7 조 강창호 강애량 김창규 오혜영 최재영 이홍일 MQ-9B

1. Goal of Project 2. Project members 3. Schedule 4. Analysis of UAS 4.1 Requirement analysis 4.2 Air vehicle analysis 4.3 Propulsion analysis 4.4Payload analysis 4.5 Weight analysis 4.6 mission control 4.7 communication 4.8 performance analysis 5. Conclusion 2

3 Establishes the general concept, What it should do and how it will be used Product is usually a set of initial requirements and expectations for cost and schedule

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6 Chief engineer [ 강 창 호 ] Air vehicle engineer [ 강 애 량 ] Subsystem engineer [ 최 재 영 ] Electric engineer [ 오 혜 영 ] performance analysis engineer [ 김 창 규 ] weight engineer [ 이 홍 일 ]

7 Tier II: Medium altitude, long endurance Multi-Mission ISR Intelligence, Surveillance, Reconnaissance (ISR)

Interdiction and armed reconnaissance against critical, perishable targets Reconnaissance, surveillance and target acquisition in support of the Joint Forces commander Reconnaissance is now accomplished with: – Persistent airborne platform – Day and night streaming video – Synthetic aperture radar to image through clouds – Near instantaneous distribution world wide 8

Long Endurance Armed Reconnaissance – 30~50hr flight times – Camera and radar sensors to detect – Precision weapons to destroy To make it routine – The pilot/crew had to come out of the airplane – The airplane had to be reliable enough to run for 30 – 50hr per flight – A control scheme had to be developed in order to fly the airplane anywhere – Unique distribution and reception systems HG620TJC 9

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11 Mid Wing Provides lowest drag Some ground clearance benefits of the high wing (Possible under wing stores) Advantages in aerodynamic maneuver Structural carry-though presents a weight increase Y-tail V-tail is used only pitch control the third vertical stabilizer is used yaw control

12 Fuselage/nacelle model Parametric analysis

13 wing model

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delta0=IF(h<36.089,( *h/1000)^ ,IF(h<65.617,0.2234*EXP((h )*( *10^-2)),IF(h< ,EXP( h* )))) theta0=IF(h<36.089, *h/288.16,IF(h<65.617,0.7519,IF(h< , h*1.0566*10^- 3))) delta =delta0*(1+0.2*B9^2)^3.5 theta= =theta0*(1+0.2*B9^2) WdotA0=T0/(Core FSP/(1+BPR)+Fan FSP*(V0/V)*(BPR/(1+BPR))) WdotA=WdotA0*delta/SQRT(theta) WdotA-gg=WdotA/(1+BPR) WdotF=WdotA-gg*fuel air ratio*theta^0.75 Ta=WdotA*Core FSP/(1+BPR)+Fan FSP*(V0/V)*(BPR/(1+BPR)))*0.95 (0.95 means install loss efficicency) SFC=WdotF*3600/Ta 16 Parametric analysis

17 Using Excel spread sheet

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4.4.1 SAR(APY-8 Lynx ) 19

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21 Lynx 3D targeting

4.4.2 MTS-B EO/IR camera system 22

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4.4.3 weapons 24

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26 grossweight W0=Emptyweight(We)+Fuel weight(Wf)+ Payload weight(Wp) +Miscellaneous weight(W_m) Empty weight fraction(EF)=We/W0 Fuel weight fraction(FF)=Wf/W0 Payload weight fraction(PF)=Wp/W0 Miscellaneous weight fraction(MF)=W_m/W0 Using Excel spread sheet

C band Lineof Sight (LOS) data link for take off, landing Ku Band satellite link for missions over the horizon 27

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32 Using Excel spread sheet Parametric analysis

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36 MQ9 are well suited for precision weapons delivery – Designs allow easy mission role expansion – Man-in-the-loop allows for positive control of weapons employment – Satellite control and persistence allows weapons to be in the right place at the right time to engage time sensitive targets MQ9 will bring significant additional capability to the fight.

37 Comparing this result with UAV.xlsUAV.xls

[1] Tom Kaminski: "The Future is Here", article in Combat Aircraft Vol. 4, No. 6, 2003 [2] Department of Defense Missile Nomenclature Records [3] "Unmanned Aircraft Systems Roadmap, ", Office of the Secretary of Defense, 2005 [4] [5] Aviation week & space technology, 2002 [6] q-9.htm [7] international.com/mq9_funding_authorization_b.htmhttp:// international.com/mq9_funding_authorization_b.htm [8] mics_MQ-9_Reaper#MQ-9A 38