterth
an
expected.
Demetriadeshim
self
estim
ate
dit
at10-20
years
from
thestart
ofawell-funded
tech
nologydevelopmentpro
gra
m,aboutmid
care
erforour
genera
tion.
Additionally,
we
would
like
togetaero
space
pro
fessionals
ofourgenera
tion
thinking
aboutth
iste
chnicalca
pability
and
designing
acc
ord
ingly.
Thus,
we
pro
pose
astudentco
nte
stassuming
the
existe
nce
ofa
PROFAC-like
device.
Conte
stants
would
be
ask
ed
toplan
amission
thatis
only
possible
oreco
nomically
feasible
given
PROFAC
as
infrastru
cture
.This
would
highlightth
eadvanta
gesofth
esy
stem
and
limitationsth
efield
face
swithoutit.
By
exploring
whatco
uld
be
ach
ieved
insp
ace
afterth
isbre
akth
rough,
theca
sefordevelopingit
ismade.
1of1
AmericanInstituteofAeronauticsandAstronautics
Pro
posalforan
EducationallyIn
tera
ctiveLunarBase
Exhibit
Justin
White,
DillonLankenau,JulianSullivan
WorcesterPolytechnic
Institute
Since
1970
NASAssh
are
ofth
efedera
lbudgethassh
runk
by
75
perc
ent,
thre
ate
ning
thefu
ture
ofth
eU.S.sp
ace
pro
gra
m.How
can
were
vivein
young
mindsth
eexcite
ment
and
sense
ofdisco
very
thatacc
ompanied
ourfirstvisit
toth
emoon
in1969?
What
ifwe
retu
rnto
the
moon
via
adynamic
educa
tionalexhibit
base
don
acirc
a2069
lunarbase
thatis
tech
nologically
and
eco
nomically
feasible
today,
aspre
sente
dby
Cra
tersville
and
Moon
Capital?
Whatif
this
exhibit
were
inpara
llelwith
asp
iralcu
rricu-
lum
pro
gra
m,which
buildson
itse
lfevery
yearfor6years
with
students
ingra
des5-10in
theW
orc
esterPublicSch
ools
(WPS)sy
stem?
Whatif
italso
pro
videshands-on
learn
ing,
review
forM
CAS
conce
pts
(MA
state
exam),
auniqueyearlyca
pstoneexperience
,and
an
immersiveenvironmentsimilarto
actually
living
and
work
ing
on
themoon?
This
exhibit
could
insp
ire
students,pare
nts,educa
tors,artists,enth
usiasts,
and
pro
fessionals
towork
toward
saco
mmon
goal:
anew
space
ageofdisco
very
.A
single
exhibit
ofelements
found
on
the
moon
could
explain
state
sofmatter,
the
Periodic
Table,andco
mpounds.
Apre
sente
r,forexample,mightintroduce
iron,aluminum,
tita
nium,silico
n,and
oth
ertrace
elements
pre
sentin
thelunarre
golith
.These
elements
may
be
separa
ted
from
the
regolith
using
their
resp
ective
melting
points.
Nitro
gen
and
Carb
on
Dioxide
are
rare
on
the
moon,and
willlikely
be
imported.
This
pre
sents
an
opportunity
todemonstra
tehow
nitro
gen
initsliquid
state
can
lower
the
tempera
ture
ofobjectsenough
tobe
shattere
dwith
lightforc
e.
Plants
harn
ess
energ
yby
consu
ming
card
ondioxide,whichin
aso
lidstate
beco
mesdry
iceandwillsu
blimate
(sta
tech
angefrom
solid
togas)
(07.P
S.09)1
.Thepre
sente
rca
ndoexampleswith
multiple
elements
from
the
periodic
table
(07.P
S.04).
Furtherm
ore
,th
eFahre
nheit,Celsiusand
Kelvin
scaleswillall
beuse
dth
roughoutth
eexhibit
(07.P
S.08).
Anoth
erexhibit
mightfeatu
rero
botics,where
visitors
identify,re
pair,and
implement
robots
forvariouspurp
ose
s(0
5.IS.01).
Visitors
would
beask
edto
imaginewhatfu
nctionit
willperform
(07.T
S.05,07.T
S.07),
and
then
customizearo
botforminingopera
tions,
con-
stru
ction,and
transp
ortation.In
terchangeable
partsmightincludeca
mera
s,te
rrain
com-
patible
wheels,co
mmunication
systems,
and
roboticarm
sand
tools
(08.T
S.01,07.T
S.03).
Visitors
could
test
their
robots,forexample,bymeltingmoon
dust
into
glass
usinglase
rs,
orbre
aking
thro
ugh
lunarcr
ust
with
adrill.
There
willalso
be
controlco
nso
lesallow-
ing
visitors
tointe
ract
with
the
robots
manipulating
the
camera
sorro
tating
the
robot
(08.T
S.06).
This
could
late
rbe
expanded
toinclude
students
controlling
actualro
bots
work
ingon
thelunarbase
,usingco
ntrolco
nso
lesloca
ted
inth
emain
controlro
om
ofth
eexhibit,and
watchingvideofeedsofth
ero
bots
from
their
classro
om.(0
8.T
S.01).
Thepote
ntialforanexcitingandinte
ractiveexhibit
thatinsp
iresandeduca
tesstudents
goes
beyond
the
examples
described
here
.This
exhibit
can
change
the
idea
ofsp
ace
disco
very
from
an
unre
alistic
thoughtto
an
ach
ievable
goalin
themindsofouryouth
,and
futu
regenera
tions.
1of1
AmericanInstituteofAeronauticsandAstronautics
AStrongly
Implicit
Meth
od
forth
eSolution
of
Tra
nsientIn
compressible
ViscousFlow
Pro
blems
NicholasDiZinno,GeorgeVradis
Polytechnic
Institute
ofNYU
Anew
meth
od
forth
eso
lution
oftime-d
ependentincompressible
viscousflow
problems
isintroduced.Themeth
od
takesadvanta
geofa
predominantflow
direction
and
strongly
couplesth
epressureandvelocityfields.
Thegoverningequations,
usingprim
itivevariables,
arediscretized
on
astaggered
grid,and
theso
lution
isgenerate
dby
aline-b
y-linesw
eep
ofth
eflow
field.Alongeach
computa
tionalline,th
eequationsareso
lved
usingan
e!cient
block-tridiagonalalgorithm.
The
meth
od
isfu
lly
implicit
and
doesnothave
any
ofth
e
drawbacksofexistingmeth
ods.
Numericalexperim
ents
show
themeth
od
toberobust
and
e!cient.
Application
ofth
emeth
od
tocanonicalproblemsin
fluid
mechanicsis
prese
nte
d.
1of1
AmericanInstituteofAeronauticsandAstronautics
AdvancingSpaceM
ission
Opera
tionsBest
Pra
ctices
betw
een
theM
ilitary
and
Civilian
Communities
JoshuaAlbers,ChrisRegan
,Jason
Price
TheJohnsHopkinsUniversity
Applied
PhysicsLab
Assp
ace
craft
opera
tionsco
ntinueto
adaptto
thefiscalausterity
ofth
epost
9/11federa
lbudgetenvironment,
thenationalse
curity
and
civilian
space
opera
tionsco
mmunitiesare
incr
easingly
task
ed
with
merg
ing
their
resp
ective
opera
tionsin
ord
erto
ach
ieve
gre
ate
re!ciency
with
limited
reso
urc
es.
Where
once
these
two
environments
existe
din
close
d,
narrowly
defined
opera
tionalse
ttings,
wenow
find
thatth
ese
twoelements
ofsp
ace
opera
-tionsmust
work
inte
rdependentlyto
ach
ievegre
ate
rco
mmonality
acr
oss
multiple
pro
gra
ms.
Both
communitieshavedevelopeddistinctly
di"
ere
ntco
nce
pts
ofsp
ace
craft
opera
tions,
and
norm
alizing
these
opera
tionsto
allow
cross-m
ission
and
intra-m
ission
coopera
tion
willbe
akey
componentin
the
continued
succ
ess
ofDepartmentofDefense
(DOD)sp
ace
mis-
sions.
Whileth
ere
are
nece
ssarily
distinct
di"
ere
nce
sbetw
een
thecivilian
and
DOD
space
missions,
commonalitiesexistaswell.
This
paperwilldiscu
ssth
evariouswaysin
which
the
civilian
and
DOD
space
mission
overlap
inth
eir
capabilities,
and
where
these
capa-
bilitiesca
nbee"ectively
managed
inord
erto
incr
ease
opera
tionale!ciency
and
reduce
dopera
tionsco
st.
By
doing
so,th
eDOD
and
civilian
space
opera
tionsco
mmunitiesmay
be
able
toincr
ease
coopera
tion
betw
een
pro
gra
ms,
there
by
enhancing
mission
capability
whileco
ntinuingto
keep
opera
tionsco
stswithin
budget.
1of1
AmericanInstituteofAeronauticsandAstronautics
SatelliteServ
icing:M
odelingFlexible
Satellite
Dynamics
JustinBrannan
University
ofMaryland
Advancesin
roboticte
chnologyhavesp
arked
anew
agein
sate
llitese
rvicingasmission-
criticalfailuresth
atwould
oncelead
toth
eend-of-life
ofasp
acecraft
can
now
beremedied
byth
euse
ofroboticse
rvicingplatforms.
Inorderto
reach
this
goal,
itis
necessaryto
test
concepts
ofth
ismission
on
Earth
by
usingmodels
and
simulationsto
proveth
efeasibility
ofsu
ch
amission.
Many
capabilitiesare
necessary
tocomplete
this
end-to-end
mission;
howeverth
ispaperfocuse
sonth
eabilityofasp
acecraft
servicerto
grapple
withasa
tellite,
mainly
how
tomodela
spacecraft
with
flexible
appendagesin
orderto
ultim
ate
lyassess
wheth
erornotany
flexible
modesareexcited.
Ifth
ese
flexible
modesareexcited,it
could
leadto
undesirable
motionduringinte
raction
withth
esp
acecraft
servicer,makingit
di!
cult
toestablish
conta
ctbetw
eensp
acecraft
and
possibly
damagingth
esa
tellite.Although
these
models
aresimple
tocreate
inADAM
Sor
Freesp
ace,it
isnecessary
tointroducea
real-timeasp
ectth
atis
abse
ntin
eitherofth
ese
simulation
environments,to
conductverification
testson
aroboticsimulation
platform.It
isth
ereforenecessary
toincrease
thefidelity
ofth
ecurrentsa
tellitemodeluse
din
ground
testingforasa
tellitese
rvicingmission,addingmorecomplexmotionto
analyzehow
flexible
body
dynamicsa"ecthow
asp
acecraft
acts
inresp
onse
toreaction
forcesfrom
arobotic
servicingplatform.
Three
single-axis
flexible
models
were
create
dincluding
avarying
numberofflexible
appendagesin
orderto
analyzealargesa
mple
ofsa
tellitestructu
res.
Foreach
model,
the
rigid
and
flexible
body
mass
and
forcing
matricesareformed
and
combined
tocreate
the
overall
equation
ofmotion
forth
esy
stem.
The
state
ispropagate
dovertime
asvarious
inputforcesandto
rquessimulate
theinte
ractionwithth
esp
acecraft
servicer.Theresu
lting
motion
provides
insightto
how
the
sate
llite
willreactduring
many
stages
ofa
robotic
servicingmission.
Currently,th
issimulation
platform
expressesth
ecombined
rigid
and
flexible
dynamics
byplottingth
ereaction
ofasa
telliteto
agiven
initialforceorto
rqueinput.
Afterfu
rth
er
testing
and
validation
against
asimilar
modelin
ADAM
S,it
willbe
possible
toassess
wheth
erornotmodesh
apeswillbeexcited
todete
rminehow
theflexible
dynamicswill
impactth
eroboticse
rvicingmission.This
modelhasth
ecapability
tobeim
plemente
don
aroboticplatform
forground
testing,and
willbeinte
grate
din
areal-timesy
stem
using
Moto
man
robots
tovalidate
thekinematicsofth
esy
stem.
1of1
AmericanInstituteofAeronauticsandAstronautics
Onboard
Sto
chastic
Constra
intSusp
ension
forVehicle
Health
Monitoring
LouisBreger
DraperLaboratory
Auto
nomousfault
managementhasre
cently
been
identified
asakey
tech
nology
forfu
-tu
resp
ace
missionsin
NASAs2010te
chnologyro
admap.Aninnovativeappro
ach
tovehicle
health
monitoring
(VHM
)is
pro
pose
dusing
constra
intsu
spension
with
parity
space
and
hypoth
esiste
sting
tech
niques.
By
using
models
ofvehicle
components
and
dynamics,
as
well
asexplicitly
usinginform
ation
aboutse
nso
rand
pro
cess
noise,aVHM
algorith
mca
nbe
synth
esize
dth
athastu
nable,pre
dicta
ble
reliability.
An
implementa
tion
ofth
isalgo-
rith
mis
describedandanalyticre
sultsare
reportedth
atdemonstra
teanim
pro
vementover
anoth
ermodel-base
dte
chniquein
thelite
ratu
reth
atdoesnotinco
rpora
teunce
rtainty
in-
form
ation.Sim
ulationre
sultsonamodeledvehicle
GN&C
system
show
similaradvanta
ges
and
demonstra
teth
eVHM
meth
od’s
valueasboth
an
onlineFDIR
tooland
asa
design
analysisto
olforassessingse
nso
rse
lection
and
senso
rplace
ment.
Thestoch
astic
constra
int
susp
ension
algorith
mhasbeen
implemente
dusingamodel-base
ddesign
meth
odology,
au-
toco
ded,and
deployed
asembedded
software
on
aflight-likepro
cessor.
1of1
AmericanInstituteofAeronauticsandAstronautics
ARobot-C
entered
Sim
ulated
LunarBase
InhwanKim
,ErikScott
WorcesterPolytechnic
Institute
The
Worc
esterLunarBase
Exhibit
isa
pro
pose
dscience
and
tech
nology
educa
tional
reso
urc
ece
nte
r,to
be
loca
ted
inth
ebase
ment
ofth
enow-vaca
nt
Worc
ester
Memorial
Auditorium.This
part
ofth
estru
cture
rece
ntly
serv
ed
asaju
venileco
urt,and
isin
much
betterre
pair
than
theupperfloors.
Also
ofinte
rest
isa
small
theate
ratoneend
ofth
ebuilding.It
ishere
thatth
epro
pose
dlunarbase
tourwould
begin,with
an
introductory
briefingand
video.
Theprimary
purp
ose
ofth
eexhibit
willbeto
help
middle
schoolstudents
(gra
des5-8)to
ach
ieveth
eeduca
tionalgoals
setbyth
eM
assach
use
ttsScience
andTech
nologyFra
mework
.Keyco
nce
pts
willbepre
sente
din
auniqueandmemora
ble
setting,withhands-onactivities
and
pra
cticalapplica
tionsofmate
rialco
vere
din
theclassro
om.These
condary
purp
ose
isto
enco
ura
geth
enextgenera
tionofcitize
nsto
beco
meinte
restedin
space
explora
tion,learn
thatso
meth
ing
like
this
ispossible
and
implicitly
make
aca
sefordoing
it.
We
envision
an
exhibit
capable
ofacc
ommodating
aminim
um
offourclassesofup
to32
students
ata
time,with
thepote
ntialto
serv
etw
oorth
reetimesth
atnumber.
The
lunar
base
exhibit
willo!er
awide
variety
ofactivities
including
simple
pro
-gra
mmable
robots,3D
simulationsofexplora
tionandmining,andoth
erare
assu
chascr
ew
residence
s,agre
enhouse
and
mate
rials
pro
cessing.Thegoalis
topro
videasauth
entican
experience
aspossible
within
thescopeofstudents
scientificknowledge.
Betw
een
9:00
am
and
2:00
pm
daily,
fourdi!
ere
ntgro
upswith
thirty
two
students
for
each
gro
up
willto
urth
eexhibit.Afterash
ort
briefingatth
eth
eate
r,th
eguidesforeach
gro
up
willlead
students
todi!
ere
ntactivity
are
as.
The
guide
willpro
vide
explanations
thatco
nta
inEarth
and
Lunar
compariso
ns,
utilizing
inte
ractive
displaysth
atwillallow
students
toactually
experience
thelessons,
notju
stre
ad
and
hearaboutth
em.
There
willbefourmain
activity
are
as:
robotre
pair,ro
botco
ntrol,
human
habitatand
environmenta
lco
ntrol,
with
indirect
exposu
reto
the
rest
ofth
ebase
via
scre
ensloca
ted
thro
ughout
the
facility.
The
exhibits
willbe
designed
tosu
pport
agenera
lfifth-gra
de
curriculum,a
robot-ce
nte
red
seventh
-gra
de
curriculum
and
ach
emistry-oriente
deighth
-gra
de
curriculum.
Eighth
gra
ders
may
also
visit
adi!
ere
nt
site
at
anearb
ybota
nical
gard
en,mock
edupto
simulate
alunargre
enhouse
.Theexhibit
willco
nta
inallth
ere
quired
pra
cticalamenities,
butth
eca
fete
riawillse
rveonly
food
you
could
pro
duce
on
themoon.
Thelunarbase
exhibit
willbea
giftofth
eco
llegesofW
orc
esterto
thepublicschools
ofW
orc
ester.
Lots
ofco
llegestudents
willhavepart-tim
ejobsand
do
pro
jectsforcr
edit
running
thefacility.There
willalso
beclassro
omsto
pro
videlecture
sto
collegestudents,
and
fortrainingte
ach
ers
how
topre
pare
their
students
togetth
emost
outofth
eultim
ate
field
trip,th
eca
pstoneto
their
science
curriculum.
Inourview
itis
notenoughto
claim
thatso
meth
ingca
nbedone.Youhaveto
show
how
itca
nbedone,andexplain
whyit
should
bedone.Forth
isre
aso
n,to
picsth
atdemonstra
teth
era
tionale
fora
lunarbase
willbeco
vere
d,su
chasadvance
daero
space
transp
ort
and
constru
ction
engineering
using
loca
lmate
rials.
We
wantstudents
toundersta
nd
how
alunar
base
could
be
create
d,how
itwillfeed
itse
lfand
pay
for
itse
lf,and
whatsu
cha
facility
could
contribute
toth
efu
ture
ofscience
and
tech
nology.
Itis
an
invitation
tobepart
ofa
gra
nd
adventu
reasth
ehuman
race
takesitsfirstte
nta
tivestepsto
colonize
anoth
erheavenly
body.
1of1
AmericanInstituteofAeronauticsandAstronautics
CCSU
HelicopterFlightSim
ulato
rDesign
&
Fabrication
Improvement
EricRichard,Nguyen
Nguyen,EricOlender,RussellHallow
ell,
Cen
tralConnecticutState
University
Stu
dents
inth
eEngineering
and
Engineering
Tech
nology
pro
gra
msare
inth
epro
cess
ofdesign
and
upgra
dingth
eexistingCCSU
Helico
pte
rFlightSim
ulato
rpro
ject.Figure
1pre
sents
the
existing
flightsimulato
rwith
pilotco
ntroland
mach
ine
partslist.
Figure
2pre
sents
students
usingmach
ineto
ols
tomach
ineflightsimulato
rpartsin
thelab
mach
ine
shop.
Figure
3pre
sents
astudentwelding
flightsimulato
rframes.
The
existing
CCSU
flight
simulato
rmotion
platform
has
two
degre
es
offreedom,ro
lland
pitch
.Figure
4sh
owsth
emaxim
um
angle
forth
epitch
and
roll
motions.
Forth
enextflightsimulato
rpro
ject,im
pro
vements
willfinish
the
mech
anicaland
electrica
ldesignsofth
esimulato
rmotion
base
and
linkth
eflightsimulato
rso
ftware
(X-P
lane9)to
themotion
platform
.An
extra
yaw
(rota
tion)degre
eoffreedom
willbeadded
by
inte
gra
ting
additionalelectro
nic
linearactuato
rswith
thesimulato
r;also,forsa
fety
purp
ose
s,fourpointsa
fety
harn
esses
willbe
added
toth
eco
ckpit
seat.
Adding
this
componentwillallow
the
use
rto
safely
opera
teth
esimulato
rwithoutmoving
aro
und
inth
eco
ckpit
seat.
Inord
erto
powerth
esimulato
rand
all
ofitselectrica
lco
mponents,wewillinstall
apowersu
pply
thatwillhave
theca
pabilitiesto
pull
atleast
twenty
ampsofcu
rrentwhilepro
vidingtw
enty
fourvoltsof
voltageco
ntinuously.
There
fore
,aBK
Pre
cision,M
odel#1964powersu
pply
willbeadded
tofu
lfill
the
electrica
lneeds.
The
flightsimulato
rso
ftware
needsto
have
the
capability
toco
ntinuously
communicate
with
the
simulato
r.The
controlelectro
nicsand
inte
rface
willhave
tobe
update
ddue
toth
eaddition
ofth
eyaw
axis
ofro
tation.
We
willneed
electrica
lhard
ware
thatwillbeable
toanalyze
realtimedata
feedback
from
thesimulato
r.An
F.P
.G.A
.,alsoknown
asaField
Pro
gra
mmable
Gate
Array,
willbeable
tosu
!ciently
fulfill
these
task
s.All
electrica
lhard
ware
and
software
willbeable
tobeco
nstru
cted
by
students
atCCSU.All
impro
vements
willbeco
mplete
dby
nextM
ay
2013.
1of1
AmericanInstituteofAeronauticsandAstronautics
ExperimentalChara
cterization
ofIsolato
rShock
Tra
in
Pro
pagation
JonathanGeerts,KennethH.Yu
University
ofMaryland
Quasi-ste
adysh
ocktrainsin
arecta
ngularisolato
rofth
easp
ectratio3werecharacte
r-
ized
with
Mach
2.5
upstream
flow
and
underslowly
varying
backpressure
conditions.
A
time-h
isto
ry
schlieren
technique,accompanied
by
simultaneousstatic
and
dynamic
pres-
sure
measu
rements,wasperformed
tobetter
understand
the
transientasp
ectofsh
ock-
boundary
layerinte
raction
leading
toinletunstarts.
Both
spanwiseand
cente
rlinestatic
pressuremeasu
rements
wereutilized
tocharacte
rizeth
epropagation
ofsh
ocktrainsinside
theisolato
r,whileth
edynamic
pressuremeasu
rements
werefu
rth
eranalyzed
inan
e!ort
tofind
any
precurso
rofunstart.
Adata
base
showing
time-reso
lved
schlieren
imageswith
corresp
onding
axialpressure
profile
and
pressure
gradientprofile
wasconstructe
d.
The
preliminary
resu
ltsrevealed
acleardi!
erencebetw
een
visible
shock
train
length
and
the
exte
ntofth
epressuregradientin
theisolato
r.In
vestigation
on
thesh
ock
train
dynamics
revealed
ahighly
oscillato
ry
natu
reofth
epropagating
shock
trains.
Additionalrese
arch
isin
progress
tocharacte
rizeth
esh
ock
train
motion
and
thedynamic
behaviorwith
the
downstream
pressuredistu
rbancecharacte
ristics.
1of1
AmericanInstituteofAeronauticsandAstronautics
APROTOTYPE
MULTICOPTER
LOW
ALTITUDE
AUTONOM
OUS
NAVIGATION
DEVICE
SpencerHamblin
Northwood
APROTOTYPE
MULTIC
OPTER
LOW
ALTIT
UDE
AUTONOM
OUSNAVIG
ATIO
N
DEVIC
E
Theobjectiveofth
ispaperis
tosh
ow
thefeasibilityanduse
fulness
oflow
altitudemulti-
copte
rnavigation
usingacombination
ofcompute
rvision
and
operato
rcontrol.
Currently
thereis
noso
lution
available
thatwould
allow
amulticopte
rto
safely
navigate
below
tree
levelorunderobstacles.
This
multicopte
rwould
be
able
togetunderth
etree
line
and
tag
anim
als;additionally
this
devicecan
beuse
dforremote
access
ofdangerousareasto
collectsa
mples.
This
proto
typemulticopte
rdesignta
kesadvanta
geofamoto
rto
moto
rsizeof36inches.
Thelargersizeallowsforalargerpayload.Themulticopte
remploys6brush
less
moto
rsth
at
aresu
pplied
by
a5
amp
lith
ium
polymerbattery.A
flightcontrollerboard
handlesbasic
levelingand
coordination
ofth
emoto
rs.
Forte
stingand
emergency
controla2.4ghzradio
system
isutilizedwhichallowsforfast
switchingto
manualcontrol.
Videodata
isanalyzed
usingasm
all
compute
rrunningth
eOpen
Compute
rVision
library.An
avrATM
EL
chip
isuse
dto
handle
pulse
width
modulation.
Senso
rdata
forth
egyro,acceleromete
r,and
magneto
mete
rarehandled
via
I2C.Finally
videotransm
ission
tohomebase
isvia
an
800
milliwatt
900M
Hzvideotransm
ission
system.
The
multicopte
rdescrib
ed
above
isinexpensive
tobuild
and
can
go
into
hostile
envi-
ronments
tocollectsa
mplesand
taganim
als.
1of1
AmericanInstituteofAeronauticsandAstronautics
Warer-B
ased
TransferofNanomaterials
Thin
Films
Sepideh
Parvinian,HongliZhu,ZhiqiangFang,LiangbingHus
university
ofMaryland,CollegePark
Here
wepro
pose
asimple
and
cost
e!ectivemeth
od
oftransferring
nanomate
rialth
infilm
svia
wate
rassiste
dtransferprintingmeth
od
(WTP).
Asm
ooth
and
thin
film
ofhighly
conductiveSW
CNT
istransferred
tononco
nventionalsu
bstra
tes,
such
asglass
and
plastic
afterco
ating
on
wate
rtransferprinting
paperand
exposing
towate
r.Thewate
rtransfer
paper
ismade
offour
distinct
layers:
image
acc
epting
layer,
where
CNT
thin
film
isexpose
d,polymericbinderlayer,
wate
rslidinglayerand
pre
-coatinglayer.
Inth
ispro
cess,
wate
rpenetrate
sinto
theinte
rface
sofbinderand
slidinglayerand
thus,
thewate
rso
aked
binderca
nbeslid
o!,leavingath
infilm
on
theta
rgetsu
bstra
te.Theth
ickness
ofth
efilm
isdete
rmined
by
the
thickness
ofco
iled
wireson
the
Meyerro
ds.
This
transfermeth
od
yield
e"ciency
ofappro
xim
ate
ly100%
and
CNT
film
adhere
swell
toth
esu
bstra
te.
The
sheetre
sistance
and
transm
itta
nce
aftertransferand
wash
ingo!
thebinderare
1000
! sqand
betw
een
83to
88%
resp
ectively.
1of1
AmericanInstituteofAeronauticsandAstronautics
Developmentofasm
all
satelliteattitude
determ
ination
and
controlsimulation
testbed
Matthew
Disher
United
StatesNavalAcadem
y
Thepro
pose
dre
search
willco
nsist
ofdevelopingan
attitudedete
rmination
and
control
simulation(A
DCS)te
stbedin
ord
erto
impro
veperform
ance
andexpandth
escopeofsm
all
sate
llitemissions,
cubesa
ts(referringto
standard
ized
small
sate
llitedevelopmentarchitec-
ture
).This
willallow
forth
einte
gra
tion
ofmore
capabilitiesincluding
an
activeattitude
controlsy
stem
usingmomentu
mexch
angedevicessu
chasre
actionwheels.There
hasbeen
an
incr
easing
need
insu
pporting
theinte
gra
tion
and
testing
forth
ese
actively
controlled
cubesa
ts.Usingalarg
erADCSte
stbedmodelth
athasbeenwork
edonin
past
years
atth
eNavalAca
demy,
this
rese
arch
willbefocu
sed
on
developingan
attitudedete
rmination
and
controlsimulation
testbed
with
realistic
hard
ware
components
and
compute
rpre
cessors
thatca
nperform
close
d-loop
attitudedynamicsand
controlsimulation
inth
elabora
tory
environment.
Africtionless
air
bearing,which
hasbeen
rece
ntly
purchase
d,willbeinte
-gra
tedto
help
simulate
on-orb
itenvironment.
This
rese
archhopesto
create
anopera
tional
testbed
thatca
nbeuse
din
astro
nautica
lengineeringclassesatUSNA
inth
efu
ture
.
1of1
AmericanInstituteofAeronauticsandAstronautics
ABoltzm
ann
Sim
ulation
forM
ulti-grid
Inertial
Electro
staticConfinem
ent(IEC)
Andrew
Chap
University
ofMarylandCollegePark
Extra-solarexplora
tion
requiresa
powersy
stem
with
ahigh
energ
yto
fuelmass
ratio
thatca
nbe
scaled
down
e!ectively.
InertialElectro
staticConfinement(IEC)Fusion
has
thepote
ntialto
pro
videahigh
poweroutp
utwith
little
tonora
dioactiveby-p
roduct,but
todate
,no
IEC
reactor
has
demonstra
ted
apower
out
topower
inra
tio
gre
ate
rth
an
10-5.
ConventionalIE
Csemploy
two
conce
ntric
spherica
lsh
ell
grids.
The
inner
grid
ismainta
ined
ata
lowerpote
ntialth
an
the
oute
rgrid
tocr
eate
an
ion-confining
pote
ntial
well.Theionscy
clera
diallyback
and
forth
thro
ugh
theco
re,with
ach
ance
tofu
seateach
pass.Thusahigh
energ
yand
density
can
bemainta
ined
inth
eco
re,and
significa
ntfu
sion
can
occ
ur.
Howeverth
ere
are
anumberofenerg
ylossesinhere
ntin
two-grid
designsth
at
makenetpowergenera
tion
physica
llyim
possible.Theinnerca
thodegrid
hasadefocu
sing
e!ect
thatca
use
sionsto
stra
yonto
non-radialpath
s,quickly
resu
ltingin
collisionswithth
egrid.In
addition,dueto
themutu
alelectro
staticre
pulsion
oflike-charg
ed
ions,
ara
ndom
scattering,known
asth
erm
aliza
tion,occ
urs
thro
ughoutth
ech
amber,
which
alsore
sultsin
non-radialtrajectoriesand
aloss
offocu
sing
inth
eco
re.
The
addition
offocu
sing
grids
incr
ease
sion
confinementtimesovertraditionaltw
ogrid
configura
tions.
These
focu
sing
gridsare
positively
charg
ed
and
serv
eto
push
stra
yionsback
into
desire
dbeam
path
s.Io
nbunch
ing
isalso
obse
rved
toocc
urasth
ere
sult
ofth
epote
ntialwell
geometry
along
with
energ
yexch
angesbetw
een
particles.
Themono-energ
eticpack
ets
can
beopera
ted
ina
low
energ
yre
sonance
mode,co
nducive
toth
euse
ofaneutronic
p-B
11
fueland
direct
energ
yco
nversion.Ourcu
rrentre
searchinvolvesanumerica
lmodelofiontransp
ort
within
the
IEC
chamber.
The
ion
distribution
ismodeled
inposition-velocity
phase
space
with
aBoltzm
ann-P
oisso
nsy
stem
and
numerica
lly
appro
xim
ate
dwith
atime-splitting
scheme.
Inth
eone-d
imensionalmodel,
thetransp
ort
ofionsth
rough
phase
space
issp
litinto
two
linearadvection
equations.
Atw
o-d
imensionalmodelhasalso
been
developed.However,
ourinte
rest
atth
ispointliesin
thedevelopmentofafast
one-d
imensionalmodelth
atca
nbesimulate
dup
toth
eth
erm
aliza
tion
timescale
(1000sofpasses).Coulomb
collisionsare
modeled
with
the
Fokker-Planck
equation
inLandau
form
(FPL).
The
opera
tordi!
use
sth
edistribution
invelocity
space
inasitu
ation
where
low
angle
scatteringdominate
s.
1of1
AmericanInstituteofAeronauticsandAstronautics
RBSP
SPACECRAFT
COM
MISSIONING:
ATTITUDE
CONTROL
ACTIVITIES
MadelineKirk
JHU
Applied
PhysicsLab
The
Radiation
Belt
Sto
rmPro
bes(R
BSP)sp
ace
craft
are
apair
ofsa
tellitesdesigned
tostudy
the
Van
Allen
radiation
beltsaspart
ofNASAsLiving
With
aSta
rGeosp
ace
Pro
gra
m.
The
twin
space
craft
were
launch
ed
on
August
30,2012
into
highly
elliptica
lorb
itsth
atpass
thro
ugh
the
radiation
beltswhere
they
willre
main
thro
ughoutth
etw
oyearprimary
science
mission.A
suiteoffiveinstru
ments
on-b
oard
RBSP
willinvestigate
how
relativisticelectro
nsandionsin
thebeltsare
form
edandare
a!ectedbyso
laractivity
thro
ugh
measu
rement
ofparticle
energ
y,density,and
distribution,as
well
as
the
loca
lelectricand
magneticfields.
These
measu
rements
and
trendswillpro
videth
edata
needed
topro
duce
models
ofth
era
diation
beltsth
atwill,
amongoth
erth
ings,
allow
engineers
tobetterdesign
radiation
hard
ened
space
craft
and
fore
casters
topre
dictgeomagneticstorm
sth
atmay
pose
ath
reatto
space
craft
and
astro
nauts.
Thetw
inRBSP
space
craft
are
major-axis
spinners
with
noon-b
oard
attitudedete
rmi-
nation
orco
ntrol.
Theguidance
and
control(G
&C)hard
ware
on
thesp
ace
craft
includes
aSun
senso
rsy
stem,th
rusters
inamono-p
ropellantpro
pulsion
system,and
passivenuta
-tion
dampers.A
flux-gate
magneto
mete
r,included
inoneofth
escience
instru
mentsu
ites,
isuse
dasan
attitude
senso
rin
combination
with
the
Sun
senso
rsto
dete
rmine
attitude
histo
ryon
the
gro
und.
The
gro
und
base
dattitude
estim
ation
and
controlre
sulted
ina
busy
commissioningphase
forth
eG&C
flightte
am
whoplanned
and
execu
ted
maneuvers,
supported
instru
mentdeployment,
ran
daily
attitudeestim
ation
software
,and
monitore
dsp
ace
craft
attitudetrends.
Thefirstse
tofmaneuvers
perform
ed
inth
eco
mmissioning
phase
pro
vided
calibra
tion
data
on
thru
sterperform
ance
and
began
toco
nfigure
thesp
ace
craft
forscience
data
col-
lection.An
initialsp
in-u
pmaneuverbro
ughtth
esp
ace
craft
toitsnominal5.5
RPM
spin
rate
,delta-V
maneuvers
furtherse
para
ted
the
sate
llitesin
orb
it,and
asm
all
pre
cession
maneuveradju
stedth
esp
inaxis
pointingdirection.Thro
ughoutco
mmissioning,additional
spin-u
pand
pre
cession
maneuvers
were
execu
ted
toplace
thesp
ace
craft
inth
edesire
dat-
titu
deforinstru
mentdeployments.Themost
significa
ntim
pact
on
thesp
ace
craft
attitude
wasth
edeploymentoffour50mete
rsp
inplanebooms.
These
boomswere
deployed
over
aperiod
oftw
oweeksin
5-10
mete
rse
gments
thro
ugh
aca
refu
lly
planned
sequence
of
spin-u
pmaneuvers
and
boom
exte
nsionsin
ord
erto
mainta
inan
appro
priate
space
craft
spin
rate
.The
RBSP
space
craft
are
scheduled
tostart
the
primary
two
yearscience
mission
inlate
October2012.
1of1
AmericanInstituteofAeronauticsandAstronautics
Investigation
ofBuoyantTra
nsp
ort
Systemsth
at
Exploit
Martian
Wind
Pattern
s
JakeTynis
Old
DominionUniversity
This
rese
arch
hasdemonstrate
dhow
Martian
wind
patternscan
beexploited
utilizing
buoyancy-controlledballoontransp
ortsy
stemsth
atincorporate
auto
nomousnavigationca-
pabilities.
Polartransp
ortofth
eprim
ary
atm
osp
heric
constituent,
carbon
dioxide,hasa
significante!ecton
planeta
ry
weath
erpatterns.
This
globaltransp
ortproducesnominal
wind
speedsth
ataresu
"cientlyhigh
tofacilitate
planet-widetraverse
s.This
rese
arch
will
demonstrate
thatth
ese
aso
nalwind
variationsoccurin
apredicta
ble
mannerth
atcan
be
exploited.These
e!ects
havebeen
examined
usingnumericalsimulationsand
verified
sur-
facemeasu
rements,startingwith
theVikingLandersand
subse
quentlyfrom
currentrover
andorbitalsp
acecraft.This
rese
archhasutilizedth
eM
ars-GRAM
weath
ersimulationpro-
gram
toexplore
wind
conditionsovercandidate
surface
launch
locationsth
roughoutth
e
Martian
year.Thedata
collecte
dprovidesinsighton
desirable
base
locationsand
nominal
launch
opportu
nitiesforse
rialroboticballoon
missions.
Itis
possible
tota
rgetarangeof
launch
date
sin
orderto
reach
selecte
ddownwind
locations.
Foran
expedition
launching
inth
eNorth
ern
hemisphere,th
eprevailingwindsareEast
toW
est
forsignificantperiods
ofth
eM
artian
year.However,th
eNorth
ern
hemispheresu
mmerso
lsticesh
owsash
iftin
the
prevailing
winds,
nota
bly
the
flow
changesto
West
toEast
fora
shortperiod.
This
changein
flow
direction
isstrongly
driven
by
thesu
blimation
ofth
epolaricecaps.
This
flow
direction
shiftcoupled
with
shearlayerswithin
theatm
osp
hereprovidepossible
nav-
igation
techniques.
These
e!ects
and
oth
ersprovide
alogicalbasisfornavigation
using
atm
osp
heric
soundingte
chniquesand
buoyancecontrolto
e!ectnavigation
similarto
sail-
ing.Exploitingpredicta
ble
weath
ervariationscan
lead
toexploration
ofvast
areasofth
e
planetoraccess
tooth
erwiseinaccessible
locations.
1of1
AmericanInstituteofAeronauticsandAstronautics
Flightstabilization
with
flappingwingsin
gusty
environments
ChaoZhang,ZhengLingxiao,TysonHedrick,RajatMittal
TheJohnsHopkinsUniversity
Sta
bility
offlightwith
flapping
wings,
which
isth
enatu
ralinstinct
ofinse
ctflyers,is
oneofth
emajorch
allengesfordesigningM
icro
Air
Vehicles(M
AV).
Tobetterundersta
nd
how
inse
ctflyers
could
stabilizeitse
lfduringhovering,weuse
fully
coupled
computa
tional
model,
which
combinesth
eNavier-Strokesequationsand
theequationsofmotion
in6de-
gre
esoffreedom
(NS-6-D
OF)to
mim
icth
ehoveringmoth
flightboth
inca
lmenvironment
and
gusty
environments.Thro
ugh
analysisofco
mputa
tionalre
sultsand
compariso
nwith
experimenta
ldata
,a
simple
active
controlstra
tegy
isfound
for
stabilizing
the
moth
inpitch
,which
isalso
validate
din
fully
coupled
CFD
simulation.
More
over,
inth
epre
sent
study,
pro
jection
theory
isemployed
which
pro
jectseach
term
ofth
eNavier-Sto
kesequa-
tion
onto
avectorsp
ace
spanned
by
pro
perly
chose
nharm
onic
vectors
soth
atth
eforc
eexerted
on
theinse
ctbody
could
bequantita
tively
studied
inte
rmsofadded-m
ass
e!ect,
the
vectorsu
mofnorm
alsu
rface
induce
dby
free
vorticity
and
the
visco
ussk
infriction.
This
rese
arch
issu
pported
by
AFOSR.
1of1
AmericanInstituteofAeronauticsandAstronautics
E!ects
ofmean
and
fluctu
atingpressure
gra
dients
on
boundary
layertu
rbulence
PRANAV
JOSHI,XIA
OFENG
LIU
,JOSEPH
KATZ
TheJohnsHopkinsUniversity
Turb
ulentboundary
layers
are
subjected
tofavora
ble
pre
ssure
gra
dients
(FPG)in
avariety
ofengineeringapplica
tionslikeflow
thro
ugh
turb
omach
inebladepassagesand
over
wings.
Although
these
flows
have
been
studied
since
long,th
ere
levantflow
physics
isnotwell
understo
od.
Inth
epre
sentwork
,we
investigate
the
e!ect
ofa
mean
FPG
on
atu
rbulent
boundary
layer,
by
perform
ing
time
reso
lved
two-d
imensionalParticle
Im-
age
Velocimetry
(PIV
)measu
rements.
The
mean
FPG
isim
pose
dby
asink
flow.
The
time-reso
lved
measu
rements
enable
usto
calculate
the
stre
amwise
and
wall-n
orm
al(x
,y)
components
ofth
emate
rialacc
elera
tion
(Du/Dtand
Dv/Dt,
resp
ectively),
which
are
inte
-gra
tedsp
atiallyto
obta
inth
epre
ssure
distribution.Thus,
theim
pact
oflarg
escale
pre
ssure
gra
dientfluctuationson
the
stru
cture
oftu
rbulence
can
be
studied
non-intrusively.
The
mean
FPG
pre
vents
vorticalstru
cture
sfrom
rising
away
from
the
wall,decr
easing
the
Reynoldsstre
ssesin
oute
rre
gion.Larg
escale
pre
ssure
fluctuation
gra
dients
involveth
ree
dim
ensionalflow
stru
cture
s.In
both
,ze
ropre
ssure
gra
dient(Z
PG)and
FPG
boundary
layers,larg
escale
fluctuatingadversepre
ssure
gra
dients
(p/x¿0)are
pre
fere
ntially
associ-
ate
dwith
sweeps,
asfluid
appro
ach
ingth
ewall
isdece
lera
ting.Conse
quently,
theoutw
ard
transp
ort
ofsm
all-sca
letu
rbulence
issu
ppre
ssed,and
the
near-wall
enstro
phy
incr
ease
s.Conversely,ejections,
high
wall-n
orm
alenstro
phy
flux,and
visco
usvorticity
pro
duction
occ
ur
mostly
during
p/x¡0
asth
efluid
acc
elera
tesby
moving
away
from
the
wall.
The
near-wallenstro
phyfluxpeaksdueto
theinhere
ntnearwall3D
stru
cture
swhenp/x¡0
and
u¿0.Resu
ltsalsoindicate
thatth
ese
regionsoffluctuatingadverseand
favora
ble
pre
ssure
gra
dients
are
likely
tobeassociate
dwith
theoutb
oard
and
inboard
sides,
resp
ectively,of
very
larg
escale
inclined
rollerstru
cture
s,se
vera
lboundary
layerth
icknessesin
length
.Sponso
red
by
NSF.
1of1
AmericanInstituteofAeronauticsandAstronautics
Modelingofmagneto
-electric
and
mech
anical-electric
e!ects
inmagneto
strictive-p
iezoelectric
composites:
Application
toth
eenerg
yharv
estingpro
blems
Arm
anjHasan
yan,David
Piliposyan
Virginia
Tech
Wedevelop
theore
tica
lmodelforth
ere
sonance
enhance
mentofmagneto
electric(M
E)
ormech
anical-electricinte
ractionsatfrequenciesco
rresp
ondingto
bendingoscillationsfor
ferroelectric-ferromagneticorferroelectric-elastic
bi-layerco
mposite
s.A
dynamic
theory
of
bi-layerlaminate
dmagneto
-elasto-electricbars
wasco
nstru
cted.Theore
tica
lmodelwhich
included
bending
vibra
tion
e!ectswasdeveloped
forpre
dicting
theM
Ee!ectsorenerg
yharv
estingco
e"cientin
alaminate
barco
mposite
stru
cture
consistingofmagneto
strictive,
piezo
electriclayers.Theth
ickness
dependence
ofstre
ss,stra
in,and
magneticand
electric
fieldswithin
asa
mple
are
taken
into
acc
ountso
thatth
ebending
deform
ationsco
uld
be
considere
din
anappliedmagnetics,appliedmech
anicalloadorelectricfield.Thefrequency
dependence
ME
voltage
coe"cientand
electrica
lharv
esting
coe"cienthave
obta
ined
by
solving
electro
static,
magneto
static,
and
elastodynamic
equations.
Weco
nsiderboundary
conditionco
rresp
ondingto
thatis
freeto
vibra
teatboth
endsandmech
anicallysu
pported
attw
oarb
itra
rypoints.
Asa
demonstra
tion,ourth
eory
forbi-layerM
Eco
mposite
swas
then
applied
toferromagnetic-ferroelectricbilayers.Themodelis
applied
toasp
ecificca
seofM
etg
las-PZT
orPZT-E
lastic
bilayer.
Ath
eore
tica
lmodelis
pre
sente
dforstatic(low-
frequency
)M
Ee!ectsin
bilayers
asaparticularca
se.Dependingon
support
loca
tionsand
geometricaland
physica
lpara
mete
rs,wediscu
ssca
seswhen
energ
yharv
esting
coe"cient
ormagneto
-electricco
e"cientappro
ach
ingze
roorappro
ach
ingto
his
maxim
um
values.
1of1
AmericanInstituteofAeronauticsandAstronautics
OpenM
PScalabilityofan
OversetCFD
SolverUsing
Shared
Memory
Para
llelPro
gra
mming
Benjamin
Jim
enez
University
ofMarylandCollegePark
An
overse
t,compressible,Reynolds-Averaged
NavierSto
kesso
lverwasmodified
from
itsse
rialversionto
includesh
aredmemoryparallelprogrammingdirectiveswithOpenM
P.
Serialcodeprofilingwith
gprofidentified
themost
time-consu
mingsu
broutines.
OpenM
P
parallelconstructs
added
toth
ecode
prese
rved
the
serialversion
while
improving
the
performancecharacte
risticson
multi-corecompute
rarchitectu
res.
Asteady
and
unsteady
case
ofan
airfoil
with
inte
graltrailingedgeflap
and
leadingedgeslatin
awind
tunnelare
examined
forcomputa
tionale!ciency.Theprocess
ofincrementa
lly
addingparallelism
to
theexistingCFD
codewasverifiedfordouble
precisionresu
lts.
Characte
risticsofth
ese
rial
codeth
atareuniquely
di!
cult
toim
plementwith
OpenM
Paredescrib
ed
inaqualita
tive
analysis,
providingguidanceforCFD
engineerswhomay
exploreth
epossibility
ofadding
OpenM
Pto
their
existing
codes.
Scheduling
ofth
read
and
oth
erloop
optimization
tech-
niquesaredescrib
ed
usingFortran
examplesto
illustrate
best
practices.
Thescalabilityof
theparallelcodewasinvestigate
don
an
AM
DOpte
ron
6136,usingphysicallyand
logically
shared
memory
up
to8coresperprocessor.Futu
rework
willinvestigate
ahybrid
parallel
programmingapproachforth
e3D
versionofth
eso
lverusingM
PI+
OpenM
P,andexplore
theuse
ofoth
erarchitectu
resatgreate
rscales.
1of1
AmericanInstituteofAeronauticsandAstronautics
Combined
EnvironmentTestingto
ReducePayload
Mass,Cost
and
Mission
Risk
FrankArute,Jin
Kan
g,
DrexelUniversity
Inth
esp
aceindustryto
day,exhaustiveenvironmenta
lte
stingis
performed
on
payloads
priorto
flightto
ensu
reth
atth
epayload
can
withstand
theextremeenvironment,
which
it
willbesu
bjecte
dto
upon
launch.Someofth
ese
testsincluderandom
vibration,accelera-
tion,and
shock
testing.W
ith
currentvibration
test
devices,
itis
notpossible
tosimulate
environments
such
asrandom
vibration
and
sustained
ordynamic
g-loadssimultaneously.
These
testsalso
simulate
loadsfarbeyond
actu
allaunch
environmentand
overstress
the
payload
toensu
reth
epayload
can
survivelaunch
conditions.
Usingcurrentte
stmeth
ods,
thereis
also
adegreeofuncerta
inty
inth
ete
stresu
ltsdueto
thefactth
atth
ete
stsare
only
replicatingoneportionofth
elaunchenvironmentatatime.Forexample,if
apayload
wereto
havese
nsitivese
nso
rson
board
and
they
need
tobete
sted,th
edata
they
would
record
during
testing
would
notbeexactbecause
thete
stwould
belacking
thesu
stained
gfacto
rfelt
duringlaunch.Bydevelopingacapabilityto
inte
grate
acceleration,vibration,
and
shock
testing
using
astate
-of-th
e-artcentrifuge,it
ispossible
tote
stforsy
nergistic
e!ects
ofth
ese
combined
environments.Thete
stse
tup
thathasbeen
developed
tocreate
acombined
environmentconsistsofacentrifugewith
amodalexciterand
test
fixtu
rein-
stalled
on
itsgondola.This
test
setu
pwillbeable
toprovideboth
sustained,and
dynamic
g-loads,
aswell
assimultaneousvibration
loadsin
two
independentaxes.
With
combined
environmentte
sting,it
willbepossible
toprovidea
much
morerealistic
launch
environ-
ment.
By
providing
amorerealistic
test
environment,
combined
environmentte
sting
has
thepote
ntialto
reducecost
and
risk,sa
vetime,and
increase
performance.This
prese
nta
-
tion
willhighlightth
emodelingand
analysisperformed
on
ourte
stpayload,DragonSat-1,
tohelp
predictth
ee!ects
ofcombined
environments
and
theideallocationsfordata
ac-
quisition
devicesforreal-world
testing.It
willalso
highlightth
ete
stactivitieswhich
will
beperformed
on
Octo
ber26,2012with
somepreliminary
resu
lts.
1of1
AmericanInstituteofAeronauticsandAstronautics
Mission
Design
forSatellitesin
theProxim
ityofSmall
Bodies
Martin
Ozimek,Christopher
Scott
TheJohnsHopkinsUniversity
Applied
PhysicsLaboratory
When
asa
telliteis
within
thepro
xim
ity
ofa
small
body,
such
asa
moon,astero
id,or
comet,
itstrajectory
isoften
subject
toa
complica
ted
dynamicalenvironmentwhere
the
perturb
ationsfrom
non-spherica
lgra
vity,
solar
radiation
pre
ssure
,or
third-b
ody
e!ects
beco
me
significa
nt.
These
dynamics
pose
challenges
inexploring
the
trajectory
design
trade
space
when
asa
tellite
enco
unte
rssu
chbodies.
This
analysisdeta
ilsa
robust
and
systematic
appro
ach
forgenera
ting
science
orb
itsco
nnected
by
fueloptimaltransfers
inth
esm
all
body
regim
eforboth
impulsiveand
low-thru
stpro
pulsion
systems.
Forim
pulsivesy
stems,
theClohessey-W
iltshireequationspro
videan
analytica
lmeans
toglobally
inte
rpre
tth
edesign
space
allowingadesignerto
quickly
investigate
familiesof
science
orb
itsandobta
inclose
d-form
optimaltransfers.Solutionsare
refinedwithmultiple
shooting
and
nonlinearpro
gra
mming
totransition
the
resu
ltsinto
Hill’sequations,
and
finally,
ahigh-fi
delity
ephemerismodel.
Thefinalre
sult
isan
acc
ura
teso
lution
reta
ining
theinitialdesignch
ara
cteristicswithth
epote
ntialforfu
rtherfu
elsa
vingsth
atare
available
from
exploitingth
ehigh-fi
delity
perturb
ations.
Forlow-thru
stsy
stems,
the
solution
space
issu
bstantially
expanded
due
toth
epre
s-ence
ofa
time-vary
ing
thru
stmagnitude
and
direction
forth
esp
ace
craft,re
sulting
ina
challenging
optimalco
ntrolpro
blem
betw
een
two
obits.
Pse
udosp
ectra
loptimization
has
beendemonstra
tedto
yield
robust
converg
ence
tosu
chpro
blems,
however,
explicitlypro
p-
agate
dso
lutionsare
often
soughtas“truth
”forflightmissionsdueto
higheracc
ura
cyand
smooth
,im
plementa
ble
controlhisto
ries.
We
demonstra
teth
eim
portance
ofco
nnecting
pse
udosp
ectra
lto
indirect
low-thru
sttrajectory
optimization
within
this
regim
e,where
converg
ence
isnoto
riously
challenging,and
high
acc
ura
cyis
stillso
ught.
Fro
ma
coarse
initialguess,oneca
nre
adily
obta
ina
discr
etize
doptimaltrajectory
thatfacilita
tesra
pid
converg
ence
toth
eindirect
pro
blem
via
multiple
shooting.Pre
-defined
thru
st/co
ast
arc
sare
unnece
ssary
inth
isappro
ach
and
many-revolution
transfers
aboutsm
all
bodiesare
possible.
Applica
tion
ofth
ere
sultingalgorith
mson
test
pro
blemsre
vealth
atamission
designer
isable
tora
pidly
map
outcr
iticalperform
ance
metrics(e
.g.time-of-flightand
fuelusa
ge)
forth
eentire
designsp
ace
,th
uspre
ventingth
eneedto
rely
onsu
b-optimalpointso
lutions.
There
sult
isare
peata
ble,sy
stematicappro
ach
thatfacilita
testh
ese
lection
ofsm
all-b
ody
transfertrajectoriesforagiven
mission.
1of1
AmericanInstituteofAeronauticsandAstronautics
DART-C
ONCEPT
NAVIGATION
OVERVIEW
Justin
Atchison,Mark
Jensenius
JHUAPL
TheDouble
Astero
idRedirection
Test
(DART)is
apro
pose
dco
nce
ptto
impact
asm
all
body
ina
near-Earth
binary
astero
idsy
stem.
DART
isone
part
ofth
eAstero
idIm
pact
&Deflection
Assessment(A
IDA),
ajointpro
posa
lbetw
een
NASA
and
ESA.Theprimary
goalofth
emission
isto
measu
reand
chara
cterize
akineticim
pactors
ability
todeflect
an
astero
id.There
sultsofsu
chate
stwould
haveim
plica
tionsforplaneta
rydefense
,human
space
flight,
and
near-Earth
object
(NEO)science
and
reso
urc
eutiliza
tion.
Given
many
constra
ints,th
ebinary
system
Didymos
was
selected
as
ata
rget.
The
goalofth
emission
isto
impact
the
smaller,
seco
ndary
astero
idwithin
the
system.
The
NavigationTeam
hasth
ech
allengeofdevelopingaca
pabilityto
impact
the150m
diamete
rta
rgetwithaclosingvelocity
ofro
ughly
6km/s.
Thevehicle
hasavery
narrow
field-of-view
camera
asan
optica
lpayload,and
use
sch
emicalpro
pellantforattitudeco
ntroland
delta-v
maneuvers.
The
navigation
conce
pt-of-opera
tions
isto
divide
the
trajectory
into
thre
edistinct
modes:
coast,primary
-targ
eting,andte
rminalguidance
.Duringth
eco
ast-m
ode,th
evehi-
cleis
guided
usinggro
und-b
ase
dmeasu
rements
and
commands.
When
theastero
idsy
stem
isdete
ctable
usingth
eon-b
oard
camera
,navigation
transitionsto
primary
-targ
etingmode
and
use
soptica
lnavigation
forupdate
s.Finally,
afew
hours
priorto
impact,when
the
primary
and
seco
ndary
astero
idsca
nbe
reliably
di!
ere
ntiate
d,th
esy
stem
transitionsto
auto
nomouste
rminal-guidance
mode.This
modeemployshigh-rate
sensingand
on-b
oard
guidance
algorith
msto
org
anicallymaneuverto
targ
etth
eim
agece
ntroid
ofth
ese
condary
astero
id,withouthelp
from
thegro
und.This
appro
ach
isin
contrast
totraditionalmeth
-odsth
atuse
gro
und-b
ase
dso
ftware
toperform
few
care
fully-targ
ete
dmaneuvers.In
this
case
,th
ehighclosingvelocity,sm
allta
rget,
andro
und-triplighttimedonoto!ersu
"cient
pro
cessingtimeforhumans-in-the-loop.
When
inte
rminal-guidance
mode,th
evehicle
repeate
dly
compute
sestim
ate
softh
elinearize
dze
roe!ort
missdista
nce
and
ofth
ere
maining
divert
fuel.
Using
an
appro
ach
derived
from
pro
portionalnavigation,th
evehicle
perform
smaneuvers,asnece
ssary
,to
minim
izeth
efinaldista
nce
toth
eim
agece
ntroid
ofth
eastero
id.
This
pre
senta
tion
willgive
pre
liminary
simulate
dacc
ura
ciesand
fuel-use
fornominal
and
degra
ded
appro
ach
conditions.
1of1
AmericanInstituteofAeronauticsandAstronautics
TheM
ESA+
Pro
gra
m,EducationalOutreach
,and
TheAirplanePro
ject
Arm
andNok
bak
Nyembe,
Julien
A.Hou
nzangli,SyedMan
zerHasan
,
OzinoOdharo,
Claudio
Sidi,Dim
itriTito
MontgomeryCollege-Rockville
The
MESA
(Math
,Engineering,and
Science
Ach
ievement)
Pro
gra
mhasopera
ted
inM
ontg
omery
County
for
nearly
9years.
Montg
omery
College
wasth
efirstco
mmunity
collegein
Mary
landto
create
aM
ESA
chapte
r.In
2010,in
ane!ort
tore
ach
more
students,
Mary
land
MESA,M
ontg
omery
County
PublicSch
ools,and
Montg
omery
College
agre
ed
tosh
iftitsoutreach
e!ortsth
rough
themiddle
schoolscience
curriculum,which
wasbeing
rolled
outinto
all
middle
schools
inth
eco
unty.
We
called
this
new
pro
gra
m,M
ESA+.
TheM
ESA+
Pro
gra
mhasallowed
bro
ad
participation
formiddle
schooland
high
school
students,th
eir
teach
ers,and
Montg
omery
Collegestudents.-Ambassadors
org
anized
ITco
nfere
nce
forM
iddle
Sch
oolgirls.Delivere
dinstru
ctionson:
Dre
amweaver
ALIC
Eand
Scr
atch
pro
gra
mming
-W
ork
shops
were
held
for
middle
schoolstudents
over
the
2012
SummeratM
CDelivere
dinstru
ctionsand
held
competition
on:
Sea
Perch
Calculato
rRobot-M
ESA+
Ambassadors
are
also
helping
Montg
omery
County
publicschools
sta!
with:
Thetraditionalpre
-engineeringM
ESA
pro
gra
m(loca
ted
in2middle
schools
and
2high
schools)
Theco
ord
ination
ofwork
shops&
trainingsforoth
erM
ESA+
ambassadors,
Middle
schoolstudents,and
teach
ers.
Satu
rday
Sch
ooltu
toring
Middle
Sch
oolvisitsin
classro
om
THE
AIR
PLANE
PROJECT
(compose
dofth
reete
ams)
Theory
team
oExplainsth
ePhysics
conce
pts
behind
theflyingpro
cess
Sim
ulation
team
oTra
insmembers
on
how
tofly
an
RTF
plane,using
simulation
software
.Assembly
team
oBuildsth
eaircr
aft
and
gainsan
understa
ndingofth
epurp
ose
,ofeach
componentofth
eaircr
aft.
AIR
PLANE
COM
PETIT
ION
(Futu
rePhase
ofTheAirplanePro
ject)
Use
there
search
pro
vided
by
theairplanepro
ject
crew
todevelop
specifica
tions,
challenges,
and
guidelines
forM
ESA
high
schoolco
mpetitions.
1of1
AmericanInstituteofAeronauticsandAstronautics
NovelTech
nologyforBra
nd
Pro
tection
and
Anti-C
ounterfeitingM
easu
resusingFluoro
phore
and
DNA
Sanjula
Singhal
Ward
MelvilleHighSchool
Counte
rfeitingnotonly
damagesth
enameofapro
duct
and
theeco
nomy,
butca
nalso
compro
misequality
and
e!ca
cyofpro
ducts,
such
asth
eco
unte
rfeitingofmicro
chipsuse
din
aero
space
.W
ith
this
tech
nology,
DNA
and
fluoro
phore
were
bound
tosu
bstra
testo
pro
vide
bra
nd
pro
tection.
The
DNA
isa
unique
mark
er,
while
fluoro
phore
allowsra
pid
auth
entica
tion,as
itis
aco
mpound
that
fluore
sces
under
UV
light.
Fluoro
phore
was
added
toth
esu
bstra
tevia
two
linkers,a
short
linker(n
=2)and
along
linker(n
=9).
Alinkeris
aca
rbon
chain
with
asu
perre
activegro
up
thatbindsco
mpoundsto
geth
er.
The
reactionwaste
stedonafluoro
mete
r,whichsh
owedfluoro
phore
boundto
fabric,
leadingto
optimization
ofth
ere
action.DNA
wasth
en
added
toanoth
erlinker(e
pichloro
hydrin
or
epibro
mohydrin),
andru
nonagelelectro
phore
sis.
Thelinkerwasable
tobindto
theDNA,
dete
rminedbyth
edi"
ere
nce
inmolecu
larweightofDNA
withandwithoutth
elinker.
DNA
was
also
bound
tofluoro
phore
,with
both
an
alkaline
and
acidic
reagent,
and
analyze
don
agelelectro
phore
sis.
These
reactions
pro
vide
an
anti-counte
rfeiting
tech
nology,
as
fluoro
phore
and
DNA
are
able
tobind
tolegitim
ate
pro
ducts.
These
mark
ers
are
then
dete
cted
underUV
lightand
DNA
analysis,
forra
pid
and
definiteauth
entica
tion.
1of1
AmericanInstituteofAeronauticsandAstronautics
OptimizingCurrentCollection
inM
icro
bialFuelCells
Kushagra
Singhal
SUNY
StonyBrook
Currently,th
ereis
an
energy
crisis
inth
eworld,in
which
impoverished
nationsarenot
equipped
toprovidecheap
powerto
their
inhabitants.Their
health
isjeopardized
without
access
tobasicenergyrequiredto
heatfood,sa
nitizewate
r,orevenpowerelectricaldevices.
Providing
energy
toth
ese
nationsis
very
feasible
and
cost
e!cientif
weuse
microbial
fuelcells.
These
fuelcellsuse
self
sustainingbacte
ria
asth
ebioreacto
rs,
which
provideth
e
energyto
powersm
all
electricaldevices.
Thefu
eluse
dto
powerth
ese
bioreacto
rsis
found
inwastewate
r;in
addition
tobeing
acheap,readily
available
reso
urce
which
isusu
ally
dispose
dof,
itis
alsobeneficial,
sinceth
efu
elcellsasasidee"ectprocess
and
breakdown
thewastewate
r,reducingcostsrequired
intreatm
entfacilities.
The
microorganismsform
abiofilm
on
the
anode,where
they
transfer
the
electrical
charge,so
metimeswith
theaid
ofamediato
r.From
theanode,th
eelectronsflow
through
an
exte
rnalcircuit,th
en
back
toth
efu
elcell,into
the
cath
ode,where
the
electronsare
picked
up
by
oxygen.
Oxygen
hasa
high
reduction
capacity,and
the
excess
electronsat
thecath
odereadily
reduceto
wate
r.
Acurrentlimitation
forusingmicrobialfu
elcellsasan
energy
sourceis
thelow
power
outp
ut.
This
isameliorate
dby
ouroptimization
ofth
edesign
ofth
efu
elcell.
Forth
e
electrodes,
variousmate
rials
havebeenuse
din
variousconfigurations,
suchasstainless
steel
mesh
es,
graphite
anodes,
and
graphite
brush
es.
Were
designing
microbialfu
elcellswith
electrodes
that
incorporate
nanomate
rials.
These
nanomate
rials
increase
power
outp
ut
tenfold,dueto
very
high
electricalconductivity
ofth
ese
nanoparticles,
and
their
inherent
surfaceroughness
and
largesu
rfacearea,which
ispreferred
foradhesion
with
bacte
ria.
Currently,werete
stingvariousstructu
resofcarbon:fu
llerenes,
nanoribbons,
and
nanoplate
lets.Additionallydrop
casting,vacuum-fi
ltration,and
spraycoatingofnanopar-
ticles,
all
di"
erentmeth
odsofpreparingth
eelectrodes,
isbeinganalyzed.
This
rese
arch
isan
asset
for
aeronautics
and
astronautics
for
futu
re
extrate
rrestrial
colonization
missions.
Conventionalenergy
sourcessu
ch
assu
nlight,
natu
ralgase
s,and
nuclearenergy
mightnotsu
!ce.
Itis
expensive
totransp
ortfu
els,and
building
energy
plants
would
takemany
yearsto
establish
.Asa
supplementa
ry
energy
source,microbial
fuelcells
would
lift
some
burden
for
futu
re
energy
needs,
while
providing
waste-w
ate
r
treatm
ent.
1of1
AmericanInstituteofAeronauticsandAstronautics
E!ects
ofM
odelScalingon
Sedim
entTra
nsp
ort
in
Brownout
MarkGlucksm
an-G
laser,Anya
Jon
es
University
ofMaryland
Bro
wnoutis
ahighly
coupled
aero
dynamicsand
sedim
enttransp
ort
phenomenon
that
occ
urs
when
aro
torc
raft
opera
tesovera
bed
ofloose
sedim
ent.
The
purp
ose
ofth
isre
-se
arch
isto
investigate
the
e!ects
ofscaling
on
roto
rcra
ftbro
wnout.
Currentre
search
hasfocu
sed
on
labora
tory
-sca
leexperiments
which
can
be
perform
ed
more
readily
than
full-sca
lete
sting.Thee!ectsofscalingfrom
thelabora
tory
-sca
leto
full-sca
leare
notfu
lly
understo
od.
Alabora
tory
-sca
lero
torte
sted
inwate
rin
hoverovera
sedim
entbed
was
compare
dto
similarstudiesperform
ed
inair.Testingin
wate
rallowed
forth
eexplora
tion
ofch
ara
cteristicsnotach
ievable
inair.Sim
ilarity
para
mete
rssu
chasth
eflow
velocity
tose
dim
entte
rminalvelocity
ratiowere
moved
close
rto
full-sca
lere
sultsasco
mpare
dto
lab-
ora
tory
testsin
air.Oth
erpara
mete
rssu
chasdensity
ratiowere
reduce
dasco
mpare
dto
full-and
labora
tory
-sca
lete
sting
inair.Tim
e-reso
lved
and
phase
-reso
lved
particle
image
velocimetry
(PIV
)meth
odswere
use
dto
measu
reth
evelocity
field
underth
ero
torand
chara
cterize
pattern
sofse
dim
entuplift
and
dispersion.Velocity
field
measu
rements
show
thatinstanta
neousvelocitiesca
nbemany
timesgre
ate
rth
an
time-orphase
-avera
ged
ve-
locities.
Instanta
neousvelocity
excu
rsions150%
larg
erth
anphase
-avera
gedvelocitieswere
regularly
obse
rved,and
even
more
extremedi!
ere
nce
swere
note
dbetw
een
instanta
neous
and
time-avera
ged
resu
lts.
Dual-phase
flow
visualiza
tion
showed
sedim
entuplift
focu
sed
aro
und
the
upstre
am
edge
ofpassing
vortices.
Itwasth
eorize
dth
atsh
earstre
ssesand
high
velocities,
both
tangentialand
para
llelto
the
sedim
entbed
played
importantro
les
inse
dim
entmobilization.There
fore
,similarity
para
mete
rsth
atacc
ountforth
eloca
lun-
steadych
ara
cteristic
velocities(o
pera
tionalpara
mete
rs)are
more
likely
topro
videacc
ura
tescalingth
anth
ose
thatdonot(g
eometric
para
mete
rs).
ABuck
ingham-P
ianalysiswasper-
form
ed
on
somepara
mete
rsexpected
tobeim
portantto
bro
wnout,
e.g.particle
and
fluid
density,sw
irlvelocity,vortex
stre
ngth
,se
dim
entte
rminalvelocity,and
sedim
entparticle
size
.New
scalingpara
mete
rs,su
chasmaxim
um
swirlvelocity
toparticle
term
inalvelocity
ratio
and
vortex
stre
ngth
toparticle
term
inalvelocity
and
particle
size
ratio
were
found
using
the
Buck
ingham-P
imeth
od.
Dual-phase
flow
visualiza
tion
allowed
forpre
liminary
measu
rementofbro
wnoutse
verity
asafu
nction
ofth
enew
similarity
para
mete
rs.Futu
rete
stsatinte
rmediate
valuesofth
enew
similarity
para
mete
rsmayaid
inth
edevelopmentof
apre
dictivebro
wnoutse
verity
modelca
pable
ofbridgingth
ere
sultsfrom
labora
tory
-sca
leto
full-sca
leflightenvironments.
1of1
AmericanInstituteofAeronauticsandAstronautics
LLCD
ExperimentalJitterTestingand
Model
Validation
BrandonDilworth
MIT
Lincoln
Laboratory
TheLunarLase
rCommunicationDemonstra
tion(L
LCD)pro
gra
matM
ITLinco
lnLabo-
rato
ryis
thefirstsp
ace
lase
rco
mmunicationsy
stem
forNASA.Theoptica
lco
mmunications
term
inalwillbeca
rried
into
lunarorb
itby
theLunarAtm
osp
here
and
Dust
Environment
Explore
r(L
ADEE)sp
ace
craft
which
isscheduled
tolaunch
in2013.Theprimary
goalof
theLLCD
pro
gra
mis
todemonstra
teoptica
lco
mmunicationfrom
lunarorb
itto
theEarths
surface
.Optica
lco
mmunication
systemshavemany
advanta
gesoverra
dio
frequency
(RF)sy
s-te
mswhichincludeach
ievinghigherdata
rate
susinglowersize
,weightandpower(S
WaP).
Optica
lco
mmunication
systemsre
lyon
much
narrowerbeamsth
an
RF
systemsto
ach
ieve
these
advanta
ges;
thepenality
isth
atth
eoptica
lbeam
must
havegood
stability
inord
er
tomainta
inth
eco
mmunication
link
betw
een
the
transm
istterand
rece
iver.
There
are
anumberoffactors
thatplay
aro
lein
the
stability
ofth
eoptica
lbeam,butth
efocu
sof
this
talk
ison
the
residualline-of-sight(L
OS)jitterre
sulting
from
unre
jected
space
craft
excita
tion.
During
early
pro
gra
mdevelopmentmath
ematica
lanalyse
s,starting
from
simple
hand
calculationsandevolvingth
roughco
mplexco
mputa
tionalte
chniques,
are
use
dto
driveth
edesign.
Aswith
any
type
ofanalytica
lanalyse
s,many
assumptionsare
use
dto
identify
di!
ere
ntch
ara
cteristicsofth
esy
stem.
Aspro
gra
msdevelop,th
ese
math
ematica
lmodels
are
use
dto
driveth
edesignso
there
isastro
ngdesire
tovalidate
these
models
asth
edesign
continuesto
matu
re.
Experimenta
tion
with
physica
lhard
ware
isa
common
meth
od
for
validatingmath
ematica
lmodels,includingre
sidualLOSjittermodels.TheLLCD
pro
gra
mdeveloped
ate
stbench
inord
erto
validate
there
sidualLOS
jittermodelwhich
pro
vides
higherco
nfidence
inth
eco
mputa
tionalre
sults.
This
pre
senta
tion
willpro
videan
overv
iew
ofth
eLLCD
pro
gra
m,su
mmarize
someof
the
components
ofth
eOptica
lM
odule
and
todescribe
the
e!ortsbehind
validating
the
residualLOS
jittermodelusingexperimenta
lte
chniques.
This
work
issp
onso
red
by
the
NationalAero
nautics
and
Space
Administration
under
Air
Forc
eContract
#FA8721-05-C
-0002.Opinions,
inte
rpre
tations,
conclusionsandre
com-
mendationsare
those
ofth
eauth
orand
are
notnece
ssarily
endorsed
by
theUnited
Sta
tes
Govern
ment.
1of1
AmericanInstituteofAeronauticsandAstronautics
Design
and
ControlofaCycloidal-Roto
rAircra
ft
ElenaShrestha,Moble
Benedict,Vikram
Hrishikeshavan,InderjitChopra
University
ofMaryland,CollegePark
This
rese
archdescribesth
edesignandco
ntrolofahover-ca
pable
cycloidal-ro
toraircr
aft
(Cycloco
pte
r)atM
icro
Air
Vehicle
(MAV)scale.
Cycloidalro
toris
are
volutionary
con-
ceptand
hasbeen
pro
ven
tobemore
e!cientth
an
conventionalro
tors.
Fro
ma
controls
perspective,oneadvanta
geofaCycloco
pte
ris
thatth
eth
rust
vectorofeach
cycloidalro
tor
can
beinstanta
neously
changed,th
ere
by
impro
vingth
emaneuvera
bility
ofth
eM
AV.The
hybrid
Cycloco
pte
rutilize
stw
ocy
cloidalro
tors
and
aco
nventionalro
torforth
eta
il.An
e"ective
controlstra
tegy
wasdeveloped
tosu
ccessfu
lly
demonstra
tepitch
,ro
ll,and
yaw
capabilitiesofth
eCycloco
pte
r.In
addition
toopen
loop
control,
close
dloop
controlwas
also
enabled
by
an
onboard
pro
cessorunit
equipped
with
tri-axialgyro
s,acc
elero
mete
r,micro
pro
cessor,
andwireless
communicationco
mponents.Alongwithapilot,
thefeedback
controlsy
stem
wasable
toco
ntrolth
evehicle
forastable
hover.
1of1
AmericanInstituteofAeronauticsandAstronautics
ChemiluminescenceSenso
rDevelopmentforReal-Tim
e
MonitoringofGasTurb
ineCombustorDynamics
JasonBurr
University
ofMarylandatCollegePark
Chemiluminescence
Senso
rDevelopment
for
Real-Tim
eM
onitoring
of
Gas
Turb
ine
CombustorDynamicsJaso
nBurr,Underg
raduate
Rese
archeratth
eUniversity
ofM
ary
-land Chemiluminescence
isate
chniquewidely
use
din
theco
mbustionco
mmunityto
measu
reequivalence
ratios
and
heat
release
rate
swithin
aco
mbustion
reaction.
Typically
this
involvesth
euse
ofphoto
sensitivedevicesto
measu
reth
ephoto
nic
emission
from
excite
dfree
radicals
inth
eco
mbustion
field.
These
radicals
include
CH*
and
OH*.
Pre
vious
experimenta
tion
hassh
own
CH*
and
OH*
can
bere
late
dto
the
equivalence
ratio
ofth
ere
action,whileth
elatteris
considere
dastro
ngindicato
rofheatre
lease
rate
.Common
meth
odsforgath
ering
data
relate
dto
these
emissionsinvolveeitherth
euse
ofphoto
multipliers
(PM
Ts)
oran
inte
nsified
charg
e-coupled
device(ICCD)ca
mera
.Both
isolate
thewavelength
sofCH*
and
OH*
(430
nm
and
308
nm,re
spectively)th
rough
the
use
ofopticfilters
foranalysis.
Whileth
ePM
Tis
use
dforastro
ngte
mpora
lre
solution
of
these
changesin
an
isolate
dre
gion
ofth
eflow,th
eIC
CD
camera
isco
mmonly
employed
foritssp
atialre
solution.
Inmany
configura
tionsboth
are
employed
tobenefitfrom
its
counte
rpartsweaknesses.
Regre
ttably,both
are
also
typically
only
capable
ofmeasu
ring
thetw
owavelength
sindependently.
Toso
lveth
ispro
blem,te
stsare
oftenre
-rununderth
esa
meco
nditionsto
perform
themeasu
rements
again
with
adi!
ere
ntfilter.
There
searchdiscu
ssedin
this
pre
senta
tionfocu
sesonanaltern
ativeappro
ach
:re
solving
the
tempora
lre
solution
for
both
wavelength
susing
asingle
senso
r,th
us
allowing
both
equivalence
ratioandheatre
lease
rate
measu
rements
toocc
urco
ncu
rrently.
Opticoutp
uts
from
thete
stse
ction
are
analyze
dbyadual-PM
Tsy
stem
thatinco
rpora
testh
ero
bustness
ofth
ePM
Tte
mpora
lre
solutionwithauniquese
nso
rth
atallowsfrom
somevary
ingsp
atial
reso
lution.These
designim
plementa
tionswillallow
forsimplifica
tionin
theappara
tuss
use
and
pote
ntially
furtheradvance
ments
inth
eco
mbustion
field.
Ifsu
ccessfu
l,su
chse
nso
rdevelopmentca
nlead
toa
new
opportunity
for
revolutionizing
gas-tu
rbine
combustion-
controlte
chnology
by
making
iteasier
toapply
aclose
d-loop
active
controlfor
in-situ
engineperform
ance
optimization.
Ongoingre
searchincludesth
ephysica
lmach
iningandmanufacture
ofth
ecu
rrentdesign.
Once
assembled,ca
libra
tionsto
these
nso
rwillbeach
ieved
via
amodelco
mbustor.
The
resu
ltswillhopefu
llyim
pro
veth
eabilityto
acc
ura
tely
map
theequivalence
ratioand
heat
release
rate
during
combustion
with
the
use
ofco
mbining
customized
signal-pro
cessing
opto
electro
nicswith
o!
thesh
elf
optics
and
opto
mech
anicalparts.
1of1
AmericanInstituteofAeronauticsandAstronautics
Developmentand
chara
cterization
ofatu
bular
Dielectric
ElectroActivePolymeractu
ato
rwith
a
pre-strain
mech
anism
OscarAlvarado,AlisonFlatau
University
ofMarylandCollegePark
This
rese
arch
explore
sth
edevelopmentand
chara
cteriza
tion
ofamultilayere
dtu
bular
actuato
rmadeofadielectricelastomerwithco
mpliantelectro
des.
Electro
ActivePolymers
(EAPs)
are
very
attra
ctivein
theactuato
rco
mmunity
dueto
their
muscle
likeopera
tion,
light
weight,
low
electrica
lpower
consu
mption
and
no
noise.
Dielectric
Electro
Active
Polymers
(DEAPs)
belongto
thefamily
ofEAP
inwhich
theactuation
isca
use
dby
elec-
trostatic
forc
esbetw
een
two
electro
deswhich
squeeze
the
polymerin
planardirections.
ForourDEAP
actuato
rdesigns,
an
exte
rnalmech
anism
toapply
constantuniaxialpre
-stra
inis
use
dto
incr
ease
thesu
rface
are
aofmate
rialwhilere
ducing
itsth
ickness.Base
don
Maxwellselectro
staticstre
ssequation,a
smallerth
ickness
allowsfora
larg
erelectro
-static
pre
ssure
forth
esa
me
voltage
levelapplied,hence
highermate
rialelongation.
Inth
isstudy,
the
actuato
rsare
base
don
Danfoss
PolypowerA/S
Dielectric
Electro
Active
polymer(D
EAP)mate
rial.
This
DEAP
mate
rialutilize
sasilico
ne-b
ase
delastomer,
Elas-
tocilRT
625,co
mbined
with
smart
compliantmeta
lize
delectro
de
tech
nology
inwhich
asp
ecialco
rrugate
dsu
rface
isim
printe
din
the
elastomerto
allow
elongation
inonly
the
compliantdirection.Themaxim
um
stra
inin
themate
rialis
limited
to30%.Theco
nstru
c-tion
pro
cess
ofth
ese
manually-rolled
actuato
rsis
pre
sente
d,aswell
asadiscu
ssion
ofth
edi!
ere
ntpre
-strain
mech
anismsco
nsidere
d.Strain
and
forc
edata
issh
own
foractivation
voltagesra
nging
from
0to
2500
Voltsin
which
asp
ring
base
dpre
-strain
mech
anism
isuse
d.Thre
esp
ringsofdi!
ere
ntsti!
ness
are
considere
dand
thre
epre
-strain
levels
foreach
spring
studied.
Actuato
rtransientre
sponse
toelectrica
lstim
ulusis
pre
sente
daswell
asimple
dynamic
modelth
atpre
dicts
theactuato
rsfirstmodeofvibra
tion.
1of1
AmericanInstituteofAeronauticsandAstronautics
TheCratersville
StudentContest
Gregory
Sharp,JoeCacaccio
WPI
TheCra
tersville
Stu
dentConte
st:Design
aSim
ulate
dLunarBase
Science
Exhibit
By
Jose
ph
Caca
ccio
and
Gre
gory
Sharp
Imagineth
atyou
are
a5th
gra
der,
ten
years
old,and
there
isasp
ecialSpace
Enrich
ed
Science
Educa
tion
curriculum
experimentgoing
on
inyourschool.
Thus,
inyourscience
class
whenyouare
dealingwithse
ctionsonmatter,
motion,forc
es,
lightandso
und,energ
yand
electricity
there
isan
activitydealingwith
oneofth
ech
allengesoflivingand
work
ing
on
themoon.Someofth
ese
challengesincludese
para
tingth
emeta
lsmixed
inth
ere
golith
togetbuilding
mate
rials,figuring
outhow
tominewate
rand
transp
ort
there
sulting
ice
from
the
bottom
ofa
crate
r,and
how
touse
the
reso
urc
esathand
towire
the
base
for
electricity.Sim
ple
solutionsto
these
pro
blemsare
possible
once
onehasmastere
din
the
basicco
nce
pts
inth
e5th
gra
descience
curriculum.
Then
asa
6th
gra
derth
ere
isa
unit
thatre
turn
sto
this
themeto
examineth
ebiologicalissu
es,
focu
sing
on
gre
enhouse
food,
fibers,th
ebiosp
here
and
wate
rre
pro
cessing.These
topicswillexaminehow
life
on
earth
can
bere
plica
ted
on
amuch
smallerscale
toallow
fora
self-su!cientbase
on
theM
oon.
Thestudents
willlearn
how
theM
oon
base
willhaveto
modify
tolivingco
nditionsofth
eplants
toallow
foracc
elera
ted
gro
wth
and
higheryield.A
spiralcu
rriculum
with
alunar
base
themewould
flow
from
5th
gra
deall
theway
up
toth
e9th
gra
de.Thech
allengeof
this
conte
stis
tohaveco
llegestudents
inaero
space
,architecture
,andoth
erfields,
team
up
toenvision,visualize
and
dra
wup
imagesofwhatth
isperfect
field
trip
capstoneexhibit
should
look
likeyearby
yearTheco
nte
stuse
sth
efloorplan
ofth
eW
orc
esterAuditorium
asth
esp
ace
forth
epro
pose
dexhibit.
TheW
orc
esterAuditorium,a
warmemorialbuilt
inth
e1930s,
wasch
ose
nbeca
use
ofitsvast
base
ment.
Itis
underg
round,hasmany
tight
twisting
hallways,
and
thecu
rrentbuilding
isunuse
d.W
orc
esteris
an
esp
ecially
suitable
site
dueto
thefact
thatRobert
Goddard
,th
efounderofmodern
rock
etry
inaloca
lhero
Inth
ispre
senta
tion
wewillexplain
where
theco
nte
stca
mefrom,stre
ssing
itsorigins
ina2010architectura
llunarbase
design
conte
stru
nby
Shiftb
oston.Cra
tersville
wasone
of102
entries.
Ittied
forfirston
tech
nicalfeasibility
and
elegance
,co
uld
feed
itse
lfand
pay
foritse
lf.W
ewillth
en
show
imagesofth
eAuditorium
and
go
into
ahisto
ryofwhy
Worc
estermightcr
eate
such
an
exhibit
hers,th
ough
thesp
onso
rsofth
eco
nte
stare
not
committe
dto
havingth
elunarbase
exhibit
there
.Thebase
gre
enhouse
would
pro
bably
be
atth
enearb
yTowerHillBota
nicalGard
en.In
summation,ourgoalis
topre
pare
theway
forpapers
tofollow
onwhatth
esimulate
dlunarbase
should
looklikegivenitseduca
tional
goals.If
this
curriculum/exhibit
pre
cedentdisse
minate
sit
could
beavery
big
dealforth
eaero
space
work
forc
epip
eline.
1of1
AmericanInstituteofAeronauticsandAstronautics
ASTEROID
IMPACT
AND
DEFLECTIO
NASSESSM
ENT
(AID
A)M
ISSIO
NCONCEPT
ZacharyFletcher,Andrew
Cheng
JHU/A
PL
TheEarth
isco
ntinually
bombard
ed
by
astero
ids,
themajority
ofwhich
are
very
small
and
bre
ak
up
harm
lessly
inth
eatm
osp
here
.However,
there
isalso
arisk
oflarg
escale
damagefrom
astero
idim
pacts.
Impactssu
chasth
ose
inTungusk
ain
1908,whichflattened
nearly
2000sq
uare
km
offore
stin
Russia,occ
urevery
few
hundre
dyears.
Inan
ord
erto
mitigate
theth
reatoffu
ture
impactsto
Earth,NASA
hasta
ken
resp
on-
sibility
for
conducting
asu
rvey
ofall
Near
Earth
Astero
ids(N
EA),
and
assessing
their
likelihood
toim
pact
earth.W
hileth
emajority
ofth
epopulation
oflarg
erastero
idsis
be-
lievedto
havebeendisco
vere
d,th
ere
remain
manyastero
idsth
athaveyetto
bedisco
vere
dth
atare
ofsimilarsize
toth
atofth
eTungusk
aim
pact.
Inaddition
tofinding
pote
ntially
haza
rdousastero
ids,
there
needsto
bea
meth
od
for
deflection
them
should
ahaza
rdous
object
be
found.
There
have
been
severa
loptions
discu
ssed
forhow
this
deflection
could
beacc
omplish
ed,ra
nging
from
akineticim
pact
toagra
vity
tractor.
This
pre
senta
tion
focu
seson
the
Astero
idIm
pact
and
Deflection
Assessment(A
IDA)
mission
conce
pt
that
combines
aJHU/APL
developed
conce
pt
ofth
eDouble
Astero
idRedirectionTest
(DART)sp
ace
craft
withanESA
developedco
nce
ptofth
eAstero
idIm
pact
Mission
(AIM
).TheDART
space
craft
isa
simple,low-cost
space
craft
designed
toim
pact
theastero
id65803Didymos.
Itse
rvesasate
chnology
demonstra
tion
ofakineticim
pactor,
whose
pri-
mary
goalis
todete
rmineth
ee!ectiveness
ofakineticim
pactorfordeflection
an
astero
id.
Itwillalsopro
videim
agesand
basicch
ara
cteriza
tion
ofth
eDidymosastero
idsy
stem.
TheAIM
space
craft
isalow-cost
space
craft
whichwillch
ara
cterize
andobse
rveDidymos
prior,
during
and
post
impact
with
DART.It
isan
ESA
design
base
don
the
SM
ART-1
space
craft
bus,
hosting
severa
lscience
payloads.
Itwillpro
videinsightinto
theDidymos
binary
astero
idsy
stem
andpro
videanincr
ease
dscience
retu
rnifable
toobse
rveth
eim
pact
forDART.
1of1
AmericanInstituteofAeronauticsandAstronautics
Pro
jectile
Aero
dynamics
AlistairAndrulis
WashingtonLatinPublic
Charter
School
Pro
jectileAero
dynamicsby
Alistair
Andru
lis,
Febru
ary
16,2012
Question:
Which
of3
nose
cone
shapeson
aro
cketwillhave
the
least
dra
gand
go
thefu
rthest/highest?
#1
Bullet(h
alf
sphere
w/flatbottom)#2
Sphere
;#3
TearShape
Hypoth
esis:
#3
willgo
the
furthest
and
the
highest
ofth
eth
ree
rock
ets
beca
use
itwill
bre
ak
thro
ugh
the
air
and
the
tapere
dsh
ape
willre
duce
the
dra
gbehind.
Purp
ose
:To
calculate
the
di!
ere
nce
indra
gth
atocc
urs
by
manipulation
ofonly
apro
jectilessh
ape,
keepingoth
ervariablesco
nstant.
Pro
cedure
:
1.Assemble
thero
ckets
withdi!
ere
ntsh
apednose
cones.
Conduct
2ru
nseach
ofvertical
and
45degre
eangle
testsforeach
shape.
2.Use
aca
mera
tore
cord
thero
cket’stimeforth
everticalte
st.Aftereach
rock
ethas
been
launch
ed
twice,re
cord
thedata
and
avera
geit.
3.Repeatth
ete
stru
nslaunch
ingth
ero
ckets
ata45degre
esangle.M
easu
reth
edista
nce
each
rock
ettraveled
with
string,re
cord
itfor2launch
eseach
,th
en
avera
geit.
Resu
lts/
Conclusion:
My
testing
pro
ved
my
hypoth
esis:
that
Rock
et
#3
with
its
tear-
shapednose
conewillth
egre
ate
stflightdura
tionanddista
nce
ofth
eth
reero
ckets,beca
use
itwillbre
ak
thro
ugh
theair
and
theta
pere
dsh
apewillre
duce
thedra
gbehind
thehalf-
sphere
front.
Bydoingth
ete
stsIam
able
tostate
thatth
isro
cketcr
eate
dth
eleast
amount
ofdra
gdueto
itssh
aped
conedesign.
This
rock
etoutp
erform
ed
all
ofth
eoth
erro
ckets
by
agood
marg
in.
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AmericanInstituteofAeronauticsandAstronautics
SolarEnerg
yforaBrighterFutu
re!
SonyaDatta
River
HillHighSchool
This
studydete
rminedth
ee!ectofte
mperatu
reonth
eoutp
utofaso
larpanelbyheating
andcoolingth
eso
larpanelto
acerta
inte
mperatu
reandth
enmeasu
ringth
ecurrentwitha
multi-mete
r.Thehypoth
esiswas:
ifth
eso
larpanelis
cooled,th
enth
eoutp
utwillincrease
because
theconductivityin
themeta
lwould
increase
andincrease
abso
rption.Thepurpose
ofth
isprojectwasto
do
indepth
rese
arch
on
alternativesth
at,
ifputon
alarge
scale,
could
supply
energyforAmerica.Because
solarenergyis
dependentonth
esu
n,aninfinite
reso
urce,so
larenergywould
belargely
beneficialif
use
din
theUnitedSta
tes.
Peakoiland
largeenergydependencecould
beupcomingproblemsth
atprese
ntth
emse
lvesto
America,
leaving
large
gaps
inall
manufactu
ring
industries
and
everyday
life
energy
use
s.This
experim
entexpandson
ongoing
rese
arch
aboutth
emost
e"cientway
touse
solarpanels
and
increase
theenergy
they
giveo!
soth
ey
arereliable.
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AmericanInstituteofAeronauticsandAstronautics
UsingDielectric
ElectroActivePolymerSenso
rsto
DetectPressure
ChangeoveraSmooth
Surface
YitAkyuz
University
ofMaryland,CollegePark
Back
gro
und:
Dielectric
Electro
Active
Polymer(D
EAP)film
isan
experimenta
lfilm
pro
duce
dby
Danfoss
Polypower.
DEAPsare
fundamenta
lly
capacito
rsth
atch
angeth
eir
capacita
nce
whenavoltageis
appliedasth
epolymeris
compre
ssedin
thickness
andexpands
inare
adueto
theelectricfield.W
hen
mech
anicallystra
ined,th
ech
angein
capacita
nce
of
the
elementis
pro
portionalto
the
stra
inand
load.
The
basicdesign
ofa
senso
rco
nsists
ofa
section
ofPolyPowerDEAP
mate
rialwith
electrica
lco
nnections.Rese
arch:Thegoal
ofourre
search
hasbeen
touse
theDEAP
film
asapre
ssure
senso
roverasm
ooth
surface
(i.e.
an
airplane
wing).
Afterpre
paring
the
senso
rs,th
ey
are
taken
toth
ewind
tunnel
forte
sting.These
nso
ris
connected
thro
ugh
an
electriccirc
uit
toaLabview
pro
gra
mth
at
can
logth
eavera
geca
pacita
nce
atany
given
time.Thewind
tunnelis
alsoco
nnected
toa
manomete
rth
atca
ndete
ctpre
ssure
changeinsideth
etu
nnel.
Asth
evelocity
inth
ewind
tunnelincr
ease
s,th
epre
ssure
insideth
etu
nneldecr
ease
s,and
theca
pacita
nce
ofourfilm
incr
ease
s.Conclusion:Id
eally,
wewould
wanta
linearre
lationsh
ipbetw
een
thepre
ssure
changeand
theca
pacita
nce
ofth
efilm
.Although
ourcu
rrenttrials
haveyielded
positive
resu
lts,
there
are
someissu
eswith
repeata
bility.
All
ofth
etrials
havesimilartrendsbut
slightlydi!
ere
ntvalues.
Thenextstep
inourre
search
isto
reduce
theSignal/Noisera
tio.
Wewillexperimentwithusingslightlyco
rrugate
dsu
rface
sto
incr
ease
theelongationofth
efilm
.W
ewillalso
use
larg
erse
nso
rs,and
variousdi!
ere
ntadhesivesto
mountth
ese
nso
r.Finally,
wewillattemptto
connect
twose
nso
rsin
para
llelto
incr
ease
theoutp
ut.
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AmericanInstituteofAeronauticsandAstronautics