一种近空间高超声速飞行器的制导律设计与仿真

为了实现一种由助推、近空间巡航和俯冲攻击组成的高超声速飞行器攻击弹道以对付具有大机动能力的目标,采用粒子群优化方法一体化设计高超声速飞行器的固体火箭助推器和助推弹道;巡航段水平面内采用一种3维虚拟目标比例导引律,纵向平面内基于非线性系统奇异摄动理论和虚拟目标导引方法设计一种次最优组合制导律;俯冲攻击段基于随机跳变系统理论设计一种最优制导律.3维全弹道仿真结果表明所设计的制导律合理,中制导律能够有效衔接助推段和俯冲攻击段,末制导律能够有效实现攻击大机动目标的制导任务.

Design and Simulation of Guidance Law for a Kind of Near-Space Hypersonic Vehicle

To realize an trajectory composed of boost phase,cruise phase and diving attack phase for a kind of NSHSV(Near-Space Hypersonic Vehicle) to attack targets with great maneuverability,a PSO(Particle Swarm Optimization)algorithm was adopted to carry out the integration design and optimization for solid rocket booster and boost trajectory.During cruise phase,a proportional navigation guidance law based on three-dimensional virtual target was used in the latitudinal plane,and a sub-optimal guidance law based on singular perturbation theory of nonlinear system and virtual target method was developed to control the vehicle in longitudinal plane.An optimal guidance law based on stochastic jump system control theory was adopted in the diving attack phase.Three-dimensional whole trajectory simulation shows that all the guidance laws designed were suitable,and the middle guidance laws join the boost phase and diving attack phase properly,and the terminal guidance law can achieve the aim of attack great maneuverability targets effectively.