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摘要末制导炮弹末段制导方式有很多种，本文主要以比例导引法作为末段控制方式，研究对某大口径制导炮弹的弹道精确控制问题，阐述末制导炮弹的飞行原理和末制导率的设计原则，建立其飞行动力学模型，分析设计其末段制导率并建立末制导控制方程，数值计算分析其飞行弹道特性与末段控制效果等，为末制导炮弹的研制提供技术支撑。结果表明，过重力补偿比例导引适用于攻击非机动和机动性不大的目标，落角增大，命中点附近视线偏转和控制过载变大，能够实现对目标的大落角攻顶效应。64269
毕业论文关键字 末制导炮弹 弹道特性 重力补偿 末制导率 比例导引法
毕业设计说明书（论文）外文摘要
Title Rate of terminal guidance ammunition of the terminal guidance of design and analysis
Abstract There are many kinds of terminal guidance projectile terminal guidance way, this article mainly proportional guidance law as terminal control mode, research to a certain large caliber guided artillery ballistic accuracy control problem, this terminal guidance ammunition flight principle and the design principle of rate of terminal guidance, the flight dynamics model is established, the analysis and design its rate of terminal guidance and terminal guidance control equation, the numerical analysis of the flight trajectory characteristics and terminal control effect, etc., to provide technical support for the development of the terminal guidance ammunition. The results indicate that proportional navigation with over-gravity compensation is suitable for attacking fixed or less mobile targets，and especially for hitting the top of the target，for its angle of fall is greater and the line of sight at the point of impact has
deflection and greater overload.
Keywords Terminal guidance ammunition Ballistic characteristics The gravity compensation Rate of terminal guidance Proportional guidance law
1绪论 1
1.1课题研究背景及意义 1
1.3 末制导炮弹主要技术及特点[14] 3
1.4 末制导炮弹研究前景[13] 4
2.末制导炮弹弹道计算模型[2][4] 5
2.1 概述 5
2.2 末段制导主要研究内容 6
2.3 坐标系转换 15
2.4 各坐标系间的转换关系 17
2.5 各方位角之间的关系 20
2.6 作用在炮弹上的力和力矩 21
2.7弹道的运动方程和控制方程[3] 23
2.8 弹道设计的基本参数 25
3.无控弹道特性仿真及分析[8] 26
4.有控弹道仿真及计算分析[1] 28
5.K值变化时弹道特性及分析 32
5.1 比例系数K的选择 32
5.2 K值不同时其弹道特性分析 33
6. 重力补偿ωg变化时弹道特性及分析[12] 35
6.1 重力补偿ωg的引入