基于物理规划的固体运载火箭多学科设计优化  

Physical Programming Based Multidisciplinary Design Optimization of Solid Launch Vehicle

作　　者：宣颖[1] 张为华 张育林[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《宇航学报》2009年第2期669-674,711,共7页Journal of Astronautics

摘　　要：固体运载火箭设计属于典型的多学科设计问题,为提高固体运载火箭设计水平和缩短研制周期,提出了基于物理规划的固体运载火箭多学科设计优化方法。建立了固体运载火箭多学科系统分析模型,以卫星轨道设计计算得到的运载火箭关机点参数和最小火箭起飞质量为设计准则,采用物理规划方法构造系统级火箭总体设计优化模型,以发动机总体性能指标为设计准则,采用物理规划方法构造子系统级发动机设计优化模型。通过系统级总体设计优化和并行的子系统级发动机设计优化的嵌套循环,得到满足火箭运载能力的各级固体发动机最优设计结果,即得到内外弹道相匹配的发动机最优推力-时间曲线。The design of solid launch vehicle is representative multidiseiplinary design problem, in order to improve design quality and shorten design period, the methods of physical programming-based multidisciplinary design optimization （PPBMDO） are developed. The muhidisciplinary system analysis models for solid launch vehicle are derived, the launch vehicle system design optimization model based on physical programming is set up by regarding cutoff parameters calculated by satellite orbit design and minimization of vehicle takeoff mass as design metrics, the solid rocket motor subsystem design optimization model based on physical programming is also set up by the design metrics which are solid motor design performance index. PPBMDO methods can gain the optimal design which is consistent with system design constraints and the solid rocket motor thrust time curve which is a best match for exterior trajectory by looping execution between system design optimization and parallel subsystem solid rocket motor design optimization.

关 键 词：固体运载火箭 多学科设计优化 物理规划 固体火箭发动机 

分 类 号：V421.1[航空宇航科学与技术—飞行器设计]