UAV lecture no 6 devoted to Technologies 2itlims-zsis.meil.pw.edu.pl/pomoce/UAV/ENG/Lecture... · 2...
Transcript of UAV lecture no 6 devoted to Technologies 2itlims-zsis.meil.pw.edu.pl/pomoce/UAV/ENG/Lecture... · 2...
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UAV – lecture no 6 devoted to
Technologies 2
Zdobyslaw Goraj
Warsaw, 9.04.2020
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Power supply for -UAV
CdNi
NiMH
Li-poli
Battery of ~7,4 V and capacity of ~ 120 mAh
36g 16x24x42mm (7,2V)
19,2g 20x30x13,7mm (7,2V)
7g 9x21x28 mm (145mAH)
Other concepts:
Combustion engine
Gas micro-turbine with
alternator (current generator)
Fuel cells
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Copying the nature Mechanical seeds powered with micro-rocket engines will have range till 1 km
and carry-on of 10 grams of sensors (cameras, microphones, which can stay
on site). Micro UAVs can return back for next portion of sensors
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Conclusion and recommendation
Speedy horizontal flight Hover
possibility
efficiency
Manoeu-
vrability
possibility
efficiency
Manoeu-
vrability
Fixed wing yes Very
good
Very
good
no - -
helicopters yes average average yes average average
Enthomo-
pters
no - - yes Very good Very good
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Type of missions
• Long range and endurance,
high maximum speed
• Short range, high maximum
speed, hover
• Essential endurance, high
aerodynamic efficiency and
manoeuvrability in hover
Fixed wing ?
Ornithopter ?
Rotary vehicle like
helicopter
Enthomopter ?
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GlobalHawk
Crash, South Arabia, Dec. 2001,
Aircraft went into flat spin,
Caused by a 2 min interruption of
Communication. When Com. was
Reestablished recovery from spin
was not possible.
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Darkstar
LMSW - Lockheed Martin Skunk Works (Palmdale, CA)
BMAD – a composite structure company
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Pointer MTOW
Endurance
Max speed
Flight radius
Payload
4,55kg
2h
69km/h
8km
0,91kg
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Dragon EyE (used in I Gulf War 1992)
MTOW
Endurance
Max speed
Flight radius
Payload
2,3kg
0,5-1h
64km/h
8km
0,45kg
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Experience gained in PW – C.G.
MTOW
Endurance
Battery NiCd
Battery Li
Max speed
Payload
2kg
15min
1h
70km/h
0,2kg
MTOW
Endurance
Battery NiCd
Battery Li
Max speed
Payload
5kg
15min
1h
70km/h
0,8kg
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UAV carried-on in artillery missiles
When close to target the UAV have to
leave the shell and start its independent
flight
When folded must be inside the shell of
155 mm diameter
Must withstand the initial acceleration
of 60000 g
Power of emitter must allow the
communication range typically 50 km
range
Combat applications „UAVs” GLUAV – Gun Launched
Unmanned Aerial Vehicle
(US Army)
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Rotary mini UAV UAV VTOL, used for surveillance mission either in
urban environment or in densely tree-covered
areas
MTOW
Payload
Endurance
Flight radius
Wariant 1
10kg
0,5kg
15min
1km
Wariant 2
35kg
3,5kg
25min
2km
Reciprocal engine
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Canadian's CL-
227 Sea Sentinel
Nicknamed the
„PEANUT”
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Other ideas
Flying saucer
Flying deformable wing
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Ground Control Station – different versions
Pointer
Dragon Eye
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SAMONIT – GCS based on COTS Trolley
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Transport
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CAPECON Configurations
IAI
ONERA
PW
PW
POLITO
UNINA
EUROCOPTER
AGUSTA
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WUT – MALE Configuration
WUT PW103 Configuration
WUT PW103 Internal Layout
Maximum Takeoff Weight
Basic Empty Weight
Fuel Weight
Payload Weight
Span
Reference Area
Propulsion Type
Propulsion
Flight Altitude
Total Endurance
kg
kg
kg
kg
m
m 2
kft
hr
930
488
225
217
12 . .6
10 . 22
Piston
20
42
TAE 125
Auxiliary power unit
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PW-126 VLUAV class airplane
0
1000
2000
3000
4000
50.00 100.00 150.00 200.00 250.00
speed [km/h]
ran
ge
[k
m]
0
10
20
30
40
en
du
ran
ce [
h]
range
endurance
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SAMONIT (Proposal accepted
by MoReHES)
Start: May 2007
Duration: 3y
Value: ~ $ 0.9 mln
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SAMONIT – baseline configuration
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SAMONIT – swept wing configuration
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Successive phases of parachute deployment
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Moulds, frames, ribs etc. ready for the fuselage
and wing assembling
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PW113 - structure
Forward electronics
& sensors bay Bottom electronics & sensors buy
Backward electronics buy
Main segment of the structure
- central fuselage Engines
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PW113 – central element of the
structure - continued Three main frames
made of alluminium alloy Other frames made
of composite material
Wing – fuselage joining
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PW113 – central element of the structure
Body fuel tank
Bay for on-board systems:
electro-energetical, air-conditioning,
navigation, control, ...
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SATCOM Antenna and Radome
SATCOM - KU band
antenna about 800 mm
diameter
For high data link rate or
real time communication
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Structural concept
Construct of composite materials to keep structure as light as possible and at the same time sufficiently strong.
The structure is basically composed of :
– Sandwich structures of Graphite\Epoxy plies – Nomex honeycomb or Rohacell foam core
Fuselage
Structure
Wing Box
Tail Spars
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Modular Structural Segments Design
Engines
nacelles
Reducing the transportability Footprint to one standard
40ft (11.7m) container
Unitized structure (maximum segment
length 11.7m)
SATCOM
radome
Aft cover
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Wing structure concept
Front spar
Rear spar
Lower cover
Upper cover
Front Spar
Rear Spar
Rohacell
foam core
Upper
flange
Lower flange
Spar concept
The spars are comprised of upper and lower flanges
made of GR\EP plies and sandwich web made of
Rohacell core and GR\EP plies
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Horizontal and Vertical tail structure concept
Front Spar
Rear Spar
Rear Spar
Front Spar
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Fuselage production breakdown concept
Upper Cover
Lower Cover
Lower Cover
Payload Section
SATCOM
Fairing
Frame
Floor
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Fuselage structure concept Cover
Floo
r
Rib
Modular
payload bay
Floor
Rohacell foam core
GR\EP plies
Covers
Frames, ribs and floors
Nomex honeycomb core
GR\EP plies
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Main frame located at the
joining of wing spar,
tail beam and central
fuselage
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2020-03-29 Z.Goraj: Problemy projektowe ...
ILOT, 29.03.2004 37
PW-103 - Wing box structure
Sandwitch cover Carbon rowing
Wing – torque box
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2020-03-29 Z.Goraj: Problemy projektowe ...
ILOT, 29.03.2004 38
PW-114 - Wing tip stbilizer structure
wing tip –
vertical
stabilizer
Wing
wheel
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2020-03-29 Z.Goraj: Problemy projektowe ...
ILOT, 29.03.2004 39
PW-103 - Wing structure
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2020-03-29 Z.Goraj, St.Suchodolski: Samoloty
bezzałog. ..., 15.06.2004 40
Aircraft structure
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Civilian Long Range UAVs - Design
Challenges 41
Materials & structure
Torsion box - epoxy-carbon composite
Main spar flanges - carbon roving
Walls – filled with polyurethane foam
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Civilian Long Range UAVs - Design
Challenges 42
Torsion box section (HALE PW-114)
Mass [kg] %
m1 0,60 6,5
m2 3,17 34
m3 3,17 34
m4 0,59 6,5
m5 0,87 9,5
m6 0,88 9.5
Torsion box total 9,28 100
Weights of wing components [kg]
torsion box with fuel ribs, nose and
anti-icing installation
96
control surfaces 11.5
wingtip with brackets 7.8
control surfaces’ consoles 3
actuators 16.5
fuel installation 6
Whole wing
2x 140,8 =
281.6 kg
4,5 % of
max TOW
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Civilian Long Range UAVs - Design
Challenges 43
Extended fuel tank wing section (FT/EX) internal fuel
FT/EX - (t/c)max = 24%
HERON-1 - (t/c)max = 21%
-2.5
-2.0
-1.5
-1.0
-0.5
0.0
0.5
1.0
0.0 0.2 0.4 0.6 0.8 1.0x/c
CpCp
x/c
Cl = 1.5-2.5
-2.0
-1.5
-1.0
-0.5
0.0
0.5
1.0
0.0 0.2 0.4 0.6 0.8 1.0x/c
CpCp
x/c
Cl = 1.5-2.5
-2.0
-1.5
-1.0
-0.5
0.0
0.5
1.0
0.0 0.2 0.4 0.6 0.8 1.0x/c
CpCp
x/c
Cl = 1.5Cl =1.7
-3.0
-2.0
-1.0
0.0
1.0
0.0 0.2 0.4 0.6 0.8 1.0
x/c
Cp
WT
MSES
FT/EX
SA-21