Proceedings of the Korean Society of Propulsion Engineers Conference (한국추진공학회:학술대회논문집)
- 2004.03a
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- Pages.499-505
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- 2004
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- 1975-342X(pISSN)
Dynamic Performance Simulation of the Propulsion System for the CRW Type UAV Using $SIMULINK^{\circledR}$
- Changduk Kong (Department of Aerospace Engineering, Chosun University) ;
- Park, Jongha (Department of Aerospace Engineering, Chosun University) ;
- Jayoung Ki (Department of Aerospace Engineering, Chosun University)
- Published : 2004.03.01
Abstract
A Propulsion System of the CRW(Canard Rotor Wing) type UAV(Unmanned Aerial Vehicle) was composed of the turbojet engine to generate the propulsive exhaust gas, and the duct system including straight bent ducts, tip-jet nozzles, a master valve and a variable main nozzle for three flight modes such as lift/landing mode, low speed transition flight mode and high speed forward flight mode. In this study, in order to operate safely the propulsion system, the dynamic Performance behavior of the system was modeled and simulated using the SIMULIN