RBCC引射/亚燃模态过渡点选择

Selection of ejector-ramjet mode transition interval on RBCC

以RBCC推进系统为动力的飞行器设计流程出发，建立了考虑发动机工作的限制条件的引射和亚燃模态性能评估方法，研究了不同燃料条件下发动机引射和亚燃模态下比冲和推力系数随飞行弹道的变化规律，提出了基于比冲最优、推力变化最小的模态过渡点选择方法；结合某一具体飞行任务的典型弹道，获得了在飞行马赫数为2．6±0．1、飞行高度为11．7—12．9km范围内进行引射／亚燃模态过渡最佳的结论。

The performance evaluating method that takes into account the RBCC restrictive real operation condition of ejector and ramjet mode was set up based on aircraft design flow chart. The change of specific impulse and thrust coefficient of motor using different fuels with flight trajectory were discussed. The selection method based on optimum specific impulse and minimum thrust fluctuation of ejector/ramjet mode transition interval was put forward. In considering the reference flight trajectory of a certain mission, the reasonable mode transition interval in condition of Ma = 2.6± 0.1 flight velocity and 11.7- 12.9 km flight height was resuited.