针对机动目标带攻击角约束的三维制导律  

Three-dimensional guidance law with attack angle constraint for maneuverable target

作　　者：尹永鑫[1] 杨明[2] 吴鹏[2] 

机构地区：[1]中国航天空气动力技术研究院,第十一总体设计部,北京100074 [2]哈尔滨工业大学航天学院,控制与仿真中心,哈尔滨150001

出　　处：《固体火箭技术》2010年第3期237-241,共5页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(60434010);黑龙江省杰出青年基金(JC200606)

摘　　要：针对机动目标设计了带攻击角约束的三维制导规律。建立了球坐标系下的三维弹-目标相对运动模型,描述了视线高低角和视线方位角之间的耦合关系。针对导弹与目标作非共面运动的情况,基于滑模控制理论,给出了带攻击角约束的三维制导律。为了克服抖动,对所给出的三维制导律进行了修正。针对目标的机动加速度是时变的情况,给出了基于先验知识的制导参数自适应调整规则。仿真结果表明,该三维制导律能垂直命中机动目标,并对目标机动加速度的变化具有较强的鲁棒性和适应能力。A three-dimensional guidance law with attack angle constraint was designed for maneuverable target.In order to unfold coupling of line of sight,three-dimensional relative geometry relation between missile and target was constituted in spherical coordinates.With a view of research on no-coplanar relative geometry,three-dimensional guidance law with attack angle constraint was presented by using the sliding mode control theory.And the three-dimensional guidance law was improved to overcome chattering defect.In considering varying acceleration of maneuverable target,a self-adaptive regulative rule of guidance parameter was given according to experiential information.Simulation results show that this three-dimensional guidance law can hit maneuverable target at vertical attack angle with preferable robustness and adaptability for varying accelerated target.

关 键 词：滑模制导 三维制导 机动目标 攻击角 

分 类 号：V448.15[航空宇航科学与技术—飞行器设计]