1th uas team rq-5a hunter2008 unmanned air system 2008 unmanned aerial system team rq-5a/mq-5b...

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 Team

2008. 11. 242008. 11. 24


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


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

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

Veh

icle

Pu

rpo

seV

ehic

le P

urp

ose

Veh

icle

Pu

rpo

seV

ehic

le P

urp

ose

B – BoosterM - Guided Missile, Drone, UAVN - ProbeR - RocketQ - UAVS - Satellite

B – BoosterM - Guided Missile, Drone, UAVN - ProbeR - RocketQ - UAVS - Satellite

Typ

e T

ype

Of

Veh

icle

Of

Veh

icle

Typ

e T

ype

Of

Veh

icle

Of

Veh

icle

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


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


AgendaAgenda



AnalysisAnalysis

• Air vehicle analysisAir vehicle analysis• Sub-system analysisSub-system analysis• electric analysiselectric analysis• weight analysisweight analysis• performance analysisperformance analysis


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


RQ-5ARQ-5A

MQ-5BMQ-5B

7.4ft

3,27ft

3,27ft1.95ft

1.95ft

10.9ft

ARTaper ratio

t/c ratio Sref Sref_exp Swet_wing

RQ-5A 10.5 0.6 0.187 81.1 74.72 149.44

MQ-5B 12 0.6 0.187 97.83 91.45 182.9

10.9ft

12.45ft

Main WingMain Wing ModelModel


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-5ARQ-5A MQ-5BMQ-5B


2.45ft

1.71ft

1.223ft0.49ft

14.02ft1.95ft

2.45ft1.4ft

60deg

Swet_fuseSwet_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/Sref

RQ-5A 345.38 19.98 4.26

MQ-5B 392.32 18.40 4.01

• 형상 parameter

Fuselage ModelFuselage Model


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


PayloadPayload

MOSPMOSP

Multi-mission Optronic Stabilized Payload

- TV camera/FLIR- Laser Rangefinder- Designator

SARSARSynthetic Aperture Radar

MTIMTI

Moving Target Indicator

LN-251 GPSLN-251 GPS

Inertial Navigation System

Viper StrikeViper Strike

- Only on MQ-5B


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


• 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)


• 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


• General Values– Wfdot0 = 421/12 = 35 pph– SFC 0 = 0.58

• For takeoff and climb

• For cruise(loiter)

Value 1 engine 2 engine Formular

BHP0 60HP 120HP

Fuel 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 Formular

Air density ratio(σ) 0.63 0.63 δ/θ= 0.564/0.896

BHP 34.8HP 70HP BHP0*(8.55*σ-1)/7.55

Fuel consumption 168LB 336LB Total fuel * FF421LB * 0.8

Ta 129.54LBF 302LBF 325.6 * BHP0 *Np/ V(KTAS)

Wfdotcr 15.27pph 30.61pph 168LB/11hr

SFCcr 0.439 0.439 10.9pph / 34.8 HP

PropulsionPropulsion


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


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 Vtosqrt{(W3/Sref)/Clto/

0.00339}89.40

Cfe given 0.0045 Vcr given 70

delta0[δ](1-(6.875586*h/

1000))^5.2559120.56 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


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 kts

D(Drag) W/(L/D)max 79.41 lb

Ta(Thrust) 325.6*BHP*Np/V(KTAS) 311.03 lb

Vv V*(Ta-D)/W 10.02 fps

WdotF LB/HR 35.08 pph

SFC WdotF/Hp 0.50 　ROC(Rate of Climb) V*(Ta-D)/W*60.032 601.47 fpm

TTC(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 pph

KTAS 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 lb

ROC 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 1hr

Vlo 　 40 Kts

SFC 　 0.58Raymer

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 　


AgendaAgenda



AnalysisAnalysis


• 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 hunter2008 unmanned air system 2008 unmanned aerial system team rq-5a/mq-5b...

Documents