内装式空射运载火箭与载机分离过程的纵向飞行品质研究  

The Study on Longitudinal Flight Quality during Separation of Built-in Air-launched Launch Vehicle from Launch Aircraft

作　　者：张艳华[1,2] 张登成[1] 张久星[1] 朱和铨[1] 

机构地区：[1]空军工程大学工程学院,西安710038 [2]西北工业大学航空学院,西安710072

出　　处：《弹箭与制导学报》2011年第6期190-192,共3页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为了掌握空中发射运载火箭分离过程中载机的纵向飞行品质,基于载机重心位置的变化特点,建立了纵向无量纲的线化小扰动状态方程,利用时域分析的方法对长、短周期模态特性进行了数值模拟,对照飞行品质规范与准则确定了飞行品质等级。结果表明随着运载火箭向后移动,短周期模态的飞行品质由等级1下降到等级2;长周期模态仅满足等级3要求。可见分离过程严重影响了载机的飞行品质,需要进一步采取措施提高载机的飞行品质和安全性。In order to know the longitudinal flight quality of a launch aircraft during launch vehicle＇s separation,according to the change of aircraft＇s center of gravity,the longitudinal small perturbation state equations were built,and the time-domain method was applied to the simulation of long and short cycle modes,then the grade of flight quality was given according to criterion.The results show that the flight quality of short mode degrades from grade one to grade two,long mode only satisfies grade three during launch vehicle＇s separation.Obviously,the separation has serious effect on flight quality and it is necessary to improve flight quality and safety in the future.

关 键 词：运载火箭 重心 状态方程 飞行品质 

分 类 号：V475[航空宇航科学与技术—飞行器设计]