基于OPTIMUS的临近空间飞行器再入轨迹优化设计

摘要

针对临近空间飞行器再入飞行受到热流率、动压和过载等多约束情况下的轨迹优化问题,提出了基于OPTIMUS优化软件平台搜索初值的编程求解方案。首先根据再入飞行动力学原理建立数学模型,并合理简化,应用最优控制理论设计滚转角控制律;然后利用OPTIMUS软件平台搭建系统工作流程,进行试验设计并建立响应面模型,通过平台集成的优化算法寻找初值;最后结合不同优化算法的优点,基于遗传算法加模式搜索法编写程序求解轨迹。结果表明,基于OPTIMUS分析所设计的轨迹优化方案,可以快速确定较为准确的初值,计算效率显著提高,且能够保证较高精度。%A trajectory optimization method with heating rate,dynamic pressure and load constraints is proposed for near space vehicle based on the OPTIMUS optimization software platform.The dynamic model of entry flight is given and reasonably simplified.The optimal bank angle control law is designed then.The system working flow,design of experiment（DOE） and response surface model（RSM） are built up on OPTIMUS platform.The initial guess is obtained using the optimal algorithms on the platform.With benefits of local and global algorithms,a program combining genetic algorithm and pattern search method is developed to optimize trajectory.The simulation results show that the proposed trajectory optimization method based on OPTIMUS can find accurate initial guess rapidly and improve computation efficiency with high precision.