1

UAV – lecture no 6 devoted to

Technologies 2

Zdobyslaw Goraj

Warsaw, 9.04.2020

2

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

3

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

4

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

5

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 ?

6

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.

7

Darkstar

LMSW - Lockheed Martin Skunk Works (Palmdale, CA)

BMAD – a composite structure company

8

Pointer MTOW

Endurance

Max speed

Flight radius

Payload

4,55kg

2h

69km/h

8km

0,91kg

9

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

10

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

11

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)

12

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

13

Canadian's CL-

227 Sea Sentinel

Nicknamed the

„PEANUT”

14

Other ideas

Flying saucer

Flying deformable wing

15

Ground Control Station – different versions

Pointer

Dragon Eye

16

SAMONIT – GCS based on COTS Trolley

17

Transport

18

CAPECON Configurations

IAI

ONERA

PW

PW

POLITO

UNINA

EUROCOPTER

AGUSTA

19

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

20

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

21

SAMONIT (Proposal accepted

by MoReHES)

Start: May 2007

Duration: 3y

Value: ~ $ 0.9 mln

22

SAMONIT – baseline configuration

23

SAMONIT – swept wing configuration

24

Successive phases of parachute deployment

25

Moulds, frames, ribs etc. ready for the fuselage

and wing assembling

PW113 - structure

Forward electronics

& sensors bay Bottom electronics & sensors buy

Backward electronics buy

Main segment of the structure

- central fuselage Engines

PW113 – central element of the

structure - continued Three main frames

made of alluminium alloy Other frames made

of composite material

Wing – fuselage joining

PW113 – central element of the structure

Body fuel tank

Bay for on-board systems:

electro-energetical, air-conditioning,

navigation, control, ...

SATCOM Antenna and Radome

SATCOM - KU band

antenna about 800 mm

diameter

For high data link rate or

real time communication

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

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

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

Horizontal and Vertical tail structure concept

Front Spar

Rear Spar

Rear Spar

Front Spar

Fuselage production breakdown concept

Upper Cover

Lower Cover

Lower Cover

Payload Section

SATCOM

Fairing

Frame

Floor

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

36

Main frame located at the

joining of wing spar,

tail beam and central

fuselage

2020-03-29 Z.Goraj: Problemy projektowe ...

ILOT, 29.03.2004 37

PW-103 - Wing box structure

Sandwitch cover Carbon rowing

Wing – torque box

2020-03-29 Z.Goraj: Problemy projektowe ...

ILOT, 29.03.2004 38

PW-114 - Wing tip stbilizer structure

wing tip –

vertical

stabilizer

Wing

wheel

2020-03-29 Z.Goraj: Problemy projektowe ...

ILOT, 29.03.2004 39

PW-103 - Wing structure

2020-03-29 Z.Goraj, St.Suchodolski: Samoloty

bezzałog. ..., 15.06.2004 40

Aircraft structure

Civilian Long Range UAVs - Design

Challenges 41

Materials & structure

Torsion box - epoxy-carbon composite

Main spar flanges - carbon roving

Walls – filled with polyurethane foam

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

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