DocumentCode
3056609
Title
Integrated performance of hypersonic vehicle and turbine based combined cycle propulsion system
Author
Liu, Zengwen ; Wang, Zhanxue ; Cai, Yuanhu ; Ma, Huimin
Author_Institution
Sch. of Power & Energy, Northwestern Polytech. Univ., Xi´´an, China
fYear
2010
fDate
8-10 June 2010
Firstpage
262
Lastpage
266
Abstract
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.
Keywords
aerospace engines; aerospace propulsion; Mach 4; TSTO; combined cycle propulsion system; equal shock intensity method; hypersonic turbine; hypersonic vehicle; Engines; Fuels; Numerical simulation; Propulsion; Trajectory; Turbines; Vehicles; TBCC engine; hypersonic vehicle; integrated performance; numerical simulation;
fLanguage
English
Publisher
ieee
Conference_Titel
Systems and Control in Aeronautics and Astronautics (ISSCAA), 2010 3rd International Symposium on
Conference_Location
Harbin
Print_ISBN
978-1-4244-6043-4
Electronic_ISBN
978-1-4244-7505-6
Type
conf
DOI
10.1109/ISSCAA.2010.5634020
Filename
5634020
Link To Document