摘要制导火箭弹因为是在常规火箭弹的基础上制作的，而常规火箭弹的价格相对廉价，从而大大降低了制导火箭弹的价格，显得经济实用。并且没有导弹那么高的技术要求，没有太多的使用限制条件的优点受到国内外广泛的关注，很多学者都对制导火箭弹相对技术进行了研究，其中制导控制问题成为了重中之重。本文围绕制导火箭弹末制导制导律设计方法进行了初步的研究，所做的研究内容归纳如下：首先推导了制导火箭弹在纵向平面内的质心运动方程组，为制导火箭弹末制导律设计奠定了基础。其次，针对经典的比例导引法无法满足制导火箭弹落点速度方向，落角约束的问题，提出了采用带落角约束的最优制导律解决问题。最后，通过制导火箭弹末制导段的运动仿真分析，研究带有落角约束的最优的末制导规律是否能够满足制导精度和落角约束的要求，并对末制导段制导律参数进行设计。设计制导火箭弹的末制导参数 和 时，应该保证制导系统在满足战术要求的落点精度与落角约束的同时，还具有较强的自适应性。研究结果也说明该末制导段制导律参数设计方法可行，对制导火箭弹末制导控制系统参数设计有着重要的参考作用。23404
关键词 制导火箭弹 控制系统 最优制导律 参数设计
毕业设计说明书（毕业论文）外文摘要
Title Terminal Guidance of Guided rockets control system Design parameters
Abstract
As the guided rocket is based on the conventional rocket production, Conventional rockets’ price is relatively cheap,Thus greatly reducing the price of guided rockets, It seem economical and practical.it has no technical requirements so high like a missile, It has the advantage of having not many using restrictions and gets widespread attention at home and abroad,Many scholars are on the guided rocket technology were studied,Guidance and control problem which has become a top priority.This paper focuses on guided rockets terminal guidance’s guidance law for a preliminary design research.Research contents done summarized as follows.
First deduced guided rockets the centroid motion equations in the longitudinal plane.For guided rocket terminal guidance law laid the foundation.The classic proportional guidance law does not meet the impact point velocity direction and terminal angular constraint requirements,
Proposed uses with terminal angular constraint to solving the problem.
Whether optimal terminal guidance law with terminal angular constraint can meet the requirements of guidance accuracy and angular constraint by guided rockets terminal guidance’s motion simulation analysis.And terminal guidance guidance law design parameters.Design guided rockets terminal guidance parameters and ,Should ensure that the guidance system to meet the requirements of the tactical placement accuracy terminal angular constraint simultaneously but also has strong adaptability.Research results also indicate that the terminal guidance parameter design method of guidance law is feasible.Has important reference for guided rocket terminal guidance control system design parameters.
Keywords Guided rockets Control Systems The optimal guidance law
parameter design
目 录
1 绪论 1
1.1 课题研究背景 1
1.2 课题研究意义 1
1.3 国内外研究现状 1
1.4 本文主要工作 3
2 制导火箭弹末制导弹道模型 3
2.1 坐标系的定义及坐标系转换 3
2.2 建立弹道方程组 9
2.3 本章小结 10
3 制导火箭弹末制导律设计 10 制导火箭弹末制导控制系统参数设计:http://www.youerw.com/zidonghua/lunwen_16437.html