空间拦截修正比例导引律研究

基于追踪导引律和比例导引律,提出了一种新的空间拦截末制导律。通过调整两种导引法的系数决定其在导引法中的权重。考虑空间末段拦截的具体情况,在相对运动方程进行线性化处理的基础上可以得出运动方程的解析解。将非线性方程得出的数值解和这种导引律的解析解相比,仿真表明这种方法的解析解与数值解一致,且避免了最优制导复杂的解析结果。     

捷联寻的制导系统弹体追踪导引方法研究

对捷联寻的系统的简易制导方法—弹体追踪法进行全面剖析 ,解析分析了弹体追踪法对导弹速度、目标速度的约束 ,以及弹体阻尼、滞后、舵偏到攻角之间的传递系数对弹体追踪导引性能的影响。通过数学推导及应用控制理论分析与仿真 ,弹体追踪法较比例导引和速度追踪法在导引特性和打击机动目标时性能较差 ,但其成本较低 ,是一种降低制导武器成本的简易制导方法。但采用弹体追踪法时 ,导弹和目标的速度不能太大 ,当制导武器系统在形成导引误差信号存在固有滞后时 ,弹体稳定回路需要有一定阻尼 ,且舵偏到攻角之间的传递系数不能太大 ,即飞行过程中攻角要较小。     

Performance analysis of PNG laws for randomly maneuvering targets

The performance of the conventional proportional navigation guidance (PNG) law for a randomly maneuvering target is considered. By means of the Lyapunov method, it is proved that an ideal missile guided by the conventional PNG law can always intercept a target which maneuvers with time-varying normal acceleration provided that the navigation constant is sufficiently large. The authors also propose a modified PNG (MPNG) law which seems to improve the performance of the conventional PNG law at the final phase of pursuit. Simulation results demonstrate that the MPNG law demands less missile acceleration at the final phase of pursuit than the conventional PNG law     

A Qualitative Study of Proportional Navigation

This paper represents a study of the trajectories of an ideal missile homing on a target according to the proportional navigation law. A qualitative study is performed and conditions are determined which enable one to demonstrate that: 1) the missile always reaches the target regardless of the initial conditions at launch; 2) the rotational rate of the line of sight is decreasing at the pursuit end.     

Cooperative differential games guidance laws for multiple attackers against an active defense target

This paper is concerned with a scenario of multiple attackers trying to intercept a target with active defense. Three types of agents are considered in the guidance: The multiple attackers, the target and the defender, where the attackers aim to pursuit the target from different directions and evade from the defender simultaneously. The guidance engagement is formulated in the framework of a zero-sum two-person differential game between the two opposing teams, such that the measurements on the m...     

基于非线性模型的大气层内拦截弹微分对策制导律

针对新型战术弹道导弹(TBM)和智能巡航导弹等具有高机动性的拦截目标,应用控制受限的非线性对策模型,提出非线性微分对策制导律,并分析了零脱靶量拦截所容许的初始航向误差.目标和拦截弹间的相对运动是非线性的,采用传统线性化模型建立的拦截制导律会因为线性化而带来误差.提出的制导律是在保持拦截弹和目标的非线性运动学关系的基础上...     

基于比例导引的空间交会寻的段飞行任务设计

比例导引涉及的参数测量和控制手段简便,常被用作空间拦截的制导算法。基于该制导算法,在相对运动参数测量条件较弱的情况下,对空间交会对接寻的段飞行任务进行了设计。采用C-W制导算法,对寻的段飞行任务的标称轨道进行了设计。推导了基于固定推力发动机的比例导引轨道控制模型,并利用该模型对寻的段轨道进行了控制。通过仿真计算验证了所给出的比例导引模型的有效性。     

弹道导弹中段防御的拦截窗口分析

根据弹道导弹中段飞行近似为二体运动的特点，应用二体运动理论分析了弹道导弹中段防御的拦截窗口。假设最低拦截点由拦截弹末段寻的飞行正常工作的最低地面高度决定，最高拦截点由拦截弹投射能力决定，给出了根据当前时刻弹道导弹位置和速度求解拦截窗口的算法。对采用最小能量弹道飞行的弹道导弹，给出了根据射程求解拦截窗口的算法，并对不同射程的最小能量弹道，给出了求解拦截窗口的算例。     

Generalized guidance law for homing missiles

The concept of a generalized guidance law is presented, and the closed-form solution for a homing missile pursuing a maneuvering target according to generalized guidance laws is given. It is shown that the guidance laws appearing in the literature are merely special cases of the one proposed by the authors. The derived generalized forms of capture area, missile acceleration, and homing time duration that are derived provide insight into the performance of the guidance laws being considered and lead to the discovery of new ones. The problem of finding a nonlinear optimal guidance law for a homing missile with controlled acceleration, applied so as to capture a maneuvering target with a predetermined trajectory while minimizing a weighted linear combination of time of capture and energy expenditures, is solved in closed form. The derived optimal control law is equal to the LOS (line of sight) rate multiplied by a trigonometric function of the aspect angle. Numerical simulation shows that the resulting guidance law appears to yield a significant advantage over true proportional navigation     

Adaptive block dynamic surface control for integrated missile guidance and autopilot

A novel integrated guidance and autopilot design method is proposed for homing missiles based on the adaptive block dynamic surface control approach. The fully integrated guidance and autopilot model is established by combining the nonlinear missile dynamics with the nonlinear dynamics describing the pursuit situation of a missile and a target in the three-dimensional space. The integrated guidance and autopilot design problem is further converted to a state regulation problem of a time-varying nonlinear system with matched and unmatched uncertainties. A new and simple adaptive block dynamic surface control algorithm is proposed to address such a state regulation problem. The stability of the closed-loop system is proven based on the Lyapunov theory. The six degrees of freedom (6DOF) nonlinear numerical simulation results show that the proposed integrated guidance and autopilot algorithm can ensure the accuracy of target interception and the robust stability of the closed-loop system with respect to the uncertainties in the missile dynamics.     

飞行器比例导引综述

基于导弹制导和机器人控制等领域，对追踪／截获动目标——导引问题的研究，综观几十年来大量国内外研究成果，系统分析与比较了各种比例导引律的含义、特点与性能。指出纯比例导引及其改进是非常有效的导引方式，可以有效地用于机动目标追踪／截获导引，能为相关领域机动目标导引问题的研究，包括战斗机追踪导引设计提供参考。     

三维RTPN的追踪导引研究

描述三维RTPN导引的模型是超越非线性微分方程组，不易求解．常规的方法是进行线性化。通过坐标系的变换和引入辅助向量获得了解析的捕获域和截获时间，并在三维空间内对这种追踪导引过程进行了仿真验算。理论分析和仿真表明：所设计的追踪导引律，能使整个追逃过程是在一个由初始相对距离和初始相对速度确定的平面内进行；当导弹采用RTPN导引，目标分别以IPN、RTPN逃逸和非机动飞行时，拦截TPN逃逸导引的目标能量消耗大，截获时间长，捕获域小。     

翼伞系统在未知风场中的归航控制

翼伞系统在未知风场中执行归航任务时,需获得风场的大小和方向信息,以便在归航过程中利用或者消除风场的影响。为实现翼伞系统在未知风场中精确归航与逆风雀降着陆,首先提出一种利用全球定位系统(GPS)定位数据和最小二乘法在线辨识风向和风速的方法,然后将风场中平均风的影响在轨迹规划中予以考虑,设计分段归航路径;将突风作为外界干扰,在轨迹跟踪过程中由线性自抗扰控制(LADRC)器进行观测和补偿。最后通过仿真实验验证了本文所提出的归航控制方法对于提高翼伞系统在未知风场中的归航精度和抗风能力有重要意义。     

某型战机追踪导引研究

基于对广泛应用与研究的各种比例导引律的比较与分析，提出应用纯比例导引实现战机追踪导引的方法，并通过追踪以不同机动方式逃逸的飞行目标的仿真，说明了它的正确性与可行性。     

A Lyapunov-like approach to performance analysis of 3-dimensionalpure PNG laws

The 3-dimensional PPNG (pure proportional navigation guidance) law was proposed about forty years ago, but its performance has been analyzed only on the basis of the linearized trajectory equations, which are valid locally around the collision course. We take into full account the nonlinear dynamic characteristics of pursuit situation in the 3-dimensional space to analyze the performance of the 3-dimensional PPNG law more rigorously. We prove that a missile guided by the 3-dimensional PPNG law can always intercept a target maneuvering randomly in the 3-dimensional space if 1) the target acceleration varies with a known bound, 2) the navigation constant is selected large, and either 3a) the initial heading error is small or 3b) the missile keeps the head toward the target during flight. We also propose a modified PNG law, which seems to exhibit better performance at the final phase of pursuit than the conventional PPNG law. We introduce a Lyapunov-like method that proves to be a very powerful tool in obtaining our results     

Counterweapon Aiming for Defense of a Moving Target

Previous correspondence [1, 2] considered the problem of defending moving target by means of a counterweapon launched from the target to intercept the attacker, deriving relations between attacker-target ranges at counterweapon launch and at intercept of the attacker, and the speed capabilities of the counterweapon. The present correspondence derives the location of the intercept point in target-centered coordinates (the counterweapon aimpoint), analyzes the complicated behavior of range and bearing settings with attack geometry, and formulates the relations for determining whether any given attack can be countered under restrictions on speed or angle at which the counterweapon may be fired. Exhaustive analysis is not attempted. A simplified treatment portrays kinematic conditions which must exist if the target is to counter the attack before the target is impacted by the attacking vehicle, through the use of examples.     

目标机动对反舰导弹目标捕捉概率的影响

根据反舰导弹末制导雷达捕捉目标和舰艇机动的原理,建立了目标机动条件下末制导雷达捕捉目标的计算模型,仿真结果显示,对中远程反舰导弹而言,目标机动对目标捕捉概率有显著影响。     

基于目标距离的末制导雷达最优搜索图模型

深入研究了反舰导弹末制导雷达目标捕捉模型,以末制导雷达第一方位搜索周期捕捉概率和全程搜索捕捉概率为约束条件,建立了以末制导雷达第一方位搜索周期扫描面积为目标函数的末制导雷达最优搜索图求取模型,解决了基于目标距离的末制导雷达最优搜索图参数求取问题,并利用多项式拟合,得到了最优搜索图参数工程实现方法,该方法易编程、计算量小、占用内存少,是一种简单、实用的中远程反舰导弹末制导雷达最优搜索图参数实现方法。     

助推段防御比例导引法研究

基于助推段防御和比例导引法,分析了拦截弹与目标导弹的相对运动关系并给出了比例导引方程;采用差分法分析了拦截弹与目标导弹的位置关系、构建了数学模型并推导了拦截弹的差分方程;以拦截时间和拦截弹道为研究对象,分析了拦截弹的速度和比例系数对拦截时间和拦截弹道的影响,并对比例导引法的拦截弹道进行了三维仿真。仿真结果表明,助推段防御使用变系数比例导引法,可有效缓解拦截时间与拦截弹机动性之间的矛盾。     

Closed-form solution of pure proportional navigation

The closed-form solution of the equations of motion of an ideal missile pursuing a nonmaneuvering target according to the pure proportional navigation law is obtained as a function of the polar coordinates for all real navigation constants N⩾2. The solution is given in the form of a uniformly convergent infinite product which reduces to a product of a finite number of factors if the navigation constant is a rational number. The solution is discussed, and necessary and sufficient conditions are stated for vanishing, bounded, and unbounded missile acceleration in the final phase of pursuit