RBCC飞行器变结构进气道方案研究

火箭基组合动力循环(RBCC,Rocket Based Combined Cycle)飞行器的飞行速域宽、距离远,这就要求飞行器在整个飞行包络内,其推进系统不仅在设计点具有良好的性能,在非设计点时也要求能正常工作。本文以一种RBCC飞行器为研究对象,计算不同马赫数条件下动力系统进气道的性能,在此基础上提出一种进气道的变形方案。结果表明,本文所设计的变几何进气道方案,能够使得组合动力发动机在工作段满足不同的推力需求,提高了发动机的效率。

Research on Veriable Geometry Inlet Scheme of RBCC Vehicle

The vehicle powered by Rocket Based Combined Cycle (RBCC) which has wide range of velocity and distance requires a good performance both in the design point and the non-design point of propulsion system throughout the flight envelope. In this paper, the performance of a inlet on different Mach number is calculated based on a kind of RBCC vehicle. And a solution of inlet deformation is proposed. The results showed that the design of variable geometry inlet can make the RBCC meet the different needs of the working section and improve the efficiency of the engine.