To realized the integration of the design flight process and flight simulation of the Airborne launch vehicle, and further improve the reliability of the system analysis model, based on traditional analysis methods, the interaction between carrier aircraft and rocket flight process had been considered during the separatist movement of rocket and carrier aircraft, the separation multi-body dynamic model had been established, and the main factors affecting the flight process had been studied. d A set of systems were developed, which have many useful functions such as system simulating compute, 3D scene demonstration and video results analysis. The system realizes the design of the airborne vehicle, flight performance analysis and 3D flight demonstration functions. Simulation results show that the design of flight process can help improving the airborne launch vehicle flight performance and can provide reference for the analysis of the feasibility and reliability of flight process design.%关于载机和运载火箭分离程序的优化设计问题,为实现机载运载火箭飞行程序设计保证运行姿态稳定性,并进一步提高系统模型的可信度,在传统分析方法的基础上.考虑了箭机分离过程中载机与火箭飞行程序之间的相互作用,建立了载机与运载火箭的分离多体动力学模型,研究了影响飞行姿态的主要因素.开发了集仿真计算、三维视景演示和可视化结果分析为一体的机载运载火箭飞行程序设计仿真系统,实现了机载火箭飞行程序设计,性能分析以及三维飞行演示等功能.仿真结果表明系统提高了机载运载火箭飞行性能,并能为飞行程序设计的可行性与可靠性提供了科学依据.
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