关键词: 组合式发动机;进气道;设计

Abstract: In this paper, consideration of design of inlet for combined rocket-ramjet engine is discussed. The characteristics of sudden expansion aft bypass supersonic inlets is described. The total pressure recovery coefficient decreases greatly due to curved flow, sudden expansion and mixing. Therefore, it is not necessary to overemphasize the inlet configuration design, and it is the most important to decrease the external drag as much as possible.Solid combined engine is usually used for accelerativc surface-to-air missile. Greater thrust is reguired at take-over condition. Thus, by workingin the over normal regime of inlet, increased flow can improve the performance of accelerative ramjet engine and surface-to-air missile.Also, the suitadle range of attack angle for aft bypass supersonic inlet and the performance of high attack angle inlet are discussed.It is a promin ent problem to be solved for the combined engine used for surface-to-air and anti-radiation-missiles. A key issue at present is how to increase the range of attack angle for the engine.

Key words: Composite engine;Inlet;Design