内装式空射运载火箭与载机分离研究  

Study on Internally Carried Air-launched Launch Vehicle Separaftion from Aircraft

作　　者：张登成[1,2] 闫杰[2] 张久星[1] 

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

出　　处：《弹箭与制导学报》2009年第5期158-161,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为了比较内装式空射运载火箭前向发射和后向发射的性能,在定性分析内装式运载火箭与载机分离过程的基础上,建立了内装式空射运载火箭采用前向发射和后向发射时的分离过程数学模型。其中运载火箭的数学模型是刚体运动模型,稳定伞的模型是质点模型,而伞绳的模型是弹簧阻尼系统模型。以此数学模型为基础,对两种发射方式的分离过程进行了仿真计算。结果表明,内装式空射运载火箭采用前向发射方式比采用后向发射方式具有较大的性能优势,但运载火箭的姿态控制是前向发射的技术难点。In order to compare the performance of forward launch and backward launch of the internally carried airlaunched launch vehicle, the mathematical models of respective separation process were built on the basis of qualitative analysis. The model of launch vehicle is rigid-body motion equation. The model of stabilizing parachute is mass point motion equation. The parachute line model is spring-damp system equation. The separation of the both launch modes was simulated. The results indicate that the forward launch gains an advantage in capability over backward launch, but the difficulty of forward launch is attitude control of the launch vehicle.

关 键 词：飞行力学 空中发射 运载火箭 稳定伞 物伞系统 

分 类 号：V475[航空宇航科学与技术—飞行器设计]