弹用涡喷发动机飞行试验启动加速性能仿真

推进技术 ›› 2001, Vol. 22 ›› Issue (6): 454-457.

弹用涡喷发动机飞行试验启动加速性能仿真

于军,于守志

航天机电集团公司31所北京100074;航天机电集团公司31所北京100074

发布日期:2021-08-15

Starting and accelerating model of missile turbojet engine in flight test

The 31st Research Inst., Beijing 100074,China;The 31st Research Inst., Beijing 100074,China

Published:2021-08-15

摘要/Abstract

摘要： 结合导弹飞行的应用实际 ,利用有限的部件特性 ,建立了弹用涡喷发动机启动加速至巡航状态全过程的动态性能仿真模型。对仿真模型计算结果进行了分析 ,模型计算结果与飞行试验数据吻合较好。该模型的建立对导弹发射过程发动机性能的分析具有重要的现实意义。

关键词: 导弹推进;涡轮喷气发动机;飞行试验;空中起动;加速过程;数学模型

Abstract: A mathematical model of missile turbojet engine from starting and accelerating to cruising state was established combining with the missile flight test. The results of model simulation were well in accord with the flight test data. The model was important for engine performance analysis in the period of missile launch and cruise conditions.

Key words: Missile propulsion;Turbojet engine;Flight test;Air starting;Acceleration performance,Mathematical model

于军,于守志. 弹用涡喷发动机飞行试验启动加速性能仿真[J]. 推进技术, 2001, 22(6): 454-457.