122mm20km火箭弹总体改进设计+图纸+程序

在M-21火箭弹的基础上，通过提高推进剂比冲、改进装药设计、提高装药质量、改进火箭发动机结构设计等方法对火箭弹进行总体改进设计，提高火箭弹的最大射程。使用了更高强度的材料制造燃烧室外壳，并重新设计了喷管，大幅降低了火箭发动机的消极质量。对于燃烧温度升高导致燃烧室强度下降的问题，通过改进发动机热防护设计得到了解决。采用零维内弹道模型编写压强时间曲线计算程序，得到了发动机最大压力和工作时间。发动机传热计算与强度校核的结果能保证发动机的正常工作与可靠性。空气动力计算表明火箭弹有足够的静稳定储备量。 59542
毕业论文关键词火箭弹固体火箭发动机装药设计零维内弹道
Title Overall Design of Improved 122mm 20km Rocket
Abstract Overall design of the rocket was improved based on the M-21 rocket projectile. By increasing the specific impulse of propellant, improving grain design, increasing the quality of propellant and improving solid rocket motor(SRM) structure design maximum range of the rocket projectile can be enhanced. The use of higher strength materials on combustion chamber shell manufacture and redesign of the nozzle considerably reduces the negative mass of rocket motor. The problem of the propellant imposes the higher combustion temperature which causes the decrease of strength of chamber was solved by improving heat protection design. Obtaining the maximum pressure and the working time of the motor by using zero-dimensional internal ballistic model and pressure history solver. The heat transfer calculation and strength check of the motor guarantee the normal work and reliability of the motor. Aerodynamic calculations show that the Rockets have enough static stable reserve.
Keywords rocket, solid rocket motor, grain design, zero-dimensional internal ballistic

1 绪论… 1

1.1 研究背景及意义… 1

1.2 本文主要工作 1

2 火箭弹总体设计及基本参量预定 2

2.1 战术技术指标 2

2.2 发动机装药设计… 2

2.3 基本参量预定 4

3 固体火箭发动机的结构设计 10

3.1 燃烧室设计… 10

3.2 喷管设计 14

3.3 装药固药结构设计 18

3.4 点火装置设计 19

4 内弹道分析与计算 20

4.1 零维内弹道微分方程… 20

4.2 零维内弹道计算与分析 21

5 发动机传热计算… 30

5.1 燃烧室壁传热计算 30

5.2 喷管传热计算 32

6 空气动力计算 34

6.1 弹体气动特性计算 34

6.2 尾翼气动特性计算 36

6.3 尾翼弹气动特性… 37

6.4 稳定储备量计算… 37

7 设计总结 38

结论 … 39

致谢 … 40 122mm20km火箭弹总体改进设计+图纸+程序:http://www.youerw.com/jixie/lunwen_64804.html