三点法导引导弹初始段弧形弹道优化设计及实现  

Optimum Design and Implementation of Initial Arc Trajectory for a Three-point Guidance Missile

作　　者：陈罗婧[1] 刘莉[1] 于剑桥[1] 

机构地区：[1]北京理工大学宇航科学技术学院,北京100081

出　　处：《弹道学报》2009年第2期65-69,共5页Journal of Ballistics

摘　　要：为防止由发动机羽烟效应或冲击波产生的尘云引起前视红外的匿隐和目标的遮蔽,采用三点法导引导弹在初始段沿偏离瞄准线的弧形弹道飞行.通过非线性规划的直接方法优化得到最优的初始段弧形弹道,提出了采用加PI校正的过载驾驶仪对导弹进行控制.结果表明,与标准过载驾驶仪和加积分校正的过载驾驶仪相比,PI校正的过载驾驶仪具有较好的响应速度,能消除跟踪误差,具有良好的性能.利用优化得到的控制指令进行了初始段弹道仿真,验证了该方法的可行性.Three-point guidance missile flying along a initial arc trajectory was used to avoid the engine fog or dust cloud produced by shock wave shielding the target. The optimal initial arc trajectory optimized by direct method of nonlinear programming was obtained. The missile was controlled by a vertical acceleration autopilot with PI compensation. The results indicate that, compared with a standard acceleration autopilot and an integration compensated acceleration autopilot, PI compensated acceleration autopilot has good response velocity, and good close loop gain can be obtained. The initial trajectory simulation was conducted for certain kind of missile controlled under the optimization command. Simulation results validats that the scheme is feasible.

关 键 词：三点法导引 弹道优化 自动驾驶仪 比例积分校正 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]