Study on the Propulsion System Integration Optimization for a Turboprop Aircraft

터보프롭 항공기 추진기관 시스템 종합 최적 설계 연구

  • 공창덕 (조선대학교 우주항공공학과) ;
  • 김진원 (조선대학교 우주항공공학과)
  • Published : 1995.05.01


The Propulsion System Integration can be defined as the optimization technology of combining the propulsion system components with the airframe to achieve the overall aircraft misson performance goals. The disposition of propulsion system components on engine compartment enveloped by front fuselage and fire bulkhead is very restricted because of the interference with nose L/G and engine mountig strut. The design of components depends on the traditional technical data base. The engine satisfying a customer's ROC was selected among worldwide existing engines by the comparision studies of performance analysis with enigine installed effect, future growth potential, ILS, and application to aircrafts, etc. The ground test of the propulsion system integration was performed in the test cell and on the aircraft to assure the function of the components. The flight test was performed to confirm complying the performance requirements.