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Dynamic Performance Simulation of the Propulsion System for the CRW-Type UAV Using SIMULINK  

Kong Chang-Duk (조선대학교 항공우주공학과)
Park Jong-Ha (조선대학교 항공우주공학과)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.8, no.4, 2004 , pp. 76-83 More about this Journal
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 main and rotary ducts, the nozzle subsystem including main and tip jet nozzle for three flight modes such as lift/landing mode, low speed transition flight mode and high speed forward flight mode. Transient simulation performance utilized the ICV (Inter-component volume) method and simulated using the SIMULINK. Transient performance analysis was performed on 3 cases. Fuel flow schedules to accelerate from Idle to maximum rotational speed were divided into the step increase of the most severe case and ramp increase cases to avoid the overshoot of turbine inlet temperature, and variations of thrust and the turbine inlet temperature were investigated in some transient analysis cases.
Keywords
CRW type UAV; Turbo-Jet; Performance Simulation; SIMULINK;
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