122mm40km火箭弹总体设计+程序+图纸
时间:2020-11-15 09:46 来源:毕业论文 作者:毕业论文 点击:次
| 针对现代战争的战场需求，为适应现代战争的远程化，结合俄罗斯122mm20km BM-21 火箭弹的设计资料，采用比冲更高的推进剂，比强度更高的材料做燃烧室壳体，提出122mm40km 火箭弹的总体设计方案,内容涉及装药设计、弹道计算、固体火箭发动机结构设计、弹体气动等多方面。首先根据任务书进行了基本参量的预定，进行初步的装药设计和弹道计算，预估弹重以及装药质量。其次根据初选参量所选定的燃烧室壳体材料，估算燃烧室壁厚，并估算被动段质量。再次根据计算结果重新进行装药计算和外弹道计算，反复修正初选参量时预估的数据，进行了燃烧室与喷管的结构设计，对弹体的气动特性进行了计算并讨论了弹体的稳定性。最后编程计算了发动机的内弹道，得到了内弹道压强时间曲线图。计算结果表明本方案的设计满足任务书的要求。59532 毕业论文关键词 火箭弹 装药设计 燃烧室设计 内弹道计算 Title The integrated Design of 122mm 40km Rocket Projectile Abstract Concerning the requirement of the modern war battlefield , in order to adapt to the modern war of the remote , combining the data of the BM-21 rocket projectile designed by Russia ,the project about integrated design of 122mm 40km rocket projectile that use higher specific impulse of propellants and higher specific strength material for combustion chamber shell is put forward .It involves propellant loading design ,the ballistic calculation ,the structure design of solid rocket motor and so on . Firstly, according to the specification the basic parameter is reserved .The preliminary propellant loading design and trajectory calculation is given. Besides the weight of rocket projectile and the quality of propellant is estimated .Secondly , according to the primary combustion chamber shell material parameters selected , estimate the wall thickness of combustion chamber . Then design the structure of combustion chamber and nozzle and estimate the quality of passive segment. Again according to calculation results design the propellant loading and calculate the ballistic trajectory anew .Finally the aerodynamic characteristics of projectile are calculated and the stability of the projectile is discussed. The calculation results show that this scheme meets the requirements of the specification. Keywords rocket projectile, propellant design ,combustion chamber design ,internal ballistic calculation 目次 1绪论1 1.1火箭武器概述1 1.2火箭武器发展简况及特点1 1.3课题的意义3 1.4任务设计指标与设计思路的简述3 2122mm40km火箭弹基本参量预定4 2.1装药初步设计与燃烧室壁厚的预估5 2.2估算全弹重9 2.3外弹道初步分析与计算9 2.4本章小结11 3固体火箭发动机装药设计11 3.1推进剂型号与装药药型的选择12 3.2星孔装药的装药设计13 3.3装药的包覆16 3.4本章小结16 4固体火箭发动机的结构设计17 4.1燃烧室设计18 4.2喷管设计23 4.3点火装置设计28 4.4本章小结31 5空气动力计算31 5.1弹体气动特性计算31 5.2本章小结35 6内弹道的计算35 6.1零维内弹道计算与分析35 6.2本章小结39 结论与展望40 致谢42 参考文献44 附录A内弹道源程序45 (责任编辑：qin) |