摘要
提出了波载体结构与一体化超燃冲压发动机的高超音速巡航导弹的性能计算方法,可求得不同波载体的升阻比和平面-容积比。燃烧室性能分析方法中包括了燃烧室截面积变化、空气和氢混合反应的热释放分布、热传导、摩擦、当量比和比热比对性能的影响。然后,基于二维最短喷管长度的无粘理论,进行了半壁喷管的分析。在喷管推力和升力计算及型面设计中,考虑了层流粘性的影响。最后,以平直压缩面波载型前体和一体化超燃冲压发动机构成的高超音速巡航导弹总体结构为例,进行了设计计算。
The performance computimg method of hypersonic cruise missile with waverider configuration and integrated scramjet propulsion unit is set, this can compute lift-to-drag and plan-volume ratio of different waverider shapes. A methodology for a performance calculation of scramjet includes the effects of the com- bustor section variation, the distribution of the heat release of the reacting mixture of air and hydrogen, the heat transfer, the friction, The fuel/fair equivalent ratio and specific heat ratio on the performance of the scramjet. An analysis of nozzle is based on the inviscid theory of two dimensional and minimum length nozzle. Also, the effect of laminar viscous flow is considered. Finally, a complete configuration of hypersonic scram- jet-powered cruise missile with flat compression surface waverider shapes is designed as an example.
出处
《战术导弹技术》
1996年第1期45-60,共16页
Tactical Missile Technology
