TY - GEN
T1 - Inlet/TBCC/Nozzle integration concept design
AU - Chen, Min
AU - Tang, Hai Long
AU - Zhu, Zhi Li
AU - Hui, Ou Yang
AU - Zhang, Jin
PY - 2008
Y1 - 2008
N2 - The present paper focuses on the Inlet/TBCC/Nozzle integration concept design for the hypersonic civic aircraft. Firstly, several basic principles were put forward for the Inlet/TBCC/Nozzle integration concept design. Secondly. A set of fast, versatile, and trusted analysis tool was developed which could analyze the design constraints and the matching relationship between the various components among a wide flight range. Assisted by this tool, the design issues of Inlet/TBCC/Nozzle, the multiple-variable control law for an optimized TBCC propulsion system were analyzed. Then a solution for the inlet/TBCC/Nozzle integration concept design was presented. The result shows that, to meet the conflict requirements in the long range from take-off to Mach 5, the turbine based combine cycle propulsion system should apply a variable cycle engine concept via the modulation of 11 variable geometries. It can also be concluded that the solution for the TBCC propulsion system concept could meet the basic mission requirements for the hypersonic airplane.
AB - The present paper focuses on the Inlet/TBCC/Nozzle integration concept design for the hypersonic civic aircraft. Firstly, several basic principles were put forward for the Inlet/TBCC/Nozzle integration concept design. Secondly. A set of fast, versatile, and trusted analysis tool was developed which could analyze the design constraints and the matching relationship between the various components among a wide flight range. Assisted by this tool, the design issues of Inlet/TBCC/Nozzle, the multiple-variable control law for an optimized TBCC propulsion system were analyzed. Then a solution for the inlet/TBCC/Nozzle integration concept design was presented. The result shows that, to meet the conflict requirements in the long range from take-off to Mach 5, the turbine based combine cycle propulsion system should apply a variable cycle engine concept via the modulation of 11 variable geometries. It can also be concluded that the solution for the TBCC propulsion system concept could meet the basic mission requirements for the hypersonic airplane.
UR - https://www.scopus.com/pages/publications/77957852507
M3 - 会议稿件
AN - SCOPUS:77957852507
SN - 9781563479434
T3 - 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
BT - 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
T2 - 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Y2 - 21 July 2008 through 23 July 2008
ER -