关键词: 超燃冲压发动机;多模态冲压发动机;高超声速冲压发动机;模态特性;技术途径

Abstract: In order to reach simultaneously high performances (specific impulse, thrust coefficient, thrust/weight ratio) for the hypersonic ramjet under wide range flight condition, it is necessary to match the parameters of inlet/combustor /nozzle based on the characteristics of multi mode operation. Under the condition of fixed geometry, the integrated internal flow path should be designed,and the heating process has to be sophisticatedly adjusted. Thus, different optimal operation mode should be adopted for different flight condition to prevent the subsonic spillage or extreme supercritical condition in the inlet, the over or under expansion in the nozzle, the extreme high temperature and pressure in the combustor, and to obtain maximum impulse increase. Due to the complexity of the hypersonic propulsion technology, lots of experiences and lessons occurred during research and development in domestic and foreign countries, the technical innovation should be pay attention and carried out.

Key words: Supersonic combustion ramjet engine;Multi mode ramjet;Hypersonic ramjet engine;Characteristics of mode;Technical path