火星进入舱开伞弹伞载荷动力放大系数研究与试验验证  

Study and Experimental Verification on Dynamic Magnification Factor of Parachute Inflation and Ejection Loads of Mars Entry Vehicle

作　　者：王刚[1] 杨昌昊[1] 祁玉峰[1] WANG Gang;YANG Chang-hao;QI Yu-feng(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《宇航学报》2021年第11期1355-1364,共10页Journal of Astronautics

摘　　要：首先推导了单自由度系统在矩形和半正弦波形脉冲冲击下响应谱动力放大系数与脉冲作用时间的理论解析公式,然后采用有限元显示冲击动力学分析方法,分析了火星探测器进入舱进入过程中开伞弹伞低频大冲击载荷的载荷波形、脉冲作用时间以及结构阻尼对进入舱主结构动力放大系数的影响;最后介绍了开伞载荷悬吊冲坠模拟冲击动载试验和弹伞载荷真实弹伞筒冲击动载试验。分析与试验结果表明:冲击作用时间在1 ms以下时,结构衰减效应明显,冲击作用时间大于5 ms后,动力放大系数同波形下趋于稳定;开伞载荷由于指数型前沿上升时间较长,动力放大系数基本为1;弹伞载荷上升前沿较陡,矩形前沿波放大倍数在1~2倍之间。上述研究可为火星探测器进入舱结构载荷条件的确定提供参考。Firstly,the analytical formulas of the dynamic magnification factor with the pulse time of the response spectrum of a single-degree-of-freedom system under the rectangular and half-sine pulse are derived.Then the parachute inflation and ejection low-frequency high shock load dynamic simulation model of the Mars entry vehicle is built based on abaqus explict dynamics,and the influence of the shock load shape,load time and load damping are analyzed.Finally,the experiments of the opening parachute load suspension impact dynamic load and the parachute load real parachute impact dynamic load are carried out.The results show that the structure responds decline when the shock load time is less than 1 ms,and the static equivalence load becomes steady when the load time is longer than 5 ms;the dynamics equivalence load of the parachute inflation is about 1 time than static because of the smooth time wave,but the parachute ejection’s is about 1~2 times than static due to the steep rectangle wave.

关 键 词：冲击 火星进入 开伞弹伞 动力放大 

分 类 号：V414[航空宇航科学与技术—航空宇航推进理论与工程] V416