固冲组合发动机进气道设计

THE DESIGN OF INLET FOR COMBINED ROCKET-RAMJET ENGINE

关键词:  组合式发动机  进气道  设计

Key words:  Composite engine  Inlet  Design

摘要:

简要地介绍了固体火箭-冲压组合发动机进气道设计思想,叙述了后置旁侧进气道突扩的特点,由于气流的拐弯、突扩和掺混,进气道总压恢复系数辐度下降。因此过于讲究进气道本身型面设计是完全没有必要的,而尽可能减小外阻却是极为重要的。 固冲组合发动机多用于加速式地空弹,这就需要增加接力点附近的推力,因此应考虑采用超额定工作进气道,增大流量以提高地空弹加速式冲压型发动机和导弹性能。 文中对后置旁侧气道攻角适用范围以及大攻角进气道性能进行了讨论,因为这是组合发动机用于地空弹和反辐射弹需要解决的突出问题,加大组合发动机攻角范围是当前急需解决的技术关键。

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.