高超声速试飞器系统的多目标优化设计  

Multi-Objective Optimization of Hypersonic Test Vehicle

作　　者：范培蕾[1] 杨涛[1] 张晓今[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》2010年第4期973-980,共8页Journal of Astronautics

基　　金：武器装备预研基金(51400010304KG0178)

摘　　要：为了将高超飞行器可靠地运载至理想工作条件,满足"平坦"型试验弹道和入轨点的约束要求,在详细分析系统气动力特性、动力特性、结构特性、质量特性的基础上,以起飞质量、高超动力飞行段射程倒数为目标函数,建立了试飞器系统的多目标优化模型,并采用MOEA/D算法进行求解计算,在综合分析系统敏感稳健性的基础上,确定最终优化方案。结果表明:最终优化方案在满足约束要求的前提下,其起飞质量大幅度降低,高超声速动力飞行段射程(R2-R1)增加较多,验证了对试飞器系统进行多目标优化的必要性和合理性。In order to ferry hypersonic vehicle to flight test conditions with the restriction requirements of flight-test trajectory＇s evenness and insertion point＇s relevant parameters,a detailed description of aerodynamics characters,propulsion rocket engine,structure and mass property of test vehicle has been investigated.And the initial launch mass and range of hypersonic flight are chosen to be optimizing objectives to establish the multi-objective optimization models of test vehicle.Then a method of multi-objective evolutionary algorithm based on decomposition is adopted to search for Pareto solution of above optimization models.And the final scheme is determined combining with sensitivity robust of test vehicle.Simulation results indicate that the final scheme＇s initial mass has been greatly decreased and its flight range of hypersonic vehicle has increased about 7% compared with base scheme while validating the necessity and effectiveness of optimizing test vehicle in view of multi-objectives.

关 键 词：高超飞行器 试飞器 基于分解的多目标进化算法 敏感稳健性 

分 类 号：V421.1[航空宇航科学与技术—飞行器设计]