Content Requirements Mission profile Work Progress UCAVs and system survey Preliminary Design Comparison of the two final configurations

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2 Content Requirements Mission profile Work Progress UCAVs and system survey Existing UCAVs Armament Engines EO/IR sensors SAR Satellite comm. Avionics Aerial refueling Yaw Control Conceptual design RCS Definition of two configurations Initial Sizing Definition of required thrust Comparison of configurations with one/two engines Engine selection Weight Breakdown Airfoils Preliminary Design Landing gears Aerial refueling / Fuel lines Performance Layout Comparison of the two final configurations Configuration Selection Summary Second Semester Tasks

3 Requirements: Operation range of 2000 NM with refueling capability Armament carrying capability of 2x500[kg] smart bombs BVR (beyond visual range) Capability Stealth Capability Capability of carrying EO/IR sensors operating in all weather conditions, including night time target acquisition

4 Mission profile 1) Taxi To Runway 2) Warm-up 3) Takeoff 4) Climb to 36,000 ft 5) M=0.8 for 1,000 nm 6) 20 min loiter over target 7) M=0.8 for 500 nm 8) 10 min loiter for aerial refuel 9) Descend to S-L 10) Landing and Taxi. 1,000 nm 20 min 500nm 10 min ,000 ft

5 Mission Range 1500 NM Max Range 1000 NM Mission Radius 750 NM Combat Radius

6 Work Process Flow Chart

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8 UCAVs Survey X-47 A X-47 B Barracuda Neuron X-45 A X-45 C MQ-9 Weight [Lb] 5,500 7,100 13,000 12,200 10,000 Range [NM] unknown 3,200 unknown ,500 3,200 Ammunition Weight [Lb] 1, unknown 1,500 propulsion Turbo Fan Turbo Fan Turbo Fan Turbo Fan Turbo Fan Turbo Fan Turbo prop Stealth capability full full partial full full full low Status Active Demonstrator Prototype build completed Cancelled in Development Active Demonstrator cancelled operational

9 Armament Survey Main requirements: Minimum size (length and diameter) Maximum glide range High accuracy! " # $%&'" # () "() *+,-. /01 /01 /23 /23' " +, ', ,. 22!! 22!! /053 /053,&) : 9: ;77, <46%&= 052<46%&= ) + + # #

10 Armament Survey +! +() #4:! + +> +!!5+ +5

11 Propulsion Survey Turboprop Heron 2 Pratt & Whitney PT6 Reaper Honeywell TPE

12 X-45A Turbofan Honeywell F124-GA-100 X-47A Pratt & Whitney JT15D-5C X-47B Pratt & Whitney F

13 EO/IR sensors Survey Star SAFIR HD MX-15 True HD Sonoma 474 Toplite Manufacture FLIR WESCAM L-3 RAFAEL Weight(kg) TFU:45 CEU:10.4 Turret:46.72 MCU:9.07 Turret:86.4 Turret:59 Size[mm] 450x x394 Outside dia. 528 Endurance MIL-STD-810 MIL-STD [ c] MIL-STD-810 MIL-STD-461 MIL-STD-810 MIL-STD-461 MIL-STD-810 MIL-STD-461 Stabilization 6 axis LOS stabilization< 5urad 6 axis LOS stabilization< 6urad 5 axis LOS stabilization< 2urad 4axis LOS stabilization< 0.7mrad Resolution Day and night vision IR:1280x720 CCD:1280x720 yes IR:640x512 CCD:470TV lines yes IR:640x512 Not mentioned Not mentioned Not mentioned /A/ Laser Range[km] Not mentioned

14 EO/IR sensors Survey Selected Main requirements: Day & night detection ability Detection range: height: 10.67[km] (36,000 ft) horizontal range:9.75[km] (5.4 NM) Minimum decrease in stealth capability The EO sensor will be custom made to fit our configuration in a way that minimizes RCS increase. We will use the parameters of the selected alternative.

15 SAR Survey model "Honeywell" "EL/M- 2055D" "EL/M- 2055DX" SANDIA- MiniSAR" Range 35 Km 50 Km Frequency [GHz] Power[W] Weight[Kg] Honeywell EL/M-2055D EL/M-2055DX SANDIA-MiniSAR

16 Satellite Communication Survey Model Angle coverage[deg] Frequency [GHz] Gain[dB] Weight[Kg] "Gimbaled" "MIJET" "MIJETLite" "MiniMIJET" (each side)

17 Avionics Selection GPS/INS model: LN-100G. Lightweight, High MTBF, Low power consumption, Military proven hardware. Receiver/Transmitter model: ARC-210. C96; C65691$; Provides services for both the Ku and the C band antennas, Resistant to jamming. Identification Transponder model: APX-. Small ; (limited to line of sight-uhf). B 280x180x x145x x120x210 C-band antenna model: ANT5812SN. Small, Lightweight, Low power consumption. 210x180x45

18 Aerial Refueling Survey Two approaches: 1. Hose & Drogue Does not require an operator for the hose. Simultaneous refuel of several crafts capability. 2. Boom & Receptacle Does not require a drogue which sticks out of the receiving aircraft. Easy to make contact to refuel (boom operator s job). The boom is rigid and less susceptible to wind perturbations. The mass fuel flow is greater.

19 Yaw control Survey Control method Picture Yaw moment created by Pros Cons Forward opening spoilers Upper spoilers with inclination opening forward Very low RCS increment Few information about this control method Crowmixing Two elevons open in opposite directions Light weight High coupling with roll Spoilers Upper and lower spoilers High moment High RCS increment Splitters Control surface splits Low RCS increment Thrust vectoring Change of thrust direction Low dependence of flight speed Complexity High weight

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21 RCS (Radar Cross Section) The RCS is mostly affected by: Radome Cavities Leading edges Flat sides of fuselage Corner reflection Surface currents that scatter at discontinuity Protruding elements

22 There are several ways to reduce RCS Minimize reflecting directions Use of special weapons bays Upper and curved intake to conceal the engine compressors facing Slanted/without vertical stabilizer Use of Radar Absorbing Materials

23 Definition of two configurations The design will be based on a flying wing configuration. We simultaneously developed two configurations : Zigzag configuration Delta configuration

24 Configuration and Airfoils Flying wing configuration was selected to meet stealth requirements Advantages: High fuel efficiency (high L/D) Light weight (Less materials required ) Low drag Disadvantages: Lateral and longitudinal instabilities Loss of lift due to elevator deflections Difficulty to create pitching moment Therefore special care should be applied for the stability margin Recommended approach: Use of reflex or reverse camber

25 Initial size estimation Assumption of L/D Calculation of fuel fracture required for the mission for given L/D Relation between empty and take-off weight L/DCalculation of from drag polar Based on take-off weight Comparison withother UCAV s Yields take-off weight This is an iterative method which stops with the convergence of take-off weight

26 Initial size estimationfor the two configurations Thrust required: 5700 [Lb]!"#$%$& ' ( )* +#$, -. +#, *+ *, The two configurations have the same take-off weight however the delta carries more fuel. Assuming Thrust/Weight of 0.38 (average of other UCAV s) we will need an engine that gives 5700 [Lb] thrust.

27 Comparison between single and twin engine configuration Comparison parameters single engine configuration Twin engines configuration Engine model P&W pw306a P&W JT15-5D Volume 932[lit] 2x563.5=1127[lit] Weight 1043[lb] 2x627=1254[lb] Thrust 6400[lb] 2x3045=6090[lb] TSFC 0.394[lb/hr/lb] 0.55[lb/hr/lb] Redundancy One engine Two engines Accompanying system weight 330[lb] 430[lb] Inlet Weight 150[lb] 310[lb] Inlet Area 4[ft^2] 4.5[ft^2] Nozzle Weight 21[lb] 30[lb] Nozzle Area 2.7[ft^2] 3[ft^2]

28 Engine Model P&W pw306a Honeywell AS907 CFE B Povazske DV-2A Rolls Royce Adour MK871 Thrust 6400 [lb st] 6500 [lb st] 5725 [lb st] 5693 [lb st] 6030 [lb st] Weight 1043 [lb] 1364 [lb] 1325 [lb] 1389 [lb] 1330 [lb] Length 75.6 [in] 90 [in] 99 [in] 68 [in] 76.7 [in] Fan diameter TSFC [lb/hr/lb] 31.6 [in] 34.2[in] 34.4 [in] 25.4[in] 30.9 [in] 0.42 [lb/hr/lb] [lb/hr/lb] [lb/hr/lb] BPR

29 The selected engine is : P&W pw306a Thrust:6400 [lb st] Weight: 1043 [lb] Fan diameter: 31.6 [in] TSFC min:0.394 [lb/hr/lb] Conclusion: The selected engine has some advantages over the other engines Lightest engine Growth possibility One of the shortest engines Good TSFC

30 Weight Breakdown Component Delta Weight [lb] Wing Fuselage Engine 1043 Air induct Tailpipe 60.2 Nose landing gear Main landing gear Propulsion system Fuel system Hydraulics Electrical system Avionics Flight control ECS + Anti-icing Handling gear 4.8 Total empty weight 8658 Zig-Zag Component Weight [lb] Wing Fuselage Engine 1043 Air induct Tailpipe 60.2 Nose landing gear Main landing gear Propulsion system Fuel system Hydraulics Electrical system Avionics Flight control ECS + Anti-icing Handling gear 4.8 Total empty weight 8973

31 Weight Breakdown 5 5; 8C C. G. 3.3% MAC X N 8.84% MAC C. G. 0 Rear X N 5.54% MAC C. G. 0 Forward Component Weight [lb] Location [ft] Wing Fuselage Engine Air induct Tailpipe Nose landing gear Main landing gear Propulsion system Fuel Aerial refuel Hydraulics Electrical system Avionics Flight control Armament Misc (spread) Weight Reserve Rear C.G Forward C.G

32 Weight Breakdown 5 5;! C C. G. 0.7% MAC X N 4.6% MAC C. G. 0 Rear X N 5.3% MAC C. G. 0 Forward Component Weight [lb] Location [ft] Wing Fuselage Engine Air induct Tailpipe Nose landing gear Main landing gear Propulsion system Fuel Aerial refuel Hydraulics Electrical system Avionics Flight control Armament Misc (spread) Weight Reserve Rear C.G Forward C.G

33 Airfoil Selection MAX. CAMBER 1.75% at 16.3% 2.17% at 19.5% 1.54% at 27.2% MAX. THICKNESS 12.62% at 34.3% 12.86% at 33.4% 12.23% at 36.9% AIRFOIL EPPLER325 EPPLER326 EPPLER360

34 ;4:2 ;4:1 ;426

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36 Landing gears landing gears arrangement selection: Tricycle a4 M a Load limitations: M f 0.05 B 0.2 B a3 a1 a2 Criterion a1 [deg] a2 [deg] a3 [deg] a4 [deg] Ma/B Mf/B H [ft] Ma [ft] B [ft] Zig-zag Delta

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38 Aerial Refueling/Fuel Lines Selected system: Boom & Receptacle. The boom is standard and has a diameter of 200 mm which is derived using dimension analysis. The receptacle is of a unique design enabling it to grasp and detach the boom. # Fuel Lines? Fuel systems can be classified in two broad categories: 1. Gravity-Feed Systems. 2. Pressure-Feed Systems.

39 The fuel lines which carry the fuel from the receptacle to the fuel tanks can use the gravity feed approach. The fuel lines that carry fuel from the fuel tanks to the engine, however, have to utilize fuel pumps; (the fuel pumps are integral in the fuel tanks). Top View: D:66! D16! " - " D46 ; Refueling time calculation: For Zig-Zag : t=0.577[min]=35[sec] For Delta: t=0.667[min]=40[sec] Typical fuel pressure in fuel lines: P 20[ Psi]

40 Performance Analysis Takeoff distance: V V V S S TO TR CL 1 R ln W max 2 S TR R R hobsticle S C t V 0 V V TO ST V ST ST K TO 1 R TR C A 0 K T 2 2 gk A C S S S S S L S 2 TO For Delta configuration takeoff distance is 1.15km For Zig-Zag configuration takeoff distance is 1.22km

41 Performance Analysis Landing distance: V V V S app F TD a ST ST ST 2 2 S F R R hobsticle S S FR B V V V t V TD K ln K K V 2 g K T 2 T A TD S S S S S LF L a F FR B A For Delta configuration landing distance is 1.03km For Zig-Zag configuration landing distance is 1.19km

42 Performance Analysis Takeoff rotation: 1 2 WTO M a H VTO S ref X CP X e CG M rear a C L e e 2 S elevons C L 0.9 K e C l cos e e S ref C For Zig-Zag with e 0.1 elevon angle is 13.9 C C For Delta with e 0.13 elevon angle is 5.7 C

43 Performance Analysis Climb Rate: V ver V C W 2W S 3 T climb D0 K V W climb Vclimb W S 2 T climb T V 12CD0K 3 C W W D0 2 S Altitude [ft] Climb Rate [ft/min] Climb Velocity [kts] Mach Number 10, , , Altitude [ft] Climb Rate [ft/min] Climb Velocity [kts] Mach Number 10, , ,

44 Performance Analysis Flight envelopes: Delta Zig-Zag

45 LAYOUT Delta Configuration Development

46 Zig-Zag Zag Configuration Development

47 Delta Configuration

48 Zig-Zag Zag Configuration

49 Delta Animation

50 Zig-Zag Zag Animation

51 Delta interior components? - E7! # F%& ' F %???+ 7! ;G$% #7

52 Zig-Zag Zag interior components? - E7! # F%& ' F %???+ 7! ;G$% #7

53 Delta Section View Animation

54 Zig-Zag Zag Section View Animation

55 Configuration Comparison Category Zig-Zag Delta Weight 14,300 [lb] 14,460 [lb] Fuel weight 3,117 [lb] 3,600 [lb] AR Wing loading 30 [lbf/ft^2] 36 [lbf/ft^2] Engine P&W pw306a P&W pw306a Airfoil Eppler 360 Eppler 360 Flight ceiling 46,000 [ft] 40,000 [ft] Takeoff distance 1.22 [km] 1.15 [km] Takeoff rotation (elevon angle) Landing distance 1.19 [km] 1.03 [km] Aerial refueling time 35 [sec] 40 [sec] Climb rate (36,000 [ft]) 4869 [ft/min] 4606 [ft/min] Longitudinal stability Unstable Stable No. of reflecting surfaces (RCS) 2 3

56 Chosen Configuration

57 Summary Goal achievement: Operation range of 2000 NM with refueling capability Armament carrying capability of at least 2x500[kg] smart bombs BVR (beyond visual range) Capability Stealth Capability Capability of carrying EO/IR sensors operating in all weather conditions, including night time target acquisition

58 Second Semester Tasks Detail design and Analysis of: Wing structure Landing gear Control surfaces Flight control system Evaluation of RCS Wind tunnel test: Design of wind tunnel model Manufacture of wind tunnel model Conducting wind tunnel test

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