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300mm变推力固体火箭发动机的装药设计和内弹道计算

时间:2025-05-17 20:57来源:99795
以喷管可调的复杂装药发动机为研究对象,对固体火箭发动机的星孔装药设计以及变推力和变矢量发动机的内弹道计算进行了研究

摘要:变推力固体火箭发动机能发动机推力的方向及大小即时按实际需求调整。在火箭、导弹的飞行中,采用这样的发动机能随时改变飞行姿态,进而大大提高火箭、导弹等武器的作战效能。因此,各国军方和航空航天部门对有关变推力固体火箭发动机的研究一直有着浓厚的兴趣。本文以变推力固体火箭发动机为研究对象,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探讨。

本文以所给任务指标为依据,用编程计算的方法首先根据星孔装药的参数进计算,完成了 300mm 固体火箭发动机的装药设计工作,计算分析了推进剂烧去肉厚与装药的燃烧面积和通气面积的变化规律;然后在装药设计的基础上,对“变喉径单一喷管”和“开闭可控多喷管”两种结构的发动机方案,进行了内弹道的计算分析,得到了工作压强和推力随时间的变化规律。

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 thrust-adjustable    solid rocket motor                               

Abstract

Adjustable 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 adjustable 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, which is a single adjustable nozzle rocket and motor with one main nozzle and six smaller controllable nozzle,the variation curve of pressure and force with time was gained during multiple calculation and tests.

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

目次

1 绪论 1

1.1 发动机装药设计 1

1.1.1 装药设计概述 1

1.1.2 常用推进剂和药型的比较 1

1.2 固体火箭发动机的推力调节技术 2

1.2.1 推力大小调节技术 2

1.2.2 推力矢量控制技术 3

1.3 本文的主要研究内容 5

2 星孔装药的基本设计 6

2.1 星孔装药的基本参数 6

2.2 计算星孔装药几何参量的程序模块 11

2.3 本章小结 15

3 内弹道微分方程的计算 16

3.1 零维内弹道微分方程 16

3.1.1 零维内弹道计算时的基本假设 16

3.1.2 零维内弹道计算的基本方程 300mm变推力固体火箭发动机的装药设计和内弹道计算:http://www.chuibin.com/jixie/lunwen_205537.html

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