基于气囊缓冲方式的重复使用运载火箭回收着陆仿真分析与试验验证  

Simulation Analysis and Test Verification of Reusable Launch Vehicle Recovery Landing Based on Airbag Buffer

作　　者：徐振亮[1] 邓思超 吴胜宝[1] 汪小卫[1] 何欢[2] Xu Zhen-liang;Deng Si-chao;Wu Sheng-bao;Wang Xiao-wei;He Huan(China Academy of Launch Vehicle Technology,Beijing,100076;Nanjing University of Aeronautics&Astronautics,Nanjing,210016)

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]南京航空航天大学,南京210016

出　　处：《导弹与航天运载技术》2022年第3期8-11,59,共5页Missiles and Space Vehicles

基　　金：国家自然科学基金资助项目(52005514)。

摘　　要：运载火箭重复使用是降低发射服务成本的重要技术途径之一,重复使用运载火箭会经历多次回收着陆载荷,是影响箭体结构重复使用性能的重要因素。设计了排气式气囊着陆缓冲方案,建立了运载火箭子级有限元模型,基于气囊排气及缓冲理论真实模拟了气囊排气爆破过程和气固耦合缓冲过程,通过开发二次程序完成了重复使用运载火箭子级回收软着陆瞬态动力学冲击仿真。获得了过载随竖直着陆速度和水平着陆速度变化的响应面,找到了过载指标、应力指标满足设计要求情况下的最大竖直着陆速度。以仿真结果为输入指导了重复使用运载火箭子级着陆试验,仿真结果与试验结果吻合,验证了排气式气囊着陆仿真方法和参数设置的正确性。Reuse of launch vehicle is one of the important technical ways to reduce the cost of launch service.The reusable launch vehicle will experience multiple landing loads,which is an important factor affecting the repetitive performance of rocket boy structure.A airbag landing buffer scheme is designed.Finite element model of launch vehicle sub stages are established.Based on the theory of airbag exhaust and buffer,the blasting process of airbag exhaust and the gas-solid coupling buffer process are simulated.Transient dynamic impact simulation of soft landing for reusable launch vehicle sub stage recovery is completed by developing secondary program.Response surface of overload varying with vertical and horizontal landing velocities is obtained.The maximum vertical landing speed is found when overload index and stress index meet the design requirements.Sub stage landing test of reusable launch vehicle is guided by simulation results.The simulation results are in good agreement with the test results.The validity of simulation method and parameter setting for exhaust airbag landing areverified.

关 键 词：运载火箭 回收 着陆仿真 试验验证 

分 类 号：V421.3[航空宇航科学与技术—飞行器设计]