带落角约束的末端机动Terminal滑模导引律设计  

Design of a Maneuver Terminal Sliding Mode Guidance Law with Impact Angle Constraints

作　　者：于德海[1] 范作娥[2] 史贤俊[2] 

机构地区：[1]海军航空工程学院训练部,山东烟台264001 [2]海军航空工程学院控制工程系,山东烟台264001

出　　处：《海军航空工程学院学报》2011年第5期517-520,共4页Journal of Naval Aeronautical and Astronautical University

基　　金：总装武器装备重点创新基金支持项目(6140511)

摘　　要：为了提高反舰导弹的突防概率，有效规避敌方舰空导弹的拦截，并且实现反舰导弹按预定方向精确打击目标的战术要求，首先，基于弹目之间的三维相对运动模型，应用Terminal滑模控制理论，设计了一种带有落角约束的变结构导引律；然后，通过叠加虚拟干扰的方法，在原来导引律基础上叠加了一虚拟干扰，此虚拟干扰不影响导引律的渐进稳定性，不影响反舰导弹的打击精度，并且使得反舰导弹能够产生足够大的过载，但是又不超过其可用过载，使反舰导弹产生一定的机动变轨来实现规避舰空导弹。仿真结果表明了文章设计方法的有效性。In order to improve the penetration effect of the- anti-ship missile, avoid to be intercepted by the ship-to-air missile, and achieve the tactical mission of attacking the target on the appointed direction, based on the 3-D relative motion model of missile and target, a Terminal sliding mode guidance law with impact angle constraints, was presented in the point of view of engineering application. Then a virtual interference was added on the proposed guidance law, and the it had no effect on the stability of the guidance system and the attack precision. The suppositional disturbance can offer the enough acceleration of the anti-ship missile, but not exceed the available acceleration. And the virtual interference could produce certain terminal maneuver to avoid the intercepting of the enemy ship-to-air missile. The numerical simulation result showed the validity and effectiveness of the proposed method.

关 键 词：导引律 TERMINAL滑模 落角约束 机动 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]