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1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
2008 Unmanned Aerial System2008 Unmanned Aerial System
Team RQ-5A/MQ-5B HunterTeam RQ-5A/MQ-5B Hunter
Pre-concept design Pre-concept design AnalysisAnalysis
11stst Team Team2008. 11. 242008. 11. 24
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
AgendaAgenda
IntroductionIntroduction
AnalysisAnalysis
ConclusionConclusion
• Concept of OperationsConcept of Operations
• RequirementsRequirements
• Air vehicle analysisAir vehicle analysis
• Sub-system analysisSub-system analysis
• electric analysiselectric analysis
• performance analysisperformance analysis
• weight analysisweight analysis
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
C - TransportD - DecoyE - Special Electronics, CommunicationG - Surface AttackI - Interception (air or space)L - Launch DetectionM - Scientific Measurements, CalibrationN - NavigationQ - Drone, UAVR - ReconnaissanceS - Space Operations SupportT - TrainingU - Underwater AttackW - Weather
R Q - 5 AR Q - 5 A
Vehi
cle
Pur
pose
Vehi
cle
Pur
pose
B – BoosterM - Guided Missile, Drone, UAVN - ProbeR - RocketQ - UAVS - Satellite
Type
Ty
pe
Of
Vehi
cle
Of
Vehi
cle
Concept of OperationConcept of Operation
Division and Corps Level reconnaissance, surveillance, Division and Corps Level reconnaissance, surveillance, Target acquisition, and battle damage assessmentTarget acquisition, and battle damage assessment
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
General CharacteristicsGeneral 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 scenariosAble 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
RequirementsRequirements
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
AgendaAgendaIntroductionIntroduction
ConclusionConclusion
AnalysisAnalysis• Air vehicle analysisAir vehicle analysis• Sub-system analysisSub-system analysis• electric analysiselectric analysis• weight analysisweight analysis• performance analysisperformance analysis
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
RQ-5A MQ-5B 비고
길이 (ft) 22.6 23 0.4 증가
날개길이(ft) 29.2 34.25 5.05 증가
GTOW(lb) 1620 1800 180 증가
RQ-5ARQ-5A
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
RQ-5A
MQ-5B
7.4ft
3,27ft
3,27ft1.95ft
1.95ft
10.9ft
AR Taper ratio t/c ratio Sref Sref_exp Swet_wing
RQ-5A 10.5 0.6 0.187 81.1 74.72 149.44MQ-5B 12 0.6 0.187 97.83 91.45 182.9
10.9ft
12.45ft
Main WingMain Wing ModelModel
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
1.95ft
7.79ft
9.35ft0.39ft 0.39ft
3.43ft
0.64ft1.47ft
Kht Kvt Sht Svt Swet_tail
RQ-5A0.23 0.15
18.14 12.28 83.75
MQ-5B 21.88 14.81 97.28
9.75ft
Tail Wing ModelTail Wing Model
RQ-5A MQ-5B
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
2.45ft
1.71ft
1.223ft0.49ft
14.02ft1.95ft2.45ft
1.4ft
60deg
Swet_fuse Swet_a( 반구 )
Swet_b( 원판 및 기둥 ) Swet_fuselage
RQ-5A,MQ-5B 80.85 3.08 9.41 93.34
Swet GTOW/Sref Swet/SrefRQ-5A 345.38 19.98 4.26MQ-5B 392.32 18.40 4.01
• 형상 parameter
Fuselage ModelFuselage Model
1th UAS Team RQ-5A Hunter 2008 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*Cd0 = 2*Cfe*(Swet/Sref), Cl = sqrt(π*AR*e*Cd0)
- 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 DragWetted Area, Maximum Lift to Drag
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
PayloadPayload
MOSPMOSP
Multi-mission Optronic Stabilized Payload
- TV camera/FLIR- Laser Rangefinder- Designator
SARSARSynthetic Aperture Radar
MTIMTIMoving Target Indicator
LN-251 GPSLN-251 GPS
Inertial Navigation System
Viper StrikeViper Strike
- Only on MQ-5B
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
GCS 3000GCS 3000
Manned by two operatorsManned by two operatorsTactical mission planningTactical mission planning
1 GCS 1 GCS
Control 1 or 2 air vehiclesControl 1 or 2 air vehicles
Control the air vehicleControl the air vehicle& its payload& its payload
1th UAS Team RQ-5A Hunter 2008 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)Propulsion(Engine)
1th UAS Team RQ-5A Hunter 2008 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
PropulsionPropulsion
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
• General Values– Wfdot0 = 421/12 = 35 pph– SFC 0 = 0.58
• For takeoff and climb
• For cruise(loiter)
Value 1 engine 2 engine FormularBHP0 60HP 120HPFuel consumption 31.5LB 63.15LB Total fuel * FF (421 * 0.15)T0 312.576LBF 625.152LBF 325.6 * BHP0 *Np/ V(KTAS)
Value 1 engine 2 engines FormularAir density ratio(σ) 0.63 0.63 δ/θ= 0.564/0.896
BHP 34.8HP 70HP BHP0*(8.55*σ-1)/7.55Fuel consumption 168LB 336LB Total fuel * FF
421LB * 0.8Ta 129.54LBF 302LBF 325.6 * BHP0 *Np/ V(KTAS)Wfdotcr 15.27pph 30.61pph 168LB/11hrSFCcr 0.439 0.439 10.9pph / 34.8 HP
PropulsionPropulsion
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
Coefficient(general av.)
Multiplier Empty Weight
RQ-5A MQ-5B RQ-5A MQ-5B
Wing 2.5 74.72 91.45 186.8 228.63
Horizontal tail 2 18.14 21.88 36.28 43.76
Vertical tail 2 12.28 14.81 24.56 29.62
Fuselage 1.4 93.34 93.34 130.676 130.676
Landing gear 0.057 1620 1800 92.34 102.6
Installed Engine 1.4 155.6 155.6 219.14 219.14
All-else 0.1 1620 1800 162 180
total 851.8 934.42 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 EstimationEmpty Weight Estimation
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
W0 given 1620 Swet 345.38
Cd 2*0.0045(Swet/Sref) 0.04 Sref 81.10
Cl 0.78 Swet/Sref 4.26
BHP BHP0*(8.55*(dencity)-1)/7.55 69.61 Endurance 12 hr
BHP0 given 120.00 Max fuel 421.00
(L/M)max Cl/Cd 20.40 Vto sqrt{(W3/Sref)/Clto/0.00339} 89.40
Cfe given 0.0045 Vcr given 70
delta0[δ] (1-(6.875586*h/1000))^5.255912 0.56 Vs given 53
theta0[θ] 1-(1.9812*h/288.18) 0.90 h(Kft) given 15
Density delta0[δ]/theta0[θ] 0.63 Vlift Vs*1.1 58.3
Ta 325.6*BHP*Np/V(KTAS) 259.04 FF Wf/W0 0.25988
Wfdot(pph) LB/HR 35.08 Bhp0/W0 0.07407
Given DataGiven Data
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
Performance AnalysisPerformance Analysis
3
4 18
19
initial data Take Off Value
Wf-stto [(20*0.1+1)/60]*Bhp/W0*SFC0*W0 1.754166667
Start climb weight W3 1618
Climb starts speed (Clto) (L/D)max*Cd 0.73644
SFC0 WdotF/Hp 0.29
Start Climb Value Vclimb1 Vto*1.689 151.00 ktsD(Drag) W/(L/D)max 79.41 lb
Ta(Thrust) 325.6*BHP*Np/V(KTAS) 311.03 lbVv V*(Ta-D)/W 10.02 fps
WdotF LB/HR 35.08 pphSFC WdotF/Hp 0.50
ROC(Rate of Climb) V*(Ta-D)/W*60.032 601.47 fpmTTC(Time to Climb) h/ROC 24.94 min
15kft Climb end Value Vclimb2 Wclimb1/sqrt(density) 239.97 kts
Ta 325.6*BHP*Np/V(KTAS) 259.04 pphKTAS KTAS/sqrt(density) 88.25
W4 W3-WdotF*TTC/60 1603.66 D W/(L/D)max 78.61 lb
SFC WdotF/Hp 0.51 WdotF LB/HR = (420-63)/HR 35.79 pph
Fuel consumption 15% for takeoff and Climb 63.15 lbROC V*(Ta-D)/W*60.032 475.08 fpm
Average Value
Vclimb (Vclimb1+Vclimb2)/2 195.49 kts
WdotF (LB/HR)/2 35.43 pph
ROC (V*(Ta-D)/W*60.032)/2 538.27 fpm
TTC h/ROC 27.87 min
Dclimb Vclimb*TTC/60 90.79 nm
Cruise and Loiter
Ta = D, L = W, SFC = constant
initial data 15Kft Cruise
W4 W3-WdotF*TTC/60 1601.79 lb
Vcr 70 Kts
Reserve 5% fuel plus 1 hr loiter
Landing weight(W19) W0-0.95*FF 1220.05 lb
Rflo 144 nm
Fuel required to loiter 1hrVlo 40 Kts
SFC 0.58 Raymer 3-2
Average of Cruise
Range Rcr {V*(L/D)/SFC}*ln(Wi/Wj) 674.91
Wi/W j exp[R*SFC/{V*(L/D)}] 1.27
Endurance E {(L/D)/SFC}*ln(Wi/Wj) 9.64
Wi/W j exp(E*SFC/LOD) 1.327868852
R Dclimb+Rcr 765.70
Wi Weights at the beginning 1620
Wj Weights at the end 1220.05
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
AgendaAgenda
IntroductionIntroduction
ConclusionConclusion
AnalysisAnalysis
1th UAS Team RQ-5A Hunter 2008 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 Span
29.2 FeetWeight
1620 LbsRange
144 nmAirspeed
70 Kts cruiseAltitude
15,000 FtEndurance
8-12 Hours with EO / IRPrimary Payload(s)
EO / IRLaunch / Recovery
Unimproved 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:
HunterFlights
Hours
7,835
28,565.0
728
3,967.8
OIF
Reported As Of:23 March 2004:
SpecificationSpecification
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System
1th UAS Team RQ-5A Hunter 2008 Unmanned Air System