单兵制导火箭弹制导控制系统参数设计

本文对某型号单兵火箭弹受力及力矩情况进行了分析，通过运动学和动力学研究，推导出单兵火箭弹三自由度弹道模型，且对弹道曲线进行了仿真。然后，利用比例导引法对制导律进行了设计，求出了相关参数，并进行了动态特性分析。针对动态特性分析出的较差的动态品质，利用控制系统进行控制，通过控制系统参数设计，改善了系统的相关品质。最后，仿真结果指出，控制系统满足相应的要求。

Title      The parameters’ design of Inpidual guided    Rocket’s  guidance and control system
Abstract
Under the demand of modern warfare, more and more high requirements is used to hit the target precisely.As a powerful ground weapon,inpidual antitank rocket is unshakable.But to adapt to the modern warfare demand, it is necessary to study inpidual guided antitank rockets,through the control of the guidance and control system,the inpidual antitank rocket can effectively improve stability. 源`自*六)维[论*文'网www.lwfree.cn
This paper analyzes a certain type of inpidual antitank rocket’s force and torque and deduces the inpidual antitank rocket with three degrees of freedom trajectory model through the study of kinematics and dynamics,and simulates the ballistic curves.Then, using the proportional guidance method for the design of guidance law, the relevant parameters are calculated and the dynamic characteristics are analyzed.According to the analysis of the dynamic characteristics of the poor dynamic quality, using control system to control, through the design of the control system parameters, improve the system quality.Finally,the simulation results show that the control system can meet the corresponding requirements.
Keywords  inpidual antitank rocket    hit rate    guidance law  dynamic characteristics    control system

1  绪论    1
1.1  课题背景    1
1.2  国内外研究现状    1
1.3  本文主要工作    4
2  单兵制导火箭弹弹道模型    5
2.1  坐标系的定义及其转换    5
2.2  研究对象受力分析    8
2.3  单兵制导火箭弹数学模型    12
2.4  标准气象条件    16
2.5  本章小结    17
3  制导火箭弹制导律设计    18
3.1  制导律的选择    18
3.2  制导律参数设计    18
3.3  本章小结    24
4  制导火箭弹控制系统参数设计    25
4.1  动态特性分析    25

4.2  控制方案设计    31
4.3  控制系统参数设计    31
4.4  本章小结    36
5  单兵制导火箭弹仿真分析    37
5.1  仿真流程    37
5.2  仿真条件的设置    37
5.3  仿真结果分析    38
5.4  本章小结    44

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