Project Presentation Boiler Xpress December 5, 2000 Team Members Oneeb Bhutta Matthew Basiletti Ryan...
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![Page 1: Project Presentation Boiler Xpress December 5, 2000 Team Members Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal Van Meter AAE 451 Aircraft Design.](https://reader036.fdocuments.net/reader036/viewer/2022062714/56649d3b5503460f94a15bd0/html5/thumbnails/1.jpg)
Project Presentation Boiler Xpress December 5, 2000
Team Members Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal Van Meter
AAE 451 Aircraft Design
![Page 2: Project Presentation Boiler Xpress December 5, 2000 Team Members Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal Van Meter AAE 451 Aircraft Design.](https://reader036.fdocuments.net/reader036/viewer/2022062714/56649d3b5503460f94a15bd0/html5/thumbnails/2.jpg)
Presentation Overview Design Mission Concept Selection & Initial Sizing Detailed Analysis:
Aerodynamics Structures Propulsion Stability, Dynamics, and Control
Conclusions
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The Mission
Variable Stability Aircraft- Roll Axis 1.2 lb payload
Flight Within Mollenkopf Athletic Ctr: 20 ft/s stall speed 12 minute Endurance/ electric power
plant Robust and Affordable Transportable Airframe cost < $200
![Page 4: Project Presentation Boiler Xpress December 5, 2000 Team Members Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal Van Meter AAE 451 Aircraft Design.](https://reader036.fdocuments.net/reader036/viewer/2022062714/56649d3b5503460f94a15bd0/html5/thumbnails/4.jpg)
Flight Mission
5.5 deg Climb Angle
35 ft Radius
120 ft. max T.O. roll
10 second “Straight Line”
42’ Ceiling height
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1
2 3
4
5
ObjectiveScore % of
TotalRank
Endurance 30 10.0 7
Build within 3 weeks
10.0 9.16 4
Light weight 27.5 16.66 1
Turning radius 9.16 16.66 2
Robustness 50 10 6
Transportability 16.66 4 9
Ease of analysis 50 7.5 8
Landing ability 16.66 2.66 10
Maintainability 30 10 5
Marketability 10 13.33 3
Weighted Objectives Method
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Constraint Diagram
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Initial Sizing Electric Models wing area vs weight
0
200
400
600
800
1000
1200
1400
1600
1800
0 50 100 150 200 250 300 350 400
Weight (oz)
win
g a
rea
(sq
.in
.)
![Page 8: Project Presentation Boiler Xpress December 5, 2000 Team Members Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal Van Meter AAE 451 Aircraft Design.](https://reader036.fdocuments.net/reader036/viewer/2022062714/56649d3b5503460f94a15bd0/html5/thumbnails/8.jpg)
Geometry and Configuration
Wing:•Sref = 13.5 sq.ft.•Span = 11 ft.•Aspect Ratio = 9•Taper Ratio = 0.6 tip section•Airfoil: S1220
Horizontal Stabilizer:•Area = 1.83 sq ft.•Span = 3.0 ft.
Vertical Stabilizer:•Total Area: 1.15 sq.ft.
Boiler Xpress 11.1’
5.8’
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Aerodynamic Design Issues
Lift
• Low Reynolds Number Regime
• Slow Flight Requirements
Drag
• Power Requirements
• Accurate Performance Predications
Stability and Control
• Trimmability
• Roll Rate Derivatives
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Low Reynolds Number Challenges
•Laminar Flow -more Prone to Separation
•Airfoil Sections designed for Full-sized Aircraft don’t work well for below Rn=800,000
•Our Aircraft Rn=100,000-250,000
Separation Bubble-to be avoided!
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Airfoil Selection
Wing:Selig S1210
CLmax = 1.53 Incidence= 3 deg
Tail sections:flat plate for Low ReIncidence = -5 deg
Re = 150e3
0
0.01
0.02
0.03
0.04
0.05
0.06
-0.2 0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8 2 2.2
Cl
Cd
FX63-137
S1210
S1223
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Drag Prediction Assume Parabolic Drag Polar
2
0 LDD KCCC
AeK
1
75.0e Based on Empirical Fit of Existing Aircraft
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Parasite Drag
ref
wetfDo S
QFFSCC
(Ref. Raymer eq.12.27 & eq.12.30)
58.2(Re)10log
455.02.1fC
Drag Build-up Method of Raymer
Blasius’ Turbulent Flat Plate- Adjusted for Assumed Surface Roughness
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Drag Polar
0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.80
0.02
0.04
0.06
0.08
0.1
0.12
0.14
0.16
Aircraft Drag Polar
CL
CD CDiCDo
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Power Required
15 20 25 30 35 4016
18
20
22
24
26
28
30
32
Velocity [ft/s]
Po
wer
Req
uir
ed [
ft-l
b/s
]
Predict:• Power required for cruise
• Battery energy for cruise
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Aerodynamic Properties
Wetted area = 44.5 sq.ft.Span Efficiency Factor = 0.75CL=5.3 / rad
CL e = 0.4749 /radL/Dmax = 15.5Vloiter = 24 ft/sCLmax = 1.53CLcruise = 1.05Xcg = 0.10-0.38 (% MAC)Static Margin = 0.12 at Xcg = 0.35
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Stability Diagram
elev deflect=-8 deg
-4
0
4
8
0 0.2 0.4 0.6 0.8 1 1.2 1.4 1.6 1.8-0.4
-0.3
-0.2
-0.1
0
0.1
0.2
0.3
CL
Cm
cg
elev deflect=-8 deg
-4
0
4
8
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Flow Simulation
![Page 19: Project Presentation Boiler Xpress December 5, 2000 Team Members Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal Van Meter AAE 451 Aircraft Design.](https://reader036.fdocuments.net/reader036/viewer/2022062714/56649d3b5503460f94a15bd0/html5/thumbnails/19.jpg)
Parasite Drag CDo for Wing and Tail surfaces
18.04
34.11006.01 Mct
cx
ct
FFWing
d
lf
400100
601
3
f
fFFFuselagef
FFPOD
35.01
(Ref. Raymer eq.12.31 & eq.12.33)
For Fuselage, booms & pods
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Structures Outline
Materials Employed for the structure Mathematical Model Bending Moment & Stresses; Wing Test Equipment layout Landing Gears & Landing Loads
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Structural Materials
Styrene foam wing core
Balsa spars carry bending load 0.25 in x 0.25 in
T.E. Reinforcement
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Materials Employed
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Wing
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Mathematical Model
Wing
Assumptions:•Wing and Weight loading•Method of Analysis (Theoretical Model)•2.5g x 1.5 P
Boom
Horizontal Tail
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Bending Moments
Max Moment = 41.71 lbf/ft
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Stresses in Wing
Sigmamax = 2003 psi
Sigmacritical = 1725 psi (Actual Test Result; Whiskey Tango Team, Spring 1999)
Reasons: Light Weight Structure Safety Factor (worst case scenario) Wing Test Results
I
yM maxmax
1.5ft
P
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Horizontal Tail & Boom Horizontal Tail:
Max Stress = 850psiSpar Sizes = 1/8 in x 1/16in
Booms:Max deflection = 0.24 in @ 2.5g’s x 1.5 Assuming Young Modulus (E) for a Carbon Epoxy matrix.Testing needed to verify result.Material & Time Constraint
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Equipment Layout & CG.
CG. = 30%~38% MAC (Predicted)
CG. = 35% MAC (Actual)
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Landing Gear
From Raymer. Method of Sizing and placement of Landing gears
Rotation angle = 10 deg
Tip Back angle= 14 deg
Nose Gear: (3’’ from nose)
Main gears:
-6’’ from leading Edge
-Separation (1.5 ft)
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Vland=1.3Vstall=25ft/s
lbinVKe vertgW 6.72
21
kkSdsWorkd
5.00
For d = 1 in., k = 15.2 lb/in
= -5 degVvert=2.2ft/s
For 1 inch strut travel, peak load = 15.2 lb
spar = 240 psi on landing
Landing Loads
![Page 31: Project Presentation Boiler Xpress December 5, 2000 Team Members Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal Van Meter AAE 451 Aircraft Design.](https://reader036.fdocuments.net/reader036/viewer/2022062714/56649d3b5503460f94a15bd0/html5/thumbnails/31.jpg)
Propulsion Design Issues Power Special needs Endurance Propulsion system tests
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Power
Power required is determined by aircraftPower available comes from the motor 15 20 25 30 35 40 45 50
15
20
25
30
35
40
45
50
55
Velocity [ft/s]
Pow
er R
equi
red
[ft-
lb/s
]
Power Required Power Available
![Page 33: Project Presentation Boiler Xpress December 5, 2000 Team Members Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal Van Meter AAE 451 Aircraft Design.](https://reader036.fdocuments.net/reader036/viewer/2022062714/56649d3b5503460f94a15bd0/html5/thumbnails/33.jpg)
Special Needs
Pusher configurationAdjustable timing motorReversible motor
PropellerHigh efficiency for enduranceSpecial propeller for electric flight
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System Components
PropellerFreudenthaler 16x15 and 14x8 folding
Gearbox“MonsterBox” (6:1,7:1,9.6:1)
MotorTurbo 10 GT (10 cells)
Speed ControllerMX-50
![Page 35: Project Presentation Boiler Xpress December 5, 2000 Team Members Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal Van Meter AAE 451 Aircraft Design.](https://reader036.fdocuments.net/reader036/viewer/2022062714/56649d3b5503460f94a15bd0/html5/thumbnails/35.jpg)
System EfficienciesPropeller
60-65%
Gearbox95%
Motor90%
Speed Controller95%
Total System Efficiency
50.7%
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Propulsion TestsBoiler Xpress Propulsion system Tests
-0.2
0
0.2
0.4
0.6
0.8
1
1.2
1.4
1.6
1.8
0:00:00 0:02:53 0:05:46 0:08:38 0:11:31 0:14:24 0:17:17
Time (h:mm:ss)
Th
rust
(lb
)
Static
Test1
Test2
Test3
Test4
Endurance
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Torque Sensor
Motor/Prop
To Batteries
Test Stand Attached to Wind Tunnel Balance
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Aircraft Analysis
Best Endurance SpeedVe = 23.2 ft/s
Power Required at Best Endurance SpeedPr = 15.62 ft-lb/s
![Page 39: Project Presentation Boiler Xpress December 5, 2000 Team Members Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal Van Meter AAE 451 Aircraft Design.](https://reader036.fdocuments.net/reader036/viewer/2022062714/56649d3b5503460f94a15bd0/html5/thumbnails/39.jpg)
Flight Performance
Increased weight17% increase
Increased cruise flight speed22% increase
Lift coefficient26% decrease
Endurance/Power42% decrease in endurance
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Flight Performance, Stability & Control Sizing of horizontal and vertical tails
and control surfaces Location of c.g. and aerodynamic
center Determination of static margin Roll-axis block diagram Transfer functions Flight Performance Data
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Horizontal and Vertical Tail Initial Sizing
v
refvv x
bSVS
h
refhh x
cSVS
Vh - Horizontal tail volume coefficient = 0.50Vv - Vertical tail volume coefficient = 0.044
(8.3) (8.4)
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Control Surface Sizing
Based on historical data from Roskam Part II Tables 8.1 and 8.2.
ref
a
S
S
v
r
S
S
h
e
S
S
Homebuilts Single Engine
0.095 0.08
0.42 0.36
0.44 0.42
235.1 ftSa
280.0 ftSr
200.1 ftSe
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Dihedral Angle Paper by William McCombs
suggests 0 – 2 degrees for RC aircraft with
ailerons. Estimated by Raymer for a mid-
wing aircraft to be 2 – 4 degrees. Our Aircraft- 2 degrees
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X-plot Horizontal Tail
1.2 1.4 1.6 1.8 2 2.2 2.4 2.6 2.8
-0.4
-0.2
0
0.2
0.4
0.6
0.8
1
Horizontal tail area [sq ft]
x/c
cg location neutral point
Xac = 0.46
Xcg = 0.35
SM = 11% MAC
cgac XXSM
-Used to find elevator area for desired Static Margin
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X-plot Vertical Tail
0.4 0.6 0.8 1 1.2 1.4 1.6 1.8
-0.4
-0.2
0
0.2
0.4
0.6
Vertical tail area [sq ft]
CnB
eta
Used to determine Weathercock stability (yaw)
Cn = 0.11
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Flight Performance
Calculated MeasuredTake-off Distance (ft) 56.7 70 (astroturf)Turn Radius (ft) 50 < 40Cruise Speed (ft/s) 24 28Endurance (sec) 720 730
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Tx
Rx 1
k
/
+ aP
Block Diagram – Roll Axis
85.76
31.62
s
95040
9502 ss
Servo Aircraf
t
Gyro
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Dynamic Modeling
85.76
31.62
)(
)(
ss
sP
a
xx
l
I
qSbCL a
a
1
2
2 UI
CqSbL
xx
l
pp
p
a
l
l
C
C= 0.80
= -0.15
s
rad
2s
rad
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Root Locus
-90 -80 -70 -60 -50 -40 -30 -20 -10 0 10 20-80
-60
-40
-20
0
20
40
60
80
Real Axis
Imag
Axi
s
De-stabilizing feedback
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Nyquist Diagram
Real Axis
Imag
inar
y A
xis
Nyquist Diagrams
-1 -0.8 -0.6 -0.4 -0.2 0 0.2 0.4-0.4
-0.3
-0.2
-0.1
0
0.1
0.2
0.3From: U(1)
To
: Y(1
)
K = 0.3655
Gm=25.4284
Pm=inf.
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Economics
Man-hours per week Structural Cost Break-Up Propulsion & Electronic Equipment
Cost Total Cost of the project
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Man-Hours
BoilerXpress Man hours per Week
0
50
100
150
200
1 2 3 4 5 6 7 8 9 10 11 12 13 14
Number of Weeks
To
tal
Te
am
Ho
urs
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Structural Cost
Glue23%
Balsa7%
Micafilm13%
foam12%
fiber glass3%
Carbon fiber booms22%
wires9%
others11%
Cost = $292.00
![Page 54: Project Presentation Boiler Xpress December 5, 2000 Team Members Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal Van Meter AAE 451 Aircraft Design.](https://reader036.fdocuments.net/reader036/viewer/2022062714/56649d3b5503460f94a15bd0/html5/thumbnails/54.jpg)
Structural Cost Break-UpStructural CostComp. Cat. # Description Qty. Price/unit subtotal
CST A105-A 105 resin 1 $23.70 $23.70CST A206-A Slow Hardener (5:1) 2 $11.40 $22.80CST S-G01040-38 Fiberglass 0.5 oz/sq-yd. (2 yards) 1 $10.00 $10.00
Tower LXAS81 5510 Lite Ply 1/8"x6"x12" (6) 1 $12.59 $12.59Tower LXB243 yellow Micafilm 65" (rolls) 1 $9.99 $9.99Tower LXB247 yellow Micafilm 15' (rolls) 1 $26.99 $26.99Tower LXD867 Dubro Threaded Rod 2-56x12" (6) 1 $2.39 $2.39Tower LXD882 Dubro Nylon Kwik-Link Standard (2) 3 $0.70 $2.10Tower LXJC94 1/4"x3"x36" Balsa - 8pcs 1 $7.99 $7.99Tower LXNK03 Motor Wire (black) 2 $6.49 $12.98Tower LXNK04 Motor Wire (red) 2 $6.49 $12.98Lowes Blue or Pink Foam (4'x8' sheets) 2 $17.00 $34.00
epoxy glue 1 $20.00 $20.00Carbon fiber 1/2" x .032" x 60 " tubes for booms 2 $32.75 $65.50screws and fasteners 1 $15.00 $15.00Purdue University Stickers 2 $4.99 $9.98spray paint 1 $3.00 $3.00
Total $291.99
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Motor & Electronic Equipment
Propulsion & Electronic Equipment Cost
Comp. Cat. # Description Qty. Price/unit subtotalHobby HLAN241 1/4" Prop Shaft Adapter 1 $1.00 $1.00Hobby HLAN3168 14x8 Prop Blade 1 $13.40 $13.40Hobby HLAN3186 16x15 Prop Blade 1 $15.30 $15.30Hobby HLAN4223 47mm Middlepart Yoke 1 $12.00 $12.00Hobby HLAN5145 45mm Spinner 1 $5.00 $5.00MEC Motor Power Package 1 $200.00 $200.00
$246.70Radio Control System (transmitter, receiver etc.) 1 $250.00 $250.00Battery packs 1 $70.00 $70.00Battery charger 1 $100.00 $100.00
Tower LXTX41 Hitec/RCD HS-55J Economy Sub Micro Servo Futaba2 $19.99 $39.98Rate Gyroscope 1 $109.00 $109.00
$568.98
Total $815.68
Propulsion
Electrical Equipment
![Page 56: Project Presentation Boiler Xpress December 5, 2000 Team Members Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal Van Meter AAE 451 Aircraft Design.](https://reader036.fdocuments.net/reader036/viewer/2022062714/56649d3b5503460f94a15bd0/html5/thumbnails/56.jpg)
Total CostMan-Hour Breakup
Rate = $75/hour
hours CostPreliminary Design 525 $39,375.00
Testing 50 $3,750.00Build 720 $54,000.00
Test Material $81.70Structural Cost $291.99
Prop and Elec Cost $815.68Total Cost $98,314.37
![Page 57: Project Presentation Boiler Xpress December 5, 2000 Team Members Oneeb Bhutta Matthew Basiletti Ryan Beech Micheal Van Meter AAE 451 Aircraft Design.](https://reader036.fdocuments.net/reader036/viewer/2022062714/56649d3b5503460f94a15bd0/html5/thumbnails/57.jpg)
ConclusionsFlight performance requirements met
Turn radiusEnduranceTake-off distance
Stabilizing feedback implementedFuture Work
Data logger installationImplement destabilizing feedbackRefine propulsion analysis method (further testing)Perfect construction method
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Questions?