垂发超近程导弹弹道优化设计  

Trajectory Optimization Design of Vertical Ultra Short Range Missile

作　　者：马璐 孙瑞胜[1] MA Lu;SUN Rui-sheng(Nanjing University of Science and Technology, College of Energy and Power Engineering, Jiangsu Nanjing 210094, China)

机构地区：[1]南京理工大学能源与动力工程学院,江苏南京210094

出　　处：《现代防御技术》2018年第2期39-44,共6页Modern Defence Technology

摘　　要：垂发超近程导弹弹道优化设计是通过设计飞行攻角和发动机推力参数使得导弹性能指标达到最优或次优。针对超近程导弹垂直发射的特点给出发动机推力的分段准则,设计导弹初始飞行状态、飞行过程状态和终端弹道状态参数等约束条件,建立导弹运动学模型和多约束条件下弹道优化模型。基于hp-伪谱法将弹道优化问题转变成非线性规划问题。最后将优化方案所得的结果和遗传算法的优化结果进行对比分析验证优化方案的合理性。仿真结果表明可为垂发超近程导弹弹道设计提供参考。The trajectory optimization design of vertical ultra-short-range missile is based on the design of command angle of attack and thrust of the engine to achieve the optimal or sub optimal of missile performance. According to the characteristics of vertical launching of ultra-short-range missile,the constraints such as the subsection criteria for engine thrust,the design of the initial state of the missile,the state of the flight process and the parameters of the terminal ballistic state are given,the kinematic model of missile and trajectory optimization model under multi constraints are established. The trajectory optimization problem is formulated as a linear programming problem based on the hp-pseudo-spectral method.The results of the optimized scheme and the optimization results of genetic algorithm are compared and analyzed to verify the reliability of the optimization scheme. The simulation results show that it can be used as a reference for the optimization of vertical ultra-short-range missile＇s trajectory.

关 键 词：垂直发射 超近程导弹 攻角设计 发动机推力设计 多约束弹道优化 hp-伪谱法 

分 类 号：TJ761.7[兵器科学与技术—武器系统与运用工程] TJ013