Supervisor: Artzi Dror. Preliminary Design Review

Transcription

1 Remote Special Purpose- Eye Supervisor: Artzi Dror Preliminary Design Review

2 This project deals with UAV, that is carried and launched by the existing manned plane. The UAV s purpose is to enlarge the mother plane s range of surveillance. During this semester different surveys about the existing UAVs, the airplanes with external additions, EO/IR payloads, data transfer systems were done. 2

3 Mission definitions and purpose Mission requirements Operational concept Communication general concept Market survey ( similar system, communication) UAV concept and component selection Returning or non-returning UAV UAVs selection E/O turrets selection Modifying the UAV existing model Gondola configuration: Configuration Existing aircrafts, comparison drag Lateral & Longitudinal stability Doors UAV release concept Performance Radius of flight possibilities, endurance of mission Wind Tunnel Model Tasks for the next semester 3

4 Special Purpose EYE : video information broadcast from distant location by UAV deployed from a surveillance aircraft. Purpose: to extend the surveillance limit of existing IAF plane King Air B200 by an air deployed UAV News-Ch.1 (news1.avi) 4

5 Range 3283 km Endurance 8 hr Cruise/Top speed 220/292 kt Useful load 1790 kg Dimensions: Length m Wingspan m Height 4.54 m 5

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8 Communication general concept We ve discussed several options for communication from UAV to ground operator: UAV>>>Airplane>>>Satellite>>>Ground - Beyond Line Of Sight UAV>>>Airplane Line of Sight 8

9 Range from few meters to hundreds of Km. Telemetry and Video 9

10 Satellite Communications solutions Aeronautic VSATS for High Altitude Long Endurance UAVs 10

11 Communication types low bandwidth telemetry link high bandwidth analog/digital In most cases, both the wireless telemetry and real-time video links will be integrated into the UAV with unity gain omni-directional antennas. 11

12 Scheme of UAV communication Transmitting video from UAV to airplane 2.4 GHz Video receiver Data modem Antenna for UAV Video cam. Transmitter 900 MHz GPS Transponder Data modem Transmitting/Receiving data from UAV to airplane Auto-pilot 12

13 Video/Data transfer components selection Several options were checked. Most of transmitters/receivers have very similar characteristics. That's why, It was decided to use Israel-made systems. 13

14 UAV transmitter COMMTAC: CTX-Series: Analog video (PAL, NTSC), audio, data Output power: 200mW-15W Bandwidth: 16Mhz,??kbs Frequency band: L,S,C,X,Ku Range: ~150Km Weight: 420gr 14

15 COMMTAC: CRX-Series: Analog video (PAL, NTSC), audio, data Bandwidth: 16Mhz,??kbs Frequency band: L,S,C Weight: 370gr 15

16 OMA-P2S102 Omni-directional antenna: Frequency: Mhz, Mhz Height: 250 mm Weight: 0.14 kg One of the advantages of this antenna, that it s can be installed inside the UAV s tale to reduce drag 16

17 Airplane Transmitter/Receiver 17

18 Transmitting power/range calculation 18

19 Returnable Or Non-Returnable UAV Criteria Non-Returnable Returnable Fuel weight percentage for same configuration less More Transmitters dimensions Increasing with range Increasing with range Landing equipment May not be needed Weight/ increased complexity Self - destruction option Weight/ complexity Even more Weight/ complexity 19

20 Returnable or no continued Criteria Non-Returnable Returnable Structure Less weighting one-time job units More costly / complex/ heavy Launch reliability Can allow failure Can t allow failure Range / Endurance All the fuel => mission More than ½ fuel => go home Cost less Need to buy new one every time Bought once can be used more than one time additional maintenance expenses, even more in case of failure 20

21 The Non-Returnable UAV concept was chosen. 21

22 Dominator Raytheon MALD ScanEagle Integrator MON Guard Aerosonde Weight 27kg 100 kg 18kg 59kg 50 kg 15kg Fuel weight, % Concept 150% unknown 30% 40% Unknown, concept 33% Endurance 24h 6h 20h 24h 6.5 h 30h Range Concept 920km 500km 990km 100 km 3000km Speed Concept 111km/h 150 km/hr 60 km/h 80 km/hr Cost Concept $ $ Concept Concept $ picture Payload 2kg 20 kg 11kg 0.6kg Unknown, concept concept 22

23 Category MONGuard ScanEagle Status Concept Existing Information availability mounting on an airliner Release from an airplane The most possible amount possibility possibility Not as much as for the MONGuard Design changes must be made Design changes must be made 23

24 Category MONGuard ScanEagle Max. takeoff weight 50 kg 18 kg Payload Equipped with 2 cameras, possibility to design Carries an inertially stabilized e.o. and i.r. camera Price Concept $ x 1 Payload weight 20 kg 6 kg 24

25 MONGuard: The MONGuard uav was chosen. 25

26 E/O Turrets selection 26

27 Name/ Manufacturer Sensor Field of View (FOV) Power Requir ements Weight [kg] COBALT FLIR IR 1 IR2 EO1 EO2 14.5X cont. WIDE FOV TV 14.7X WIDE FOV 2 gimbel Azimuth 360 Elevation: ~70W 8.2kg D190mm H270mm ESP-600C Controp Daylighy Wide angle Zoom camera IRThermal 15X 3 gimbel 10 μ rad Azimuth 360 Elevation: W 12.3kg D250mm H300mm Mini POP D IAI 4 sensors Daylight Thermal Wave Laser 2-25X Better than 50 μ rad Azimuth 360 Elevation: ~ 150W 7.7kg D204mm H280mm Micro- COMPASS Elop-Elbit FLIR Color TV Laser 4X elec. 12X elec. 50 μ rad Azimuth 360 Elevation: W 6-8kg D210mm 27

28 Cobalt ESP 600 Mini POP MicroComp Flir Controp IAI ELOP 28

29 Name/ Manufact urer Sensor Zoom Field of View (FOV) Power Requir ements Weight [kg] Dimensions Micro POP IAI Day Or Night Wide angle 2-4X electronic Better than 150 μ rad Azimuth ±170 Elevation: W 1.2kg D104mm H180mm TASE DUO Cloud Cap FLIR IR And SONY Vid 2X elec. 26X optical 1 gimbal Azimuth 360 Elevation: W 1.1kg D130mm H195mm SCOPe 100 Day or Night FCB CCD μ Better than 200 μ rad 2gimbel Azimuth: ±173 Elevation W ~1kg D 100mm H182mm Micropilot Mp Day or Night Optical 25X 2X Digital Better than 400 μ rad 2gimbel Azimuth ±170 Elevation: W+ 0.9kg D110 H210 29

30 MicroPOP TASE DUO MicroPilot IAI CloudCap MP-Visione 30

31 The EO payload best suited to SP-EYE purpose is: MicroPop Pros: - excellent onboard stabilization -1 sensor, refitable for day/night use -small dimensions -low price (estimation) -made in Israel Micro POP IAI Day Night Wide angle 2-4X electronic Better than 150 μ rad Azimuth ±170 Elevation : W 1.2kg D104mm H180mm Cons: -heaviest among the light-weight EO turrets -mediocre optics 31

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33 Propeller Wing Thrown Appliances Canard Parachute Batteries Engine Fuel Tank (rear) Air Bag Camera (rear) Air Bag Fuel Tank (front) Camera (front) 33

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35 Weight after removing the components: M gr 35

36 Calculation the center of gravity of removed parts ( without fuel tank ) ˆ X cg ˆ 1110 X c. g. mm C.G. of the payload of our configuration (including fuel addition) must be at the same place. Calculations to find the center of gravity of the fuel tanks X cg.. n n X c. g. of fuel mx n m X c. g. of fuel 1370 n n mm C.G. of all the fuel (including fuel addition) must be at the same place 36

37 Antenna Self-destruct Mechanism Engine + Generator Fuel tank Avionics Transmitter + Receiver Camera 37

38 Part Camera Generator Transmitter Receiver Antenna Avionics + Gps + Auto pilot Fuel Tank Self-Destruct Mechanism 1 Self-Destruct Mechanism 2 Self-Destruct Mechanism 3 Mass [kg] ( add) Distance from nose [mm] 30 2, , , Adding 50% more fuel Adding 50% more endurance 38

39 Installation Process: ~C.G. of plane fwd The new configuration has the same center of gravity The Antenna was placed in the same line as the Self-destruct Mechanisms: 1 placed near the wings, to prevent aerodynamic changes as best as The camera, transmitter, 2 placed on receiver the transmitter and GPS with and receiver avionics The possible. Generator, Fuel Camera tank placed places was placed in next c.g. of to in former the front engine. fuel of tank the were and 3 placed was placed arbitrary for balance to balance and the will detonate moment. vehicle to ensure maximum spatial view towards the fuel tank. 39 Hence we don t need to make a new control system.

40 Payload in gondola under the body Payload Not need on to the open pylon under wings fuselage during the flight It is more safe to Why extract not? : there are no pylons on the But body we will and need wings to deal with is problems necessary : for UAV to 1. withstand It has certain the same height stress limitations. that the Mother plane 2. It does. might (additional affect the reinforcements angle of attack for during UAV will landing. be needed) Payload inside the plane Why not? : Upper fuselage position is compressed, of payload it can t be opened during Why the flight not? :. The payload hides the vertical tail Extraction is dangerous for mother plane 40

41 List of signs: As were said earlier we need to use antennas to control the UAV and to receive data R- dish radius S- hub distance f- focus distance Simplified scheme of antenna D- dish depth To meet the mission requirements it is enough for antenna azimuth range to be 360 and pitch range to be 90 (mother plane will be always above the UAV) Existing system Needed volume calculation 41

42 Result dimensions The requirement of 360 azimuth forms axisymmetrical body Height = 570 mm Diameter = 640 mm Bottom view Side view Pitch angle 0 90 Isometric view 42

43 In order to receive data/video Optimal distance between 2 from two UAV-s simultaneously antennas is not less than length of Distance xR~3150 we might have two antennas. UAV Distance-2 x r ~640 Which minimal distance between antennas is needed for their optimal work? First antenna 30% of sphere 1.2% of sphere Possible position of second one If the antennas are close to each other, one antenna will hide 30% of working surface of another 43

44 UAV & Antenna position in gondola Main dimensions ~1200 Back limitation Front limitation 44

45 UAV & Antenna position in gondola Choosing optimal configuration This configuration is optimal. Foregoing calculations will be based on it. This configuration is not optimal. If This we configuration have 2 UAV-s is in not the optimal. air it is impossible to get There Data/Video will be lots from of free both space UAV-s under simultaneously the UAV, with that one UAV-s antenna position will make huge front area addition. 45

46 Type 1 Type 2 Type 3 SP-EYE 46

47 Comparison table Name comparison picture Front area add. m²(%) ~S wet add. m²(%) Comparison of add. to SP-EYE one Front, ~S wet %,% SP- EYE 0.63 (7.8%) 5.6 (5%) 100%, 100% Type (6.25%) 4 (3.6%) 80%, 80% Type Type 3 12 Type (3.9%) 4.5 (4%) 50%, 90% Type 3 0.5(6.25%) 3.12(2.7%) 80%, 62% SP-EYE 47

48 Bombardier Global CTAS Embraer 145 Multi Intel & AEW&C 48

49 Name picture Front area tot. m² ~S wet Front area add. m²(%) ~S wet add. m²(%) SP-EYE B (7.8%) 5.6 (5%) Global Express (2.1%) 19.8 (5%) Embraer 145 SIVAM AEW&C (2.25%) (5.8%) Embraer 145 Multi Intel (12.3%) 9.34 (3.9%) 49

50 Aerodynamics 1. Gondola" faces 3. the 2. Lateral 1. same Longitudinal Overall stability flight performance: stability: conditions as the rest of the plane. 2. Change in Stability Derivatives of the plane will be linear with gondola all The the Adding gondola - s lateral derivatives of gondola position will will in the be affected. affect lower the part plane of the overall s area and position. the fuselage main performance effect will produce is expected negative on vertical pitch moment tail 3. Gondola - s position righting near moment to aerodynamic ( N ) center reduce arm of forces that appeared because of addition. 4. We expect these effects to be small. 5. Detailed calculation of those effects will be made to CDR. 50

51 Name Picture Weight,kg Dimensions L, w, h mmxmmxmm For addition it will contain wiring Doors opening mechanism Gondola - s Pylons with Gondola - s shape reinforcements standard Antennas launch units UAV-s in ( they BRU-46 protective will be chosen later shells ) UAV (folded) x377x497 2 Antenna x640x570 2 Protective Shell x395x560 2 BRU x51x152 2 Gondola shell x820x600 1 Doors opening mechanism and wiring Total ~ 390 ~20 n/a n/a Quantity 51

52 Based on C-beam that has good bending stiffness prevent damages during UAV- s extracting from mother plane but not adding much volume Composite materials made of. needed stiffness small weight. inner geometry will prevent UAV- s damages during the extracting from the protective shell UAV front view Protective shell with UAV side view Protective shell isometric view Protective shell front view 52

53 Parachute 53

54 Films (Movie1.flv) Air launch of UAV Dominator concept MONGuard (Movie2.wmv) MonGuard launch from ground station

55 Wings Parachute UAV The unfolding, Stabilization UAV is is in UAV Inflating decrease releasing free beginning air ejected the from of Doors Doors by parachute velocity its open the BRU-46 shell mission air open close 55

56 Radius of flight - possibilities: 2 Hours Observation Mission Mother plane radius 1458km MONGuard radius 1658 km 56

57 Radius of flight - possibilities: 3 Hours Observation Mission Mother Plane radius 1352km MONGuard Radius 1532 km 57

58 Radius of flight - possibilities: 4 Hours Observation Mission Mother plane radius 1246 km MONGuard radius 1446 km 58

59 Wind tunnel cross section Balance cross Plane Model section Tunnel 20 mm wall Tunnel wall Plane Model cross section Choosing scale For subsonic wind tunnel model we have 3 limitations: 1) Model FCSA (Frontal Cross-Section Area) not exceed 4% of tunnel s cross section 2) 15cm to each wall from wings 3) Balance must fit to model cross section ( not damage the original aerodynamics ) 59

60 Technion wind tunnel is 1x1 m, cross section area 1 m² Diameter of standard balance is ~20 mm To meet the requirement Model s dimensions: FCSA < 0.04m² wingspan - 70 cm Diameter of body > 40 mm. we will use 1:25 scale 8.8 m² : 25² = 0.014m² < 0.04 m² 16.6 m : 25 = m = 66.4cm < 0.7 m 60

61 Chosen scale 1:25 68 mm > 40 mm 61

62 Completion of 7 th semester tasks Components detailed design and analysis Wind tunnel experiments plane, plane with gondola Weight distribution, balancing the plane UAV control team layout for sitting and operating Design and analysis if the gondola structure, doors opening mechanism Analysis the UAV release fluency Releasing process detailed design of protection cover 62

63 We thank Mr. Arie Tzinnober for devoting his personal time and coming to the Technion, for giving a lecture about the payloads, key-terms, detailed explanations about everything that could be asked and answered: performance, prices, existing possibilities, etc. We thank Mr. Moti Ringel for giving us a detailed consulting about Technion wind tunnel, measuring equipment. 63

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