冲压发动机导弹轨迹/总体参数一体化优化设计  

Integrated Optimization Design of Trajectory and Overall Designing Parameters for Ramjet Powered Missile

作　　者：沙建科[1] 施雨阳[1] 万自明[2] 徐敏[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]北京电子工程总体研究所,北京100854

出　　处：《现代防御技术》2014年第3期37-42,共6页Modern Defence Technology

摘　　要：对以冲压发动机为动力导弹的轨迹/总体参数一体化优化设计问题进行了研究。建立了一体化优化的相关数学模型,提出采用高斯伪谱法将一体化优化中的轨迹最优控制问题参数化,然后用序列二次规划方法求解该一体化优化问题。仿真结果表明,经过一体化优化设计,起飞质量比不考虑轨迹优化的方案减少了4.06%。总体参数优化结合轨迹优化最大程度地挖掘了导弹总体设计的潜力,提高了总体性能。其结果可为冲压发动机导弹总体优化设计研究提供理论参考。The integrated optimization jet powered missile is investigated. First, design of trajectory and overall designing parameters for a ramthe mathematical model of overall designing parameters is described and the trajectory optimal control problem is transcribed into a nonlinear programming problem using Gauss pseudo - spectral method. Then, the resulting parameter optimization problem is solved by sequential quadratic programming algorithm. The simulation result demonstrates that the take off mass decreased by 4.06% does not consider the trajectory optimization for overall designing parameters optimization. Integrated optimization design of trajectory and overall parameters optimization can improve the potential of missile overall. The results can provide theoretical references for ramjet powered missile overall design.

关 键 词：总体参数 轨迹优化 一体化设计 冲压发动机导弹 

分 类 号：TJ760.3[兵器科学与技术—武器系统与运用工程] TJ013.2