摘要变推力固体火箭发动机能够实现发动机的推力可调，即根据实时需要，随时调节推力的大小和推力方向。在火箭、导弹的飞行中，通过调节推力的大小和方向可改变其飞行姿态，进而大大提高火箭、导弹等武器的作战性能。因此，变推力固体火箭发动机的研究一直受到广泛关注。本文以变推力固体火箭发动机的广泛研究为背景，对300mm变推力固体火箭发动机的装药设计和内弹道计算展开了研究。63557

本文以所给任务指标为依据，首先根据星孔装药的设计计算过程，用编程计算的方法，完成了300mm固体火箭发动机的装药设计工作，计算分析了装药的燃烧面积和通气面积随烧去肉厚的变化规律；然后在装药设计的基础上，对“单一喷管变喉径”和“多喷管可控开闭”两种结构方案的发动机，进行了内弹道的计算分析，得到了压强和推力随时间的变化规律。

毕业论文关键词：固体火箭发动机；推力调节；星孔装药设计；内弹道计算

 毕业设计说明书（论文）外文摘要

Title        The design of 300mm variable trust   solid rocket motor                               

Abstract

Variable thrust solid rocket motor can adjust the size and the direction of thrust according to the real need. On the flight of rocket and missile, their flying state can be changed by adjusting the size and direction of thrust, thereby greatly improving the combat performance of the rocket, missile and other weapons. So the research of the variable thrust solid rocket motor has been paid much attention. Based on this background, in this paper, the grain design and interior ballistic calculation of 300mm solid rocket motor is carried out.

On the basics of the given task, this paper firstly complete the grain design of 300mm solid rocket motor with the method of programming according to the process of Star-hole grain design, the calculation and analysis of the variation of combustion area and vent area with the burning of grain. And secondly, with the data of previous calculation, the paper calculate and analyze the property of interior ballistic of two kind of rocket motor, that’s motor with one variable nozzle and motor with one main nozzle and six small controllable nozzle, and get the variation curve of pressure and force with time.

Key words: Solid rocket motor, trust control, grain design, interior ballistic calculation

目   录

1 绪论 1

1.1 固体火箭发动机装药设计 1

1.2 固体火箭发动机推力调节技术 3

1.3 本文的主要研究内容 5

2 星孔装药设计的基本理论 7

2.1 星孔装药的一般类型 7

2.2 星孔装药几何参量与设计参量的关系 7

2.3 本章小结 13

3 内弹道计算的基本理论 14

3.1 零维内弹道微分方程 14

3.2 零维内弹道方程的计算 16

3.3 本章小结 21

4 星孔装药的设计计算过程 22

4.1 装药设计基本参数输入 22

4.2 星孔装药几何参数的计算过程 24

4.3 星孔装药几何参数计算结果