摘要
针对一种两级运载器、滑翔级翼身组合体外形的导弹方案,采用多学科设计优化方法研究了包括两级发动机装药量、工作时间、滑翔级翼面形状和助推-滑翔弹道在内的优化设计问题。将系统分为总体、气动、发动机、弹道四个学科。采用增强协同优化方法进行分解协调优化。目标函数为最大射程和最小总加热量的加权和,约束条件为驻点热流、导弹质量、滑翔段终点速度、高度等。采用试验设计方法进行不同外形的气动力计算,并构造响应曲面。结果表明该MDO方法可适用于助推-滑翔导弹的概念研究。
A missile scheme has been studied that has two stage launcher and wing-body configuration glider. The optimum design problem of solid rocket fuel mass and working time, wing shape, of glider and boost - glide trajectory is solved by means of muhidiseiplinary design optimization technique. The system has been decomposed into disciplinary snhsystems describing system eoordation, aerodynamics, engine and trajectory analyses. The enhanced collaborative optimization methodology has been used to decompose, coordinate and optimization. The weighted sum of maximum range and minimum total heat load is considered as the objective. Constraints are imposed on the stagnation heating rate, weight of the missile, gliding terminal velocity and altitude, etc. Design of experiment method is used to calculate aerodynamic characteristic of different shape and build response surface. The results show this MDO methodology can be used in the conceptual study of boost-glide missile.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2009年第6期2436-2441,共6页
Journal of Astronautics
关键词
助推-滑翔
多学科设计优化
形状优化
弹道优化
增强协同优化
Boost-glide
Multidisciplinary design optimization
Shape optimization
Trajectory Optimization
Enhanced col- laborative Optimization
