摘要
火箭靶弹无控飞行过程中飞行攻角较小且无法准确模拟,为提高靶弹弹道理论预估精度,弹道理论计算可假定飞行攻角为零,将飞行攻角产生的诱导阻力贡献折算为对零升阻力系数的修正。建立了火箭靶弹气动特性工程计算方法,针对火箭靶弹零升阻力系数计算模型不确定性问题,利用火箭靶弹A飞行试验GPS遥测数据对其零升阻力系数进行了参数辨识,基于辨识结果对火箭靶弹零升阻力系数工程计算方法进行了修正。经火箭靶弹B飞行试验结果验证,由于综合考虑了飞行攻角产生的诱导阻力贡献,采用修正后的零升阻力系数,弹道理论预估精度大大提高,满足工程要求。
The angle-of-attack of the unguided rocket target is small and difficult to be simulated. In order to improve the pre- diction accuracy of rocket target ballistic characteristics, the angle-of-attack of the unguided rocket target was assumed to be zero and the drag induced by the angle-of-attack was calculated to correct the zero-lift drag coefficient. The engineering calculation method of rocket target aerodynamic characteristics was established. Aiming at the uncertainty problem of zero-lift drag coefficient calculation model,the zero-lift drag coefficient was identified based on GPS telemetry results of rocket target A flight test and the engineering calculation method of zero-lift drag coefficient were corrected by identification results. The GPS telemetry results of rocket target B flight test show that, due to taking into account the induced drag effect, the prediction accuracy of rocket target ballistic characteristics can been improved greatly by applying corrected zero-lift drag coefficient.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2010年第1期5-8,共4页
Journal of Solid Rocket Technology
基金
中国博士后科学基金资助项目(20080440221)
中国博士后科学基金特别资助项目(200801491)
关键词
火箭靶弹
零升阻力系数
诱导阻力
参数辨识
不确定性
rocket target
zero-lift drag coefficient
induced drag
parameter identification
uncertainty
