满足大动压模拟要求的试验弹道优化设计

为了解决弹道导弹在高海拔发射场进行飞行试验时的大动压检验问题，提出一种模拟大动压条件的试验弹道设计方法。针对发射场的实际特点，建立残骸再入的动力学模型与落区边界模型；将大动压模拟条件转化为过程约束，提出一种主动段联合优化策略。基于自适应模拟退火算法，分别设计了三组满足不同大动压模拟条件和各项约束的试验弹道，并给出了对应的落区调整方案，验证了该方法的可行性。设计结果表明,最大动压主要出现在一级，一级最大负攻角增加，则最大动压也明显提高；同时调整发射方位角和二、三级程序角可以保证试验弹道满足弹头落点约束条件。
To solve the high dynamic pressure testing problem while ballistic missile is in flight testing with high-altitude launch site, a test trajectory design method for simulating high dynamic pressure condition was proposed. Firstly, aimed at the actual characteristics of launch site, the dynamic model of wreckage reentry and the impact area boundary model were established. Then, the high dynamic pressure simulated condition was transferred to a process constraint, and a powered phase united optimization strategy was proposed. Based on the adaptive simulated annealing algorithm, three test trajectories meeting different high dynamic pressure simulated conditions and all constraints were designed separately, meanwhile the impact area adjusted program was generated correspondingly, and its feasibility was demonstrated. Results illustrates that the maximal dynamic pressure occurs in the first stage, the maximal negative angle of attack in the first stage contributes to improve the maximal dynamic pressure greatly; the warhead impact point constraint of test trajectory can be guaranteed by adjusting launching azimuth and the pitch program angle of the second and the third stage at the same time.