1. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System 2008 Unmanned Aerial System Team RQ-5A/MQ-5B Hunter 1 st Team 2008. 11. 24

2. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System Introduction Analysis Conclusion Concept of Operations Concept of Operations Requirements Requirements Air vehicle analysis Air vehicle analysis Sub-system analysis Sub-system analysis electric analysis electric analysis performance analysis performance analysis weight analysis weight analysis

3. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System C - Transport D - Decoy E - Special Electronics, Communication G - Surface Attack I - Interception (air or space) L - Launch Detection M - Scientific Measurements, Calibration N - Navigation Q - Drone, UAV R - Reconnaissance S - Space Operations Support T - Training U - Underwater Attack W - Weather C - Transport D - Decoy E - Special Electronics, Communication G - Surface Attack I - Interception (air or space) L - Launch Detection M - Scientific Measurements, Calibration N - Navigation Q - Drone, UAV R - Reconnaissance S - Space Operations Support T - Training U - Underwater Attack W - Weather R Q - 5 A Vehicle Purpose B – Booster M - Guided Missile, Drone, UAV N - Probe R - Rocket Q - UAV S - Satellite B – Booster M - Guided Missile, Drone, UAV N - Probe R - Rocket Q - UAV S - Satellite Type Of Vehicle Type Concept of Operation Division and Corps Level reconnaissance, surveillance, Target acquisition, and battle damage assessment

4. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System General Characteristics Information gathering with day/night capability Observation and Reconnaissance Target Acquisition - Artillery Adjustment Damage assessment Support to civil missions Able to perform following missions scenarios Designed according to standards Range > 100 km Endurance up to 11 hours Low noise signature IMINT Payload 2nd generation (TV-FLIR) Unprepared terrain take off and landing Automatic Take Off and Landing System Integrated in existing Armed Forces Infrastructure (Vehicles / Coms) Transportable (Air, Train, C130, …) Minimum personnel required for operations Data link according to requirements Airworthiness : safety oriented Requirements

5. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System Introduction Conclusion Analysis Air vehicle analysis Air vehicle analysis Sub-system analysis Sub-system analysis electric analysis electric analysis weight analysis weight analysis performance analysis performance analysis

6. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System RQ-5AMQ-5B 비고 길이 (ft) 22.623 0.4 증가 날개길이 (ft) 29.234.25 5.05 증가 GTOW(lb)16201800 180 증가 RQ-5A

7. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System RQ-5A MQ-5B 7.4ft 3,27ft 1.95ft 10.9ft ARTaper ratiot/c ratioSrefSref_expSwet_wing RQ-5A10.50.60.18781.174.72149.44 MQ-5B120.60.18797.8391.45182.9 10.9ft 12.45ft Main Wing Model

8. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System 1.95ft 7.79ft 9.35ft 0.39ft 3.43ft 0.64ft 1.47ft KhtKvtShtSvtSwet_tail RQ-5A 0.230.15 18.1412.2883.75 MQ-5B21.8814.8197.28 9.75ft Tail Wing Model RQ-5A MQ-5B

9. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System 2.45ft 1.71ft 1.223ft 0.49ft 14.02ft 1.95ft 2.45ft 1.4ft 60deg Swet_fuse Swet_a ( 반구 ) Swet_b ( 원판 및 기둥 ) Swet_fuselage RQ-5A, MQ-5B 80.853.089.4193.34 SwetGTOW/SrefSwet/Sref RQ-5A345.3819.984.26 MQ-5B392.3218.404.01 형상 parameter Fuselage Model

10. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System  Wetted Aspect Ratio(b^2/Swet) - RQ-5A : 약 2.5 -> (L/D)max = 14.5 추정 - MQ-5B : 약 3.2 -> (L/D)max = 15.5 추정 (fig3.6 참조 )  Maximum Lift to Drag Estimation i) Oswald factor (e) : fig5.18 of Anderson, Aeronamics - RQ-5A : taper ratio(= 0.6) and AR(= 10) -> δ = 0.03, e=1/(1+ δ)=0.97 - MQ-5B : taper ratio(= 0.6) and AR(= 12) -> δ = 0.04, e=1/(1+ δ)=0.96 ii) (L/D)max : Let, Cfe = 0.0045(Light aircraft-twin engine) - Cd = 2*Cd 0 = 2*Cfe*(Swet/Sref), Cl = sqrt(π*AR*e*Cd 0 ) - RQ-5A : Cd = 0.0383, Cl = 0.783 ⇒ (L/D)max = 약 20.4 - MQ-5B : Cd = 0.0361, Cl = 0.808 ⇒ (L/D)max = 약 22.4  상대적으로 큰 AR 과 Oswald factor 로 인해 fig3.6 에 맞지 않는 것으로 판단 Wetted Area, Maximum Lift to Drag

11. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System MOSP Multi-mission Optronic Stabilized Payload - TV camera/FLIR - Laser Rangefinder - Designator SAR Synthetic Aperture Radar MTI Moving Target Indicator LN-251 GPS Inertial Navigation System Viper Strike - Only on MQ-5B

12. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System Manned by two operators Tactical mission planning 1 GCS Control 1 or 2 air vehicles Control 1 or 2 air vehicles Control the air vehicle & its payload

13. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System Manufacturer : Moto guzzi engine Type : 2 Stroke I.C(Internal Combustion) Power : 60 HP / 45KW Engines : 2 engines (60 x 2 = 120 HP) Fuel type : MOGAS Propulsion(Engine)

14. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System Given values –BHP0 : 60HP –Max fuel weight : 421LB –Displacement : 750 cc (46 in³) –Cruise speed: 70knot –Cruise altitude : 15,000 ft Assume –Propeller efficiency(np) : 0.8 –15% Fuel fraction for take off and climb –5% Fuel fraction for landing reserve –Installation factor : 1.4 –Take off speed = 89.4 knot –Cruise at 75% take off power Engine weight –BHP0/Displacement = BHP0/LB= 1.3 –Engine weight = 60HP * 1.3 = 78.3 LB –Installed engine weight = (78.3 * 1.4 ) * 2 = 219.14LB Propulsion

15. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System General Values –Wfdot0 = 421/12 = 35 pph –SFC 0 = 0.58 For takeoff and climb For cruise(loiter) Value1 engine2 engineFormular BHP060HP120HP Fuel consumption31.5LB63.15LBTotal fuel * FF (421 * 0.15) T0312.576LBF625.152LBF325.6 * BHP0 *Np/ V(KTAS) Value1 engine2 enginesFormular Air density ratio ( σ) 0.63 δ / θ = 0.564/0.896 BHP34.8HP70HPBHP0*(8.55*σ-1)/7.55 Fuel consumption168LB336LBTotal fuel * FF 421LB * 0.8 Ta129.54LBF302LBF325.6 * BHP0 *Np/ V(KTAS) Wfdotcr15.27pph30.61pph168LB/11hr SFCcr0.439 10.9pph / 34.8 HP Propulsion

16. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System Coefficient (general av.) MultiplierEmpty Weight RQ-5AMQ-5BRQ-5AMQ-5B Wing2.574.7291.45186.8228.63 Horizontal tail218.1421.8836.2843.76 Vertical tail212.2814.8124.5629.62 Fuselage1.493.34 130.676 Landing gear0.0571620180092.34102.6 Installed Engine1.4155.6 219.14 All-else0.116201800162180 total 851.8934.42  Payload Weight = 200lb, Fuel Weight = 421lb(Motto Guzzi) - Assumed that Miscellaneous Weight is 100lb - Empty + Miscellaneous Weight : RQ-5A = 952lb, MQ-5B = 1034lb  Cost Estimation - Assumed $150/lb(empty weight) $127,770 Empty Weight Estimation

17. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System W0given1620Swet345.38 Cd2*0.0045(Swet/Sref)0.04Sref81.10 Cl0.78Swet/Sref4.26 BHPBHP0*(8.55*(dencity)-1)/7.5569.61Endurance12 hr BHP0given120.00Max fuel421.00 (L/M)maxCl/Cd20.40Vtosqrt{(W3/Sref)/Clto/0.00339}89.40 Cfegiven0.0045Vcrgiven70 delta0[δ](1-(6.875586*h/1000))^5.2559120.56Vsgiven53 theta0[θ]1-(1.9812*h/288.18)0.90h(Kft)given15 Densitydelta0[δ]/theta0[θ]0.63VliftVs*1.158.3 Ta325.6*BHP*Np/V(KTAS)259.04FFWf/W00.25988 Wfdot(pph)LB/HR35.08Bhp0/W0 0.07407 Given Data

18. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System 3 4 18 19 initial dataTake Off Value Wf-stto[(20*0.1+1)/60]*Bhp/W0*SFC0*W01.754166667 Start climb weight W3 1618 Climb starts speed (Clto)(L/D)max*Cd0.73644 SFC0WdotF/Hp0.29 Start ClimbValue Vclimb1Vto*1.689151.00kts D(Drag)W/(L/D)max79.41lb Ta(Thrust)325.6*BHP*Np/V(KTAS)311.03lb VvV*(Ta-D)/W10.02fps WdotFLB/HR35.08pph SFCWdotF/Hp0.50 ROC(Rate of Climb)V*(Ta-D)/W*60.032601.47fpm TTC(Time to Climb)h/ROC24.94min 15kft Climb endValue Vclimb2Wclimb1/sqrt(density)239.97kts Ta325.6*BHP*Np/V(KTAS)259.04pph KTASKTAS/sqrt(density)88.25 W4W3-WdotF*TTC/601603.66 DW/(L/D)max78.61lb SFCWdotF/Hp0.51 WdotFLB/HR = (420-63)/HR35.79pph Fuel consumption15% for takeoff and Climb63.15lb ROCV*(Ta-D)/W*60.032475.08fpm AverageValue Vclimb(Vclimb1+Vclimb2)/2195.49kts WdotF(LB/HR)/235.43pph ROC(V*(Ta-D)/W*60.032)/2538.27fpm TTCh/ROC27.87min DclimbVclimb*TTC/6090.79nm Cruise and Loiter Ta = D, L = W, SFC = constant initial data15Kft Cruise W4W3-WdotF*TTC/601601.79lb Vcr70Kts Reserve 5% fuel plus 1 hr loiter Landing weight(W19)W0-0.95*FF1220.05lb Rflo 144nm Fuel required to loiter 1hr Vlo 40Kts SFC 0.58 Raymer 3-2 Average of Cruise Range Rcr{V*(L/D)/SFC}*ln(Wi/Wj)674.91 Wi/W jexp[R*SFC/{V*(L/D)}]1.27 Endurance E{(L/D)/SFC}*ln(Wi/Wj)9.64 Wi/W jexp(E*SFC/LOD)1.327868852 RDclimb+Rcr765.70 WiWeights at the beginning1620 WjWeights at the end1220.05

19. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System Introduction Conclusion Analysis

20. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System Supporting OIF Operational deployments to Macedonia in support of KFOR in 99, 00, 01, 02 Systems in place at III CORPS (Ft Hood), XVIII ABN Corps (Ft Polk), Training Base (Ft Huachuca); V Corps Fielding in FY03 22 Payload / Sensor Demonstrations 31 Joint Readiness Training Cntr Exercises (JRTC) 4 NTC Rotations Lowest mishap rate of any U.S. owned UAV Demonstrated extended center wing with hard points to drop BAT submunition. 4 for 4 against moving armed target array at WSMR – Oct 02 Wing Span29.2 Feet Weight1620 Lbs Range144 nm Airspeed70 Kts cruise Altitude15,000 Ft Endurance8-12 Hours with EO / IR Primary Payload(s)EO / IR Launch / RecoveryUnimproved runway Characteristics / Description:  Fully Qualified System  Versatile Payload Platform  Multiple Mission Configurations  Only Army Extended Range / Endurance UAV  Stellar Overseas / NTC / JRTC Performance Capabilities:  Northrop-Grumman Corp Contractors: Hunter Flights Hours 7,835 28,565.0 728 3,967.8 OIFOIF Reported As Of: 23 March 2004:

21. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System

22. 1th UAS Team RQ-5A Hunter2008 Unmanned Air System