火箭驱动释放装置内弹道过程仿真  

Interior Ballistic Process for Pyrotechnically Rocket Actuated Separation Devices

作　　者：徐汉中[1] 焦胜海 张君发 潘文[1] 吕蒙[1] Xu Han-zhong;Jiao Sheng-hai;Zhang Jun-fa;Pan Wen;Lyu Meng(Beijing Institute of Space Long March Vehicle, Beijing, 100076)

机构地区：[1]北京航天长征飞行器研究所,北京100076

出　　处：《导弹与航天运载技术》2018年第6期78-82,共5页Missiles and Space Vehicles

摘　　要：针对发射筒侧壁开孔的特殊火箭驱动释放装置,根据实际释放装置结构及工作原理,利用热力学和气体动力学理论,建立了发射过程中的经典内弹道模型;根据模型编制了计算程序,利用计算结果对比分析了在大气和真空两种环境下筒内发射和筒外火箭助推整个驱动释放过程的内弹道参数的变化规律。仿真结果表明:计算结果与试验结果基本吻合,共同反映了筒内附加弹射力在真空环境下对物体最终释放初速有较大影响;火箭驱动释放仿真模型的建立,为后续工程应用提供了理论分析手段。The classical interior ballistic model of Pyrotechnically Rocket Actuated Separation Devices was given on the basis of its mechanism and working principle.According to the model,the computer program was developed.The variation regularity of the pressure in low pressure chamber during the actuated object in the launching tube and the velocity in the whole actuating process were analyzed.Calculation results agree well with the experimental results and both reveal the final velocity of actuated object in the atmosphere higher in vacuum.

关 键 词：火工释放装置 火箭驱动 内弹道方程 数值计算 

分 类 号：TJ761.7[兵器科学与技术—武器系统与运用工程]