摘要
针对某些导弹具有末端落角的作战要求,设计了一种带落角约束的圆弧一体化导引律。首先在二维平面内对圆弧轨迹进行几何分析,得出了任意两点之间都存在给定落角的唯一圆弧轨线。据此推导出圆弧导引的状态方程。然后在小攻角假设的前提下,将导弹在俯仰平面内的运动学模型线性化,并建立俯仰平面内的导弹制导控制的一体化模型。最后将其化为了具有一般形式的含不确定量的级联系统,采用自适应滑模反演的设计方法保证了系统状态的稳定性。仿真结果表明,带落角约束的一体化圆弧末导引律不仅满足高精度的制导要求,同时也能够满足对末端落角的控制要求。
In order to meet the requirements of some missiles with a certain impact angle accurately,the integrated design of circular navigation guidance law with terminal impact angular constraint is proposed.Firstly,the geometrical relationship of the circular trajectory in a two-dimensional plane is analyzed. And the conclusion is that only if impact angle is given,the line between two of any points which have a unique circular trajectory is drawn. Based on the above,the state equation of circular navigation guidance law is deduced. Under the assumption of small attack angle,the kinematics model of the missile in the pitch plane is linearized and the integrated model of the missile in the pitch plane is established. Then the integrated model is further changed into a general form of cascaded systems with unknown uncertainties. Finally,an adaptive backstepping control method based on sliding mode control is presented for the nonlinear systems,which ensures the stability of all the states of the system. The simulation results show that the integrated design of circular navigation guidance law with terminal impact angular constraint not only meets the requirements of high-precision guidance,but also meets the requirements of the terminal falling angle.
作者
范军芳
王刚
Fan Junfang;Wang Gang(Beijing Key Laboratory of High Dynamic Navigation Technology, Beijing Information Science & Technology University,Beijing 100101,China)
出处
《战术导弹技术》
北大核心
2018年第6期70-77,共8页
Tactical Missile Technology
基金
国家自然科学基金(61201417)
北京市科技新星计划(xxjh2015B041)
北京市委组织部青年拔尖人才(2015000026833ZK03)
北京市教委青年拔尖人才计划(CIT&TCD201504055)
关键词
自适应反演控制
一体化设计
圆弧导引律
落角约束
末制导
adaptive backstepping control
integrated design
circular navigation guidance
impact angle constraint
terminal guidance
