简化弹道设计方法在运载火箭型号论证中的应用

针对运载火箭构型不确定、目标轨道多、最优化设计工作量大的问题,提出了一种简化弹道设计方法。通过简化动力学方程及设计变量,将构型不确定且难以建模的非线性规划问题转变为适用于多种构型且方便寻优的简化弹道设计方法。对运载火箭执行不同的目标轨道任务进行了分析,将所有的任务按照有无滑行段进行了分类,提出了针对不同任务的弹道拼接方法。采用该简化弹道设计方法对CZ-3B和Falcon9 2种不同构型的火箭实际飞行曲线进行拟合,验证了简化弹道设计方法的正确性。

Application of Simplified Trajectory Design Algorithm inType Demonstration of Launch Vehicle

To solve the problems such as uncertain configuration,multiple target orbits requirements and huge workload of optimization design of launch vehicle,a simplified optimal trajectory design algorithm was proposed. By simplifying the dynamic equation and control variables,the non-linear programming problem which is difficult to be modeled due to uncertain configuration,was transformed into a simplified algorithm which is suitable for multiple launch configurations and convenient for optimization. Different orbit-mission requirements of launch vehicle were analyzed,and all the missions were classified according to whether there was a glide segment,and a trajectory splicing method for different missions was proposed. The actual flight curves of two kinds of launch vehicles CZ-3B and Falcon9 with different configurations were fitted by the simplified trajectory design algorithm. The simplified algorithm is correct.