基于全模式遗传算法的导弹/固体冲压发动机一体化优化  

Integral design optimization for missiles/solid rocket ramjets based on all schema genetic algorithm

作　　者：赵建民[1] 夏智勋[1] 郭健[1] 缪万波[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：《固体火箭技术》2005年第1期1-4,共4页Journal of Solid Rocket Technology

摘　　要：在综合考虑固体火箭冲压发动机设计、导弹气动特性和外弹道关系的情况下,详细分析了各设计变量,并建立了空空导弹总体 /冲压发动机一体化设计优化模型。针对在优化过程中遇到的无显式约束问题,提出了一种高效全模式遗传算法,并分析了其收敛性。计算结果表明,与其它算法相比,全模式遗传算法具有极强的全局寻优及高速收敛能力;一体化优化设计优于工程设计方法,可有效提高导弹总体性能。On the basis of comprehensively considering design of solid rocket ramjets, aerodynamic properties of missiles and trajectory, the design variables were analyzed in detail, and an integrated optimization design model for air-to-air missiles/solid rocket ramjets was established. A kind of all-schema genetic algorithm (ASGA) was presented for the implicit confinement problems during the optimization. The convergence of ASGA was analyzed. The results show that ASGA possesses remarkable ability of searching global optimal solution and rapid convergence in comparison with other methods, and the integrated optimization design method is superior to the engineering design method and can effectively improve the system performances of missiles.

关 键 词：遗传算法 固体冲压发动机 模式 一体化优化设计 工程设计方法 发动机设计 一体化设计 固体火箭 气动特性 设计变量 优化模型 空空导弹 约束问题 优化过程 计算结果 全局寻优 总体性能 外弹道 收敛性 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程] O242.23[理学—计算数学]