Based on that two virtual target's proportional navigation laws were designed which can control the terminal azimuth of a missile, and which can also avoid the situation that the signal of control is too big at the end of propotional navigation.
由此设计出的虚拟目标比例导引律，能保证导弹以给定的落角击中目标，并有效地避免了比例导引末端控制量发散的问题。
The closed-form solutions, capable capture areas and cumulative velocity increments for three different types of proportional navigation are studied in detail.
详细研究了三种类型的比例导引规律的解析解，分析了可捕获区域，累积速度增量和工程实现方法。
In addition, a general closed-form solution to the true proportional navigation is obtained.
此外，还给出了真比例导引一般形式的封闭解。
Embaying the subject matter on attacking the key part of the target, The main results and contributions of this paper are as follows:First, it studies the structure of the air-to-air missile's guidance control system, introduce the process of guidance control system and analys the characteristics and mechanism of the guidance control system; The second, the proportional navigation have been analytical studied, the modified proportional navigation is given, that based on apprimimate conditions have been predigested.
围绕导弹末端修正控制达到杀伤目标要害部位这一主题，本论文的主要工作及贡献有以下几方面的内容：1。给出了空空导弹制导控制结构、基本框架，介绍了空空导弹的制导过程，制导系统的典型结构图，讨论了制导系统的结构方框图及其特点。
Based on proportional navigation law, the effects of commanded acceleration directions on the performance of missile miss distance are investigated.
以比例导引制导规律为基础研究了不同的指令加速度作用方向对拦截器制导性能的影响。
Finally, the computer numerical simulation of interceptions adopting optimal guidance law and proportional navigation is processed respectively.
最后，采用新型最优制导律和传统比例导引律分别进行了拦截过程的计算机数值仿真，仿真结果表明了这种新型最优制导律的有效性。
The simulation results show that the guidance law reduces the miss distance and flight time of attack missile compared with proportional navigation guidance law and fuzzy logic law.
仿真结果表明，在相同攻击时间内，对比于比例导引和一般模糊制导律，提出的自适应模糊末制导律减小了脱靶量和拦截时间。
By using modified proportional navigation law with impact angle constraints and viewing the desired rendezvous point as the target, the requirement for the terminal heading is achieved.
通过改进带终端碰撞角约束的比例导引律，将期望的会合点作为跟踪目标，实现终端航向的控制。
Based on the fuzzy logic, a new proportional navigation law is given for the navigation of air-to-air missile.
针对空空导弹的导引问题，基于模糊逻辑，提出一种新型智能导引律。
An Amendable Proportional Navigation Law for Intercepting Warhead
拦截弹头的修正比例导引律
Research on Amendatory Proportional Navigation with Variable Coefficient of Anti-Ship Missile
反舰导弹变系数修正比例导引研究
Analyses show that the optimal strategy is actually a feedback control by giving predicted miss as error signal. It is also a modified proportional navigation guidance law. Its ideal motion at each sampling instant is approximately the well-known constant bearing course.
分析表明，最优策略实质上是以零控脱靶作为误差信号的反馈控制，在每一采样时刻近似地以平行接近法作为理想运动状态，是一种修正的比例导引方法。
The variable structure proportional navigation with terminal angular constraint is utilized, and estimation about the distance rate and distance between missile and target is made, which broke the constraint that passive homing missile can't measure out the distance and distance rate.
采用带落角约束的变结构导引律，对弹目距离及距离变化率进行估计，克服被动寻的导弹不能测距的约束，同时使切换开关增益随时间自适应变化以减小俯冲过载。
The proportional navigation (PN) guidance error caused by angular noise (thermal noise) arid glint effect in radar seeker receiver is studied.
研究了雷达导引头接收机中的角噪声（热噪声）以及目标闪烁对比例导引制导精度的影响。
Strap-down seeker's detecting information is coupled with missile attitude information, hence it can't be used for proportional navigation directly.
捷联导引头测量信息中耦合有弹体姿态信息不能直接被比例导引所用。
Simulation studies show that the proposed law is superior to proportional navigation because its control energy is smaller and its guidance accuracy is better.
仿真结果表明，该导引律与常系数比例导引律相比，控制能量少，脱靶量小，命中精度高。
Simulation studies show that the proposed law in this paper is superior to proportional navigation because its control energy is smaller and its guidance accuracy is better. Application of Proportional Navigation to Rendezvous Problems ESTIMATION OF MISS DISTANCE AND GENERALIZED PROPORTIONAL NAVIGATION
仿真结果表明，应用本文的导引律在制导过程中能量消耗少，制导精度高，脱靶量小，其性能远优于常系数比例导引律
Design and Identification on Parameters of Proportional Navigation Guidance Law with Gravity Over Compensation
带过重力补偿的比例导引制导律参数设计与辨识
Based on the differential equation derived from classical mechanics, an extended proportional navigation with no restrictions on the velocities of missile and target is presented in this paper.
在传统的动力学微分方程的基础上提出了一种扩展的比例导引法，并给出了该导引规律下的相对弹道方程。
Estimation on Engagement Time of Proportional Navigation Guidance System using Approximate Time Constant The Similar Proportion Guidance Method in the Automatic Guidance System
比例导引末导时间的等效时间常数估算法