Extended trajectory shaping guidance law considering a first-order autopilot lag

To satisfy the terminal position and impact angel constraints, an optimal guidance problem was discussed for homing missiles. For a stationary or a slowly moving target on the ground, an extended trajectory shaping guidance law considering a first-order autopilot lag (ETSGL-CFAL) was proposed. To derive the ETSGL-CFAL, a time-to-go-nth power weighted objection function was adopted and three different derivation methods were demonstrated while the Schwartz inequality method was mainly demonstrated. The performance of the ETSGL-CFAL and the ETSGL guidance laws was compared through simulation. Simulation results show that although a first-order autopilot is introduced into the ETSGL-CFAL guidance system, the position miss distance and terminal impact angle error induced by the impact angle is zero for different guidance time.     

基于WINCE的末制导炮弹射表软件设计

介绍了激光半主动末制导炮弹武器工作原理、系统配置、运动目标的射击方式以及关键要素.给出了采用Embedded Visual C++开发环境编写具有串口通讯功能的末制导炮弹射表软件的基本思路和方法.该射表软件可完成运动目标射击诸元的快速解算,大大简化了目前解算运动目标射击诸元的繁琐步骤,该方案能够实现对运动目标的快速射击,为末制导炮弹运动目标射击方案提供参考.     

考虑动力学滞后的最优比例导引律研究

建立具有一阶动力学滞后的制导系统模型,利用最优控制理论,推导了考虑一阶制导动力学滞后的最优制导律。与经典的比例导引、增强型比例导引进行了对比研究,研究结果表明,这种最优制导律能有效降低弹道末端对加速度的要求,减少制导系统对末导时间的要求,同时也能有效降低动力学滞后对制导系统脱靶量的影响。     

脉冲力控制捷联探测器制导体制下命中精度研究

分析了脉冲力控制捷联探测器制导体制的特点,提出了在捷联制导体制下对光电探测器的要求.根据探测器的探测工作原理,建立了探测器探测目标的数学模型.数学仿真结果表明,增加探测器的象限个数可以提高弹丸的命中精度.当象限个数增加到16个时,弹丸的命中精度与线性探测器命中精度基本一致.     

Time-to-go weighted optimal trajectory shaping guidance law

For maneuvering target,the optimal trajectory shaping guidance law which can simultaneously achieve the designed specifications on miss distance and final impact angle was deduced using optimal control theory based on the time-to-go weighted function.Based on the same cost function,the closed-form solutions of the guidance law were derived when the initial displacement of missile,final impact angle,heading error and target maneuver was introduced into the lag-free guidance system.To validate the closed-form solutions,the simulation of the lag-free system was done and the simulation results exactly matched the closed-form solutions and only when the exponent is greater than zero,the final acceleration approaches to zero.     

激光末制导炮弹比例导引律性能研究

通过分析激光末制导炮弹比例导引制导律几何关系和原理,研究了激光末制导炮弹的工作原理,建立了含非线性进动的激光陀螺式导引头动力学模型和线性化弹体模型的末制导炮弹比例导引回路模型.根据制导控制系统是否利用导引头非线性进动信号作为制导信号,建立了两种制导控制系统数学模型,采用不同的制导时间以及弹体参数,进行了末制导炮弹比例导引回路仿真,对比分析了两种制导控制系统的性能.最后,针对非线性系统易引起弹体姿态较大摆动的问题,提出了在制导时间有限时的基于衰减系数的激光末制导炮弹改进制导方案.     

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...     

制导炮弹技术现状与发展方向

描述了制导炮弹研制初期典型代表的技术特点及其发展过程, 重点分析了当今世界各国制导炮弹的制导技术特点并进行了比较, 同时还介绍了逐渐走向成熟的弹道修正弹药的技术特点和发展现状. 通过对制导炮弹技术现状的分析, 总结归纳出制导炮弹未来的发展趋势.     

激光制导迫弹捕获概率与命中精度分析

介绍了脉冲力控制的制导迫弹基本工作原理,建立了捷联激光探测器的数学模型,分析了影响无控弹丸散布的主要因素,给出了在各种干扰下弹丸的最大纵向散布和横向散布。通过对脉冲发动机最大修正力能力的仿真,分析了弹丸的捕获概率和其命中精度之间的关系,最后给出了提高弹丸命中精度的方法。