基于微分进化算法的导弹起飞质量优化设计  

Optimization Design of Missile Take-off Mass Based on Differential Evolution Algorithm

作　　者：梅跃松[1] 于剑桥[1] 周亮[2] 孟宏志 张伟 

机构地区：[1]北京理工大学宇航学院,北京100081 [2]上海航天技术研究院,上海200233 [3]山西北方惠丰机电有限公司,山西长治046012

出　　处：《北京理工大学学报》2011年第11期1270-1272,1277,共4页Transactions of Beijing Institute of Technology

基　　金：国家"八六三"计划项目(2009AA8013110F)

摘　　要：为快速准确地计算导弹起飞质量,对优化算法进行了研究,提出了基于微分进化算法的导弹起飞质量设计方法.以单室双推力固体火箭发动机类型的导弹起飞质量作为算例进行了优化设计.确定了设计变量及约束条件,建立了导弹起飞质量优化模型.根据优化模型选取微分进化算法中的种群规模、最大进化代数等参数,最终通过不断迭代获得最小起飞质量.优化结果显示,与遗传算法相比,微分进化算法在导弹起飞质量计算方面具有更快的收敛性和更高的计算精度.The optimization algorithm was developed to calculate the take-off mass more efficiently and accurately, and the missile take-off mass design method based on differential evolution was proposed. The take-off mass o1 the missile with single-chamber dual-thrust motor was set as the example for optimization design. The design variables and constraints were set up, and the model to optimize take-off mass was established. The parameters of population size and the maximum evolutionary generation were determined according to the optimization model. Finally, the minimum take-off mass was obtained via continuous iterations. Compared with genetic algorithms, differential evolution algorithm demonstrates its faster convergence and more computational accuracy in take-off mass design o1 missile.

关 键 词：起飞质量 微分进化 遗传算法 单室双推力 

分 类 号：V279[航空宇航科学与技术—飞行器设计]