摘要
介绍了弹用涡喷发动机稳定性计算的方法。基于平行压气机模型 ,发展了计算进口压力畸变对弹用涡喷发动机稳定裕度影响的计算程序。以某型号导弹用涡喷发动机为例 ,计算了在某一评审条件下 ,不同的进口畸变指数所造成的该涡喷发动机的稳定裕度损失。
The surge of missile turbojet engine is disastrous for the missile, so it is important to ensure its stability margin. The pressure distortion of the inlet of turbojet engine has an important effect on its stability margin. According to the model of parallel compressor and Liapunov theory, a program for computing the effect of inlet pressure distortion on the surge and running line of missile turbojet engine is developed. A numerical example is given to illustrate the loss of surge margin.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2003年第3期266-268,共3页
Journal of Northwestern Polytechnical University
关键词
涡喷发动机
稳定裕度
压力畸变
Intake systems
Lyapunov methods
Mathematical models
Missiles
Stability
