2008 Unmanned Aerial System
Team RQ-5A/MQ-5B Hunter
Pre-concept design
Analysis
1st Team
2008. 11. 24
1th UAS Team RQ-5A Hunter
2008 Unmanned Air System
Agenda
Introduction
• Concept of Operations
• Requirements
Analysis
• Air vehicle analysis
• Sub-system analysis
• electric analysis
• performance analysis
• weight analysis
Conclusion
1th UAS Team RQ-5A Hunter
2008 Unmanned Air System
Concept of Operation
Division and Corps Level reconnaissance, surveillance,
Target acquisition, and battle damage assessment
Type
Of Vehicle
Vehicle Purpose
RQ-5A
1th UAS Team RQ-5A Hunter
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
B – Booster
M - Guided Missile, Drone, UAV
N - Probe
R - Rocket
Q - UAV
S - Satellite
2008 Unmanned Air System
Requirements
Able to perform following missions scenarios
• Information gathering with day/night capability
• Observation and Reconnaissance
• Target Acquisition - Artillery Adjustment Damage assessment
• Support to civil missions
General Characteristics
• Designed according to standards
• Automatic Take Off and Landing System
• Range > 100 km
• Integrated in existing Armed Forces Infrastructure
• Endurance up to 11 hours
(Vehicles / Coms)
• Low noise signature
• Transportable (Air, Train, C130, …)
• IMINT Payload 2nd generation (TV-FLIR)
• Minimum personnel required for operations
• Unprepared terrain take off and landing
• Data link according to requirements
• Airworthiness : safety oriented
1th UAS Team RQ-5A Hunter
2008 Unmanned Air System
Agenda
Introduction
Analysis
•
•
•
•
•
Air vehicle analysis
Sub-system analysis
electric analysis
weight analysis
performance analysis
Conclusion
1th UAS Team RQ-5A Hunter
2008 Unmanned Air System
RQ-5A
1th UAS Team RQ-5A Hunter
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
180증가
2008 Unmanned Air System
Main Wing Model
RQ-5A
1.95ft
3,27ft
10.9ft
7.4ft
12.45ft
MQ-5B
1.95ft
3,27ft
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
149.44
MQ-5B
12
0.6
0.187
97.83
91.45
182.9
1th UAS Team RQ-5A Hunter
2008 Unmanned Air System
Tail Wing Model
MQ-5B
RQ-5A
9.75ft
9.35ft
0.39ft
0.39ft
1.95ft
7.79ft
Kht
3.43ft
RQ-5A
0.23
0.64ft
1.47ft
1th UAS Team RQ-5A Hunter
Kvt
MQ-5B
Sht
Svt
Swet_tail
18.14
12.28
83.75
21.88
14.81
97.28
0.15
2008 Unmanned Air System
Fuselage Model
1.71ft
0.49ft
1.223ft
60deg
14.02ft
1.95ft
2.45ft
2.45ft
RQ-5A,
MQ-5B
1.4ft
Swet_fuse
Swet_a
(반구)
Swet_b
(원판 및 기둥)
Swet_fuselage
80.85
3.08
9.41
93.34
• 형상 parameter
Swet
GTOW/Sref
Swet/Sref
RQ-5A
345.38
19.98
4.26
MQ-5B
392.32
18.40
4.01
1th UAS Team RQ-5A Hunter
2008 Unmanned Air System
Wetted Area, Maximum Lift to Drag
 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 (fig3.6참조)
 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 AR과 Oswald factor로 인해 fig3.6에 맞지 않는 것으로 판단
1th UAS Team RQ-5A Hunter
2008 Unmanned Air System
Payload
MOSP
Multi-mission Optronic
Stabilized Payload
- TV camera/FLIR
- Laser Rangefinder
- Designator
LN-251 GPS
Inertial Navigation System
1th UAS Team RQ-5A Hunter
SAR
Synthetic Aperture Radar
MTI
Moving Target Indicator
Viper Strike
- Only on MQ-5B
2008 Unmanned Air System
GCS 3000
Tactical mission planning
Manned by two operators
1 GCS
Control the air vehicle
& its payload
Control 1 or 2 air vehicles
1th UAS Team RQ-5A Hunter
2008 Unmanned Air System
Propulsion(Engine)
•
•
•
•
•
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
1th UAS Team RQ-5A Hunter
2008 Unmanned Air System
Propulsion
• 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
1th UAS Team RQ-5A Hunter
2008 Unmanned Air System
Propulsion
• General Values
– Wfdot0 = 421/12 = 35 pph
– SFC 0 = 0.58
• For takeoff and climb
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)
• For cruise(loiter)
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 * FF
421LB * 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
1th UAS Team RQ-5A Hunter
2008 Unmanned Air System
Empty Weight Estimation
Multiplier
Empty Weight
Coefficient
(general av.)
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
851.8
934.42
total
 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)
1th UAS Team RQ-5A Hunter
$127,770
2008 Unmanned Air System
Given Data
W0
given
1620
Swet
345.38
Cd
2*0.0045(Swet/Sref)
0.04
Sref
81.10
0.78
Swet/Sref
4.26
Cl
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
1th UAS Team RQ-5A Hunter
0.07407
2008 Unmanned Air System
Performance Analysis
Start Climb
Value
151.00
kts
Value
79.41
lb
1220.05
lb
Value
311.03
lb
1.754166667
144
nm
10.02
fps
195.49
kts
35.08 1618
pph
35.43
pph
0.50
40
Kts
0.73644 18
601.47
fpm
Raymer
538.27
fpm
1601.79
lb
0.58
24.94 0.29
min3-2
27.87
min
70
Kts
Value
674.91
90.79
nm
239.97
kts
1.27
19pph
259.04
9.64
88.25
Vclimb1
Vto*1.689
Reserve 5% fuel
plus 1 hr loiter
initial
data
Take
Off
Cruise
and Loiter
D(Drag)
W/(L/D)max
Landing weight(W19) Average
W0-0.95*FF
Ta(Thrust)
325.6*BHP*Np/V(KTAS)
Wf-stto
[(20*0.1+1)/60]*Bhp/W0*SFC0*W0
Ta
= D, L = W, SFC = constant
Rflo
Vv
V*(Ta-D)/W
Vclimb
(Vclimb1+Vclimb2)/2
Fuel required
to loiter 1hr
Start climb
weight W3
WdotF
LB/HR
WdotF
(LB/HR)/2
initial
15Kft
Cruise
SFCdata
WdotF/Hp
Vlo
Climb starts speed (Clto)
(L/D)max*Cd
4
ROC(Rate
of Climb)
V*(Ta-D)/W*60.032
ROC
(V*(Ta-D)/W*60.032)/2
W4
W3-WdotF*TTC/60
SFC
TTC(Time
to Climb)
h/ROC
SFC0
WdotF/Hp
TTC
h/ROC
Vcr
Average
of Cruise
15kft Climb end
Range
Rcr
{V*(L/D)/SFC}*ln(Wi/Wj)
Dclimb
Vclimb*TTC/60
Vclimb2
Wclimb1/sqrt(density)
Wi/W
exp[R*SFC/{V*(L/D)}]
Taj
325.6*BHP*Np/V(KTAS)
Endurance
{(L/D)/SFC}*ln(Wi/Wj)
KTAS E
KTAS/sqrt(density)
W4j
W3-WdotF*TTC/60
1603.66
Wi/W
exp(E*SFC/LOD)
1.327868852
W/(L/D)max
78.61
RD
Dclimb+Rcr
765.70
3
SFC
WdotF/Hp
0.51
Wi
Weights at the beginning
1620
WdotF
LB/HR = (420-63)/HR
35.79
Wj
Weights at the end
1220.05
Fuel consumption
15% for takeoff and Climb
63.15
ROC
V*(Ta-D)/W*60.032
475.08
1th UAS Team RQ-5A Hunter
lb
pph
lb
fpm
2008 Unmanned Air System
Agenda
Introduction
Analysis
Conclusion
1th UAS Team RQ-5A Hunter
2008 Unmanned Air System
Specification
Characteristics / Description:
Reported As Of:
23 March 2004:
Hunter
Flights
7,835
Hours
28,565.0
O
I
F
728
3,967.8
Wing Span
Weight
Range
Airspeed
Altitude
Endurance
Primary Payload(s)
Launch / Recovery
29.2 Feet
1620 Lbs
144 nm
70 Kts cruise
15,000 Ft
8-12 Hours with EO / IR
EO / IR
Unimproved runway
Capabilities:




Fully Qualified System
Versatile Payload Platform
Multiple Mission Configurations
Only Army Extended Range /
Endurance UAV
 Stellar Overseas / NTC / JRTC
Performance
Contractors:
 Northrop-Grumman Corp
1th UAS Team RQ-5A Hunter
• 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
2008 Unmanned Air System
1th UAS Team RQ-5A Hunter
2008 Unmanned Air System
1th UAS Team RQ-5A Hunter
2008 Unmanned Air System