122mm20km火箭弹总体改进设计+图纸+程序
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
目 次
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
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