摘要
基于空空导弹的质点动力学方程建立了轨迹优化模型,并根据非线性规划优化算法的特点,对优化模型中的积分变量进行替换。采用一种改进的多重打靶法将轨迹优化问题转化为约束非线性规划问题,在此基础上采用广义乘子法和变尺度法求解满足各种约束条件的最优转弯轨迹。仿真结果表明,该轨迹优化方法实现了导弹在约束条件下的最短时间转弯,且所得结果符合运动学规律,对于离轴发射以及越肩发射的转弯问题具有一定意义。
The trajectory optimization model was established based on the air-to-air missile point-mass dynamic equations and the integral variables were changed according to the optimization algorithm. By using an improved multiply shooting method, the optimal trajectory control problem was converted to a nonlinear programming problem, which was solved by the generalized Lagrange multiplier method and variable metric algorithm. The simulation results show that the minimum-time turn with constraints was achieved by the approach, and the optimal solutions which were obtained according to the kinematics rule, will have good effect on the research of off-boresight launch and over the shoulder launch.
出处
《飞行力学》
CSCD
北大核心
2008年第3期53-56,共4页
Flight Dynamics
关键词
轨迹优化
空空导弹
非线性规划
trajectory optimization
air-to-air missile
nonlinear programming
