冲压发动机导弹爬升轨迹∕发动机一体优化设计  

Integrate Optimization Design of Climb Trajectory and Motor for Ramjet Powered Missile

作　　者：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]航天科工集团二院二部,北京100854

出　　处：《计算机仿真》2013年第10期138-142,共5页Computer Simulation

基　　金：国家自然科学基金(11202165)

摘　　要：研究液体冲压发动机为动力的导弹爬升轨迹/发动机一体化优化设计问题。综合分析了冲压发动机性能与飞行弹道参数的关系,建立了一体化优化设计的相关数学模型及优化模型。提出了用高斯伪谱法将一体化最优控制问题转化为静态参数优化问题,采用序列二次规划方法对该问题进行求解。仿真结果表明所建立的一体化优化模型是合理的,高斯伪谱法具有对初始值不敏感和收敛速度快的特点,能很好的满足终端约束。通过一体化优化设计,可有效发挥冲压发动机的性能,节省燃料,提高了导弹弹道的性能。The integrate optimization design of climb trajectory and liquid ramjet for a missile was investigated. The performance index of ramjet and the missile ballistic parameters were related, coupled with each other. The in- tegrate design optimization of mathematical model and optimization model were established. The optimal control prob- lem was transcribed into a nonlinear programming using Gauss pseudospectral method and was solved by Sequential Quadratic Programming algorithm. The simulation result demonstrates that the integrated optimization model is rea- sonable. The Gauss pseudospectral method is not sensitive to the initial guess, has well precision, high accuracy, and strong convergence. Through integrated design optimization, it can effectively play ramjet performance and save fuel, and significantly improve the ballistic performance of missile.

关 键 词：冲压发动机 轨迹 一体化设计 高斯伪谱法 序列二次方法 

分 类 号：TJ765.43[兵器科学与技术—武器系统与运用工程]