Integrated Performance of Hypersonic Vehicle and Turbine Based Combined Cycle Propulsion System

摘要：

A hypersonic vehicle concept as a first stage of TSTO is developed with a turbine based combined cycle propulsion system. The install and uninstall performance characteristics of engine are calculated by numerical simulation software. Based on equal shock intensity method, a hypersonic mix-pressure inlet is designed and the regulation is described in this dissertation. In addition, an SREN with linear extend afterbody is designed. At last, the flight performance of the vehicle with two kinds of different fuels are calculated from take off to Mach 4.

关键词： hypersonic vehicle:TBCC engine:integrated performance:numerical simulation

作者: Zengwen Liu Zhanxue Wang Yuanhu Cai Huimin Ma

作者单位: School of Power and Energy,Northwestern Polytechnical University,Xian 710072,China Institute No.31,China Aerospace Science and Industry Corporation,Beijing 100074,China

会议类型: 国际会议

会议名称: The 3rd International Symposium on Systems and Control in Aeronautics and Astronautics(第三届航空航天系统与控制国际会议 ISSCAA 2010)

会议地点: 哈尔滨

会议语种:英文

页码: 260-264

在线出版日期: 2010-01-08（万方平台首次上网日期，不代表论文的发表时间）