High Altitude Long Endurance UAV Configurations:

Transcription

1 High Altitude Long Endurance UAV Configurations: Civil UAV APplications & Economic Effectivity of Potential CONfiguration Solutions Giulio ROMEO, Politecnico Di Torino (Turin Polytec. Univ.).), Dept. of Aerospace Eng., Italy. Zvi SHAVIT,, Israel Aircraft Industries,, Israel Zdobyslaw GORAJ, Warsaw Univ. of Technology, Dept. of Airplane & Helicopter Design, Poland Jean HERMETZ, Onera, France CIRA, DLR, UNINA 1/64

2 Helios Global Hawk Lockheed Martin Heron HeliPlat EC 5FP POLITO, DIASP, 2/64

3 BIRD -Orbit: 570 Km Spatial Resolution: 370 m Repeat Cycle: 24 HOURS Design Life: 5 years LANDSAT - Orbit: 705Km Spatial Resolution: 15-60m Repeat Cycle: 14 days Design Life: 5 years POLITO, DIASP, giulio.romeo@polito.it Integration SATELLITE + UAV = Higher Resolution + Continuous Data 3/64

4 HALE UAV Configuration # MAIN GOAL: to define and consolidate, within a 2 iteration design cycle, 3 HALE Configurations: - MODULAR -SOLAR -BLENDED # MULTI-DISCIPLINARY OPTIMISATION SOFTWARE developed to - obtain the Optimised configuration # FINAL CONFIGURATIONS: as result of best compromise among production cost, aerodynamic performance efficiency, structural efficiency and aeroelastic behaviour, propulsion efficiency, and safety. # PERFORMANCE shall be improved by at least 20% with respect to current technologies. POLITO, DIASP, giulio.romeo@polito.it 4/64

5 Design of 3 HALE UAVs BLENDED WING - ONERA MODULAR - IAI BLENDED WING - WUT SOLAR HALE - POLITO POLITO, DIASP, giulio.romeo@polito.it 5/64

6 SHAMPO Main Characteristics SOLAR HALE UAV Solar Hale Aircraft Multi Payload & Operation POLITO, DIASP, 6/64

7 Main Systems SOLAR HALE UAV Solar Cells Fuel Cells POLITO, DIASP, O2 / H2 Tanks 7/64

8 Development of Solar HALE-UAV SOLAR HALE UAV 1st configuration 2nd configuration Classical configuration to improve longitudinal stability Introduction of sweep angle to improve longitudinal stability POLITO, DIASP, 3rd configuration 8/64

9 Solar HALE Wing Section OUTER-Wing Section Aerodynamics SOLAR HALE UAV BLENDED-zone section POLITO, DIASP, 9/64

10 DOWNWASH Reduction Aerodynamic development SOLAR HALE UAV TIP OPTIMIZATION (Tip Vortex Energy Reduction) POLITO, DIASP, 10/64

11 Aerodynamic Results SOLAR HALE UAV EFFICIENCY ENDURANCE PARAMETER POLITO, DIASP, 11/64

12 Ailerons & Landing Gear SOLAR HALE UAV Ailerons actuators Ailerons Inboard section:18.8m Outboard section:30.8m Tricycle Landing Gear POLITO, DIASP, 12/64

13 Flight Performance SOLAR HALE UAV Longitudinal Static Stability Lateral Static Stability Take off & Landing distances: Take-off: 804m - Landing: 420m POLITO, DIASP, giulio.romeo@polito.it 13/64

14 Flight Dynamic Analysis DERIVATIVES database SOLAR HALE UAV MATLAB- Simulink Longitudinal Dynamic Stability Results Lateral Dynamic Stability Within the MIL-F-8785C flying qualities levels criteria for a small light Aircraft in cruise condition (Cat B) POLITO, DIASP, giulio.romeo@polito.it 14/64

15 Structural design & analysis SOLAR HALE UAV Conformal fuselage Leading edge wing-box Horizontal Tail POLITO, DIASP, 15/64

16 Structural design & analysis SOLAR HALE UAV Maximum fuselage deflection:29mm Load factor = 4.5 Maximum wing deflection: 5.89m Load factor = 4.5 POLITO, DIASP, giulio.romeo@polito.it 16/64

17 Linear Flutter Analysis Non-linear effect due to high-aspect ratio structure is not included in a 1st attempt. No critical speed detected up to 100m/s (at 17000m). Normative requirement fulfilled. V-g diagram 1 st linear mode 2 nd linear mode SOLAR HALE UAV POLITO, DIASP, giulio.romeo@polito.it 17/64

18 Flight Dynamic of Flexible Aircraft SOLAR HALE UAV Waszak and Schmidt (1988) performed in the Visual and Motion Simulator facility at NASA Langley Research Center Tuzcu & Meirovitch Virginia Polytechnic institute 2003 POLITO, DIASP, 18/64

19 PRELIMINARY RELIABILITY SOLAR HALE UAV The platform has to have a very long endurance of flight ( h) is supposed to fly continuously without failure the loss of a platform must not cause damage to the service. Catastrophic failure conditions must be extremely improbable, i.e.: The probability that a failure condition would occur maybe assessed on the order of 10-9 or less. The safety standard that should be maintained is one in which UAVs are operated as safely as manned aircraft, insofar as they should not present or create a hazard to persons or properties in the air or on the ground greater than that created by manned aircraft conducting similar operations (FAA Advisory Circular 8/5/96). A MTBF=40000h for each motor and a MTBF=100000h for each propeller is assumed for the reliability analysis obtaining a POLITO, DIASP, giulio.romeo@polito.it 19/64

20 OBW-02 concept EXTERNAL VIEW BLENDED HALE UAV (ONERA) 20/64

21 OBW-02 concept External & internal views Max. fuel capacity : 2800 kg Sensors fairings Fuel systems & Air conditioning Phase array SATCOM antenna Flight control systems & complementary equipment BLENDED HALE UAV (ONERA) Payload units Fuel tanks Reference area: 51.3 m² Aspect ratio: 18 Wing loading : kg/m² Max LD ratio (M=0.6): 32 MMO: EO/IR sensor SAR antenna RR/Williams FJ44 2E engine 21/64

22 OBW-02 concept Performance & 4 Flying qualities 3 Main performance (ONERA & IAI) Initial climb altitude: ft, achieved in 20 min hold: 1 h at ft loiter: 24 h at ft loiter alt. reached during cruise segment (climbing cruise) Overall fuel consumption: 2628 kg Service ceiling reached in 1h33 Overall mission duration: 29 h Take off distance: 542 m (obs( obs.. 35 ft) BFL: 655 m Landing distance: 610 m Best RoC at SL: 28 m/s (at 138 m/s TAS) g ) ) (k (k tt W eigh eigh )) N /s /s g / (k / (k C S F Lift Lift (Cl) Drag (Cd)*100 L/D ratio // Time (h) (h) Time (h) (h) 2.5 x Time (h) (h) M ach ach 2 x Range (km) Altitude (m) Time (h) (h) 2 x Drag (N) (N) Available Thrust (N) (N) Time (h) (h) Time (h) (h) BLENDED HALE UAV (ONERA) 22/64

23 Performance & Flying qualities Flying qualities (ONERA & WUT) Computation of short period, dutch roll, phygoïd and spiral motions Vehicle doesn t t satisfy requirements for Dutch roll mode OBW_2 fulfils FAR 25 and MIL-F-8785C at (level 3) Does not fulfill FAR 23 and MIL-F-8785C at (level 2). Cannot be human manned in a backup -> > use of a robust automatic flight control damping (ξ) & frequency (η) coefficients [1/s] OBW_2; H=19 km; W=6000 kg Spiral & Phugoid: λ=ξ+/ ηi, where i=sqrt(-1) 0 η PHUGOID ξ SPIRAL ξ PHUGOID Flight speed [m/s] OBW_2; H=19 km; W=6000 kg Dutch Roll: ζd =ξ/ sqrt(ξ2+η2), ω nd =sqrt(ξ2+η2) 1.6 damping ratio (ζ d ) & undamped frequency (ω nd ) BLENDED HALE UAV (ONERA) ω nd Flight speed [m/s] ζd 23/64

24 Aerodynamic analysis BLENDED HALE UAV (ONERA) 24/64

25 Safety & Reliability BLENDED HALE UAV (ONERA) 25/64

26 Structural design & analysis BLENDED HALE UAV (ONERA) 26/64

27 OBW-02 concept BLENDED HALE UAV (ONERA) 27/64

28 PW114 Concept AN OVERALL DESCRIPTION BLENDED HALE UAV (WUT) Flying wing Overall AR: 17.7 MTOW: 6350 kg Wing area: 44.4 m 2 Wetted area: m 2 Wing loading: 143 kg/m 2 Engines: 2xWilliams FJ44-3, FJ44-4 in the future 28/64

29 Main Sensors EO/IR sensor SATCOM antenna Electronic racks BLENDED HALE UAV (WUT) Synthetic Aparture Radar Navigation system Parachute recovery system 29/64

30 Fly- by-wire or classical configuration? BLENDED HALE UAV (WUT) To reduce instability at the CG fixed one had to move the foreplane back dimensionless arm L H /c a Arm of CANARD versus Sc & a1 CANARD S c =2.16; a1=0.07 S c =1.50; a1=0.10 S c =2.16; a1=0.09 S c =2.16; a1=0.10 PW-111 S c =4.50; a1=0.10 Classical tailplane stability margin [% MAC] 30/64

31 Development HALE PW-11x Modification to improve longitudinal stability PW-111 PW-112 BLENDED HALE UAV (WUT) Further modification to improve longitudinal stability PW-114 PW-114 PW-113 Modification to improve lateral stability 31/64

32 Development HALE PW-11x BLENDED HALE UAV (WUT) 32/64

33 0.1 EILAT, May 18-19th 2005 HALE - Wing section 0.2 Global Hawk LRT-17.5 BLENDED HALE UAV (WUT) LRT-17.5: (t/c) max =17.5%, M des =0.62 Re des =1.5*10 6, C l des = C p - 1 supersonic zone sonic line transition recovery region Thickness limitation DTE clos ure x/c 33/64

34 Flaps, spoilers,, elevons BLENDED HALE UAV (WUT) 34/64

35 1.20 EILAT, May 18-19th 2005 Longitudinal trimming PW-114; H=19,5 km; Ma=0.6 BLENDED HALE UAV (WUT) C L δ elevon =0 o δ elevon = -10 o δ elevon = -11 o BEGINING OF THE PATROL C M PW-114; H=19,5 km; Ma=0.6 δ elevon = -15 o δ elevon =8 o 0.40 END OF THE PATROL 0.20 δ elevon = -15 o 0 2 α 4 6 END OF THE PATROL δ elevon = -8 o δ elevon = -10 o δ elevon =0 o BEGINING OF THE PATROL δ elevon = -11 o α /64

36 Fuel system BLENDED HALE UAV (WUT) Tank I Tank II Tank III Tank IV I:2000 l II:1500 l III:1400 l IV:700 l Σ=5600 l = 4200 kg Order of empting: I,IV,II,III 36/64

37 Wing torque box EILAT, May 18-19th 2005 Wing structure BLENDED HALE UAV (WUT) Carbon rowing Sandwich cover 37/64

38 Torsion box section BLENDED HALE UAV (WUT) Mass [kg] % m1 0,60 6,5 m2 3,17 34 m3 3,17 34 m4 0,59 6,5 m 5 0,87 9,5 5 m 6 Torsion box total 0,88 9, Weights of wing components torsion box with fuel ribs, nose and anti-icing icing installation control surfaces wingtip with brackets control surfaces consoles actuators fuel installation Whole wing [kg] x 140,8 = kg 4,5 % of max TOW 38/64

39 Structure of fuselage BLENDED HALE UAV (WUT) 39/64

40 Location and attachment Power unit Compact design Small interference drag Small assembly weight High efficiency of straight intakes Easy access & simply maintenance BLENDED HALE UAV (WUT) 40/64

41 PW114 main systems BLENDED HALE UAV (WUT) 41/64

42 Flutter Symmetric mode, fuel in wing only BLENDED HALE UAV (WUT) V kr = 100 m/s 42/64

43 PW114 & Global Hawk Comparison BLENDED HALE UAV (WUT) parameter Wing span [m] Wing area [m 2 ] Aspect ratio Empty weight [kg] Payload [kg] Fuel weight [kg] Take-off weight [kg] Take-off thrust [kn] Wing loading [kg/m 2 ] Thrust loading [kg/kn] Payload/wing area [kg/m 2 ] Payload/take-off off thrust [kg/kn] GH 35,4 50,2 25, ,5 314,1 19,9 27 PW ,4 17, , ,1 15,8 33,5 Payload/empty weight [kg/kg kg] /64

44 Aerodynamic comparison 1.6 CL BLENDED HALE UAV (WUT) 1.2 HALE modular, W=6000 kg CL=1.1, CD=0.0359, K= PW-113, W H=0 =4350 kg CL=0.8, CD=0.0270, K=29.6 (H=15km) Polar curve HALE modular (IAI) HALE BW - PW-113 (WUT) CD /64

45 Modular HALE - UAV A Multi-Role High-Altitude Long-Endurance Aircraft for Civil and Para-military Missions MODULAR HALE UAV (IAI) Modular twin jet aircraft concept (2 engines to improve reliability) Mission endurance --> > 24 hr at 1000km range 500 kg interchangeable payload bay (The modular concept) Payload power 8kW MAX ft MAX ceiling altitude MAX Cruise speed 0.65 MACH at 60kft 45/64

46 Configuration Features MODULAR HALE UAV (IAI) 46/64

47 Requirements Performance requirements (Starting point) MODULAR HALE UAV (IAI) 47/64

48 3 views Drawing MODULAR HALE UAV (IAI) 48/64

49 Structural design MODULAR HALE UAV (IAI) 49/64

50 Fuselage MODULAR HALE UAV (IAI) 50/64

51 Aerodynamic analysis By WUT body MODULAR HALE UAV (IAI) meshed body: 7386 body panels 51/64

52 Wing structure concept MODULAR HALE UAV (IAI) 52/64

53 Wing structure analysis FEM ANALYSIS BY POLITO MODULAR HALE UAV (IAI) DISPLACEMENT RESULTS WING BOX BUCKLING 53/64

54 Avionics system MODULAR HALE UAV (IAI) 54/64

55 Communication system MODULAR HALE UAV (IAI) 55/64

56 Payload MODULAR HALE UAV (IAI) 56/64

57 Payload MODULAR HALE UAV (IAI) 57/64

58 Conclusion & Recommendations HALE UAV 58/64

59 Conclusion&recommendations HALE UAV 59/64

60 Conclusion & Recommendations HALE UAV 60/64

61 Conclusion&recommendations HALE UAV 61/64