基于响应面的悬浮火箭协同优化设计  

Collaborative optimization design of suspended rocket based on response surface

作　　者：张鹏程 杨军[1] 罗志清 李晓晖[1] 

机构地区：[1]中国航天科技集团公司四院四十一所,西安710025

出　　处：《固体火箭技术》2017年第6期793-798,共6页Journal of Solid Rocket Technology

摘　　要：针对悬浮火箭的多学科、强耦合的特点,利用飞行器多学科设计优化建立导弹推进、控制学科优化模型及系统优化模型,以延长悬浮时间为目标提出一种基于改进的响应面协同优化方法。通过试验设计和响应面近似技术,分别建立复杂系统的目标函数及多学科一致性等式约束响应面,利用改进的协同优化构架进行寻优计算,结合优化结果丰富目标函数响应面样本,提高目标函数精度。结果表明,该方法能快速收敛到最优结果,优化后火箭的悬浮时间延长了11.5%、机动距离增加了3.7%、进入悬浮姿态时间提高9.4%。该方法实现了悬浮火箭的多学科优化,达到了优化目的,提升了火箭性能。Aiming at the characteristics of muhidisciplinary and strong coupling of suspended rocket, missile thrust, control opti- mization model and system optimization model were established by means of multidisciplinary design optimization method.A collabo- rative optimization method based on improved response surface method was proposed to prolong the suspension time.Through the de- sign of experiments method and approximation technique, objective function of complex system and muhidisciplinary response sur- face the uniformity equality are established ,respectively.The optimization function is used to improve the accuracy of the objective function, and the optimization result is used to enrich the sample of the objective function response surface.The results show that the method can converge to the optimal result quickly.After optimization,the suspension time of rocket is extended by 11.5% ,while the maneuvering distance is increased by 3.7%.The time of entering the suspended attitude is increased by 9.4%.The algorithm achieves the muhidisciplinary optimization of the suspended rocket and the optimization purpose, which improves the rocket performance.

关 键 词：多学科设计优化 悬浮火箭 试验设计 近似技术 基于改进的响应面协同优化 

分 类 号：V421[航空宇航科学与技术—飞行器设计]