Kinetic Optimal Midcourse Guidance Law for Air-to-Air Missiles

A new kinetic optimal midcourse guidance law is derived based on optimal control formulation. A new simplified Runge-Kutta grade numerical method is proposed t o find the optimal trajectory. Real data of an air-to-air missile is referred to for comparing results using the kinetic optimal midcourse guidance law with t hose under both the kinematic optimal guidance law and singular perturbation sub -optimal guidance law, wherein the latter two laws are modified in this paper b y adding a vertical g-bias comma...     

空间拦截系统的末制导律

研究空间拦截中导弹的脱靶量，分析影响脱靶量的因素，用非线性精确线性化理论求取非线性末制导律．     

Homing Guidance Law with Falling Angle and Flying Time Control

In this paper, a new homing guidance method is used to control the flying time and falling angle for guided missiles. Through this approach, it finds the approximate solution to the quadratic equation of time-to- go, which is used for the formula derivation of the flying time control command. In this guidance law design, the acceleration rate control command is adopted. The guidance law is composed of a PN guidance command and a flying time control command. Firstly, it obtains a desired falling angle with accurate guidance. Secondly, it introduces to satisfy the constraint of flying time. The flying time control requires an assumption on the future evolution of missile, which is called time-to-go. To cope with the time-varying speed of missiles, a method of compensating the estimation of time-to-go is presented. The new guidance law is evaluated by using a simulation of typical terminal guidance for rocket-propelled torpedo. The simulation results show that the guidance achieves excellent control performance and exhibits insensitivity to initial trajectory parameter over a widen flight envelope.     

Terminal Angular Constraint Integrated Guidance and Control for Flexible Hypersonic Vehicle with Dead-Zone Input Nonlinearity

This paper presents an integrated guidance and control model for a flexible hypersonic vehicle with terminal angular constraints. The integrated guidance and control model is bounded and the dead-zone input nonlinearity is considered in the system dynamics. The line of sight angle,line of sight angle rate, attack angle and pitch rate are involved in the integrated guidance and control system. The controller is designed with a backstepping method, in which a first order filter is employed to avoi...     

电视制导无人机导引律研究

电视制导无人机是目前国际上一项热门研究课题，它不仅要求攻击精度高，而且要求命中目标时姿态最佳，以达到最大毁伤效果，同时电视导引头采用小型化结构，其框架角受到限制，容易发生碰框，影响对目标的精确跟踪。鉴于以上因素，提出一种修正比例导引律——在纵向采取考虑无人机命中角约束和俯仰框架角约束的修正比例导引律，在横侧向采取考虑方位框架角约束的修正比例导引律。仿真结果表明提出的导引规律能满足电视制导无人机的战技指标要求。