ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Buffering characteristics and parameter influence of launch canister of space launch devices
Received date: 2025-05-30
Revised date: 2025-06-18
Accepted date: 2025-07-11
Online published: 2025-07-15
Supported by
National Natural Science Foundation of China(52102436);China Postdoctoral Science Foundation(2020M681615);Natural Science Foundation of Shanghai(23ZR1462700);Postgraduate Research and Practice Innovation Program of Jiangsu Province(KYCX23_0508);National Key Laboratory Open Fund for Strength and Structural Integrity(ASSIKFJJ202304006)
To address the issues of strong impact force and significant vibration at the launch canister of a space launch device， this study proposes a launch canister energy-absorbing structure. The aim is to reduce the impact force generated by the projectile at the launch canister and mitigate launch canister vibration， thereby further enhancing launch accuracy. An internal ballistic model served as the loading condition to establish a launch dynamics model under varying loads. Both simulations and experiments demonstrate that the deformed state of the energy-absorbing ring consistently exhibited a petal-shaped inward deformation. The deformation height error was 14.23%， the recoil force peak error was 0.30%， the forward impact force peak error was 10.72%， the velocity error was 4.14%， and the acceleration peak error was 4.88%， verifying the model's accuracy. Based on this validated model， the influence of key structural parameters on the forward impact force and pitch displacement was analyzed. Results indicate that an energy-absorbing ring inclination angle of 35° yields optimal energy absorption. At this angle， the peak forward impact force is reduced by 9.22% compared to the pre-optimized state， and the minimum launch tube pitch displacement amplitude is 3.45 mm， representing a 1.71% reduction. When the collision contact surface radius between the energy-absorbing piston and the energy-absorbing ring is 7.5 mm， the peak forward impact force decreases by 6.83% compared to a radius of 5.5 mm， with the change in radius having a relatively minor effect overall. This research provides theoretical support and practical engineering reference for the design of high-efficiency space debris removal payloads.
Zihao WANG , Wanxiang WANG , Chenglong WU , Junyu SHAN , Shuai YUE , Zhonghua DU , Lei ZHAO . Buffering characteristics and parameter influence of launch canister of space launch devices[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2026 , 47(4) : 232328 -232328 . DOI: 10.7527/S1000-6893.2025.32328
| [1] | 龚自正， 赵秋艳， 李明， 等. 空间碎片防护研究前沿问题与展望［J］. 空间碎片研究， 2019， 19（3）： 2-13. |
| GONG Z Z， ZHAO Q Y， LI M， et al. The frontier problem and prospect of space debris protection research［J］. Space Debris Research， 2019， 19（3）： 2-13 （in Chinese）. | |
| [2] | 郑世贵， 闫军. 空间碎片防护需求与防护材料进展［J］. 国际太空， 2014（6）： 49-53. |
| ZHENG S G， YAN J. Requirements of space debris protection and progress of protective materials［J］. Space International， 2014（6）： 49-53 （in Chinese）. | |
| [3] | ZHOU M Q， JIANG X Q， ZOU C L. On-orbit placement optimization of proximity defense shield for space station［J］. Acta Astronautica， 2022， 198： 295-308. |
| [4] | XIA X， SUN Y P， SUN J L. Dynamics and experiments of a tendon-actuated flexible robotic arm for capturing a floating target［J］. Defence Technology， 2025， 47： 216-241. |
| [5] | TSUNO K， WADA S， OGAWA T， et al. Laser ablation induced impulse study for removal of space debris mission using small satellite［J］. Applied Physics A， 2022， 128（10）： 932. |
| [6] | WANG R L， LIU W， YAN R D， et al. Refined study of space debris collision warning techniques for LEO satellites［J］. Journal of Space Safety Engineering， 2020， 7（3）： 262-267. |
| [7] | ZHU W L， PANG Z J， HE J， et al. Tensile experiment based nonlinear tether element model for tethered space net［J］. Acta Astronautica， 2025， 228： 643-651. |
| [8] | BOTTA E M， MILES C， SHARF I. Simulation and tension control of a tether-actuated closing mechanism for net-based capture of space debris［J］. Acta Astronautica， 2020， 174： 347-358. |
| [9] | HUANG W C， ZOU H W， LIU H W， et al. Contact dynamic analysis of tether-net system for space debris capture using incremental potential formulation［J］. Advances in Space Research， 2023， 72（6）： 2039-2050. |
| [10] | ZHU W L， PANG Z J， HE J， et al. Dynamic modeling and prediction of post launch rebound mechanism of tethered space net［J］. Applied Mathematical Modelling， 2025， 140： 115861. |
| [11] | SHI W H， YUE S， LIU Z， et al. Dynamics analysis and experimental validation of the aluminum honeycomb buffer in the tether-net launcher［J］. Advances in Space Research， 2022， 70（11）： 3405-3417. |
| [12] | BOTTA E M， SHARF I， MISRA A K. Contact dynamics modeling and simulation of tether nets for space-debris capture［J］. Journal of Guidance， Control， and Dynamics， 2016， 40（1）： 110-123. |
| [13] | HUANG W C， HE D Z， LI Y B， et al. Nonlinear dynamic modeling of a tether-net system for space debris capture［J］. Nonlinear Dynamics， 2022， 110（3）： 2297-2315. |
| [14] | LINSKENS H， MOOIJ E. Tether dynamics analysis for active space debris removal［C］∥AIAA Guidance， Navigation， and Control Conference. Reston： AIAA， 2016. |
| [15] | AGLIETTI G S， TAYLOR B， FELLOWES S， et al. The active space debris removal mission RemoveDebris. Part 2： in orbit operations［J］. Acta Astronautica， 2020， 168： 310-322. |
| [16] | 史文辉， 岳帅， 刘洲， 等. 适应火工装置冲击环境的铝蜂窝缓冲特性研究［J］. 振动与冲击， 2024， 43（5）： 292-301， 314. |
| SHI W H， YUE S， LIU Z， et al. Aluminum honeycomb buffering characteristics adapted to impact environment of pyrotechnic device［J］. Journal of Vibration and Shock， 2024， 43（5）： 292-301， 314 （in Chinese）. | |
| [17] | 潘忠文， 谭祖玮， 张新宇， 等. 航天火工冲击环境预示技术研究现状与展望［J］. 宇航总体技术， 2025， 9（1）： 1-9. |
| PAN Z W， TAN Z W， ZHANG X Y， et al. Research status and prospects on aerospace pyroshock environment prediction techniques［J］. Astronautical Systems Engineering Technology， 2025， 9（1）： 1-9 （in Chinese）. | |
| [18] | 宋杰， 廖振强， 咸东鹏， 等. 基于前冲击发原理的某自动榴弹发射器动力学仿真［J］. 系统仿真学报， 2014， 26（6）： 1378-1383. |
| SONG J， LIAO Z Q， XIAN D P， et al. Dynamics simulation of grenade launcher based on advancing ignition principle［J］. Journal of System Simulation， 2014， 26（6）： 1378-1383 （in Chinese）. | |
| [19] | 杨军荣. 基于软后坐技术的某自动迫击炮动力学分析［J］. 弹道学报， 2006， 18（1）： 63-67. |
| YANG J R. Dynamic analysis of an auto mortar based on the soft recoil technology［J］. Journal of Ballistics， 2006， 18（1）： 63-67 （in Chinese）. | |
| [20] | WANG X X， YU T， YAN H P， et al. Application of stress wave theory for pyroshock isolation at spacecraft-rocket interface［J］. Chinese Journal of Aeronautics， 2021， 34（8）： 75-86. |
| [21] | 王朋朋， 高博， 艾永强， 等. 基于冲击响应分析的星载可展天线解锁策略优化［J］. 振动与冲击， 2017， 36（10）： 57-62. |
| WANG P P， GAO B， AI Y Q， et al. Release strategy optimization for deployable satellite antennas based on shock response analysis［J］. Journal of Vibration and Shock， 2017， 36（10）： 57-62 （in Chinese）. | |
| [22] | 赵相禹， 赵春娟， 张雷， 等. 微纳卫星火工冲击载荷缓冲装置设计及验证［J］. 振动与冲击， 2023， 42（3）： 187-192. |
| ZHAO X Y， ZHAO C J， ZHANG L， et al. Design and verification of pyrotechnic impact load buffer device for micro-nano satellite［J］. Journal of Vibration and Shock， 2023， 42（3）： 187-192 （in Chinese）. | |
| [23] | 王锡雄， 秦朝烨， 丁继锋， 等. 基于激光激励的火工冲击响应及其特性研究［J］. 宇航学报， 2018， 39（4）： 464-470. |
| WANG X X， QIN Z Y， DING J F， et al. Analysis of shock response induced by laser and its features［J］. Journal of Astronautics， 2018， 39（4）： 464-470 （in Chinese）. | |
| [24] | 杨新峰， 邹轶群， 邓卫华， 等. 航天器组件高量级冲击环境的一种评估方法［J］. 宇航学报， 2017， 38（8）： 872-878. |
| YANG X F， ZOU Y Q， DENG W H， et al. An approach to evaluate high level shock for aerospace units［J］. Journal of Astronautics， 2017， 38（8）： 872-878 （in Chinese）. | |
| [25] | 冯丽娜， 李东， 田建东， 等. 削弱槽位置对膨胀管分离装置冲击特性的影响［J］. 导弹与航天运载技术， 2019（3）： 29-35. |
| FENG L N， LI D， TIAN J D， et al. Influence of Notch position on the shock characteristic of the expanding tube separation device［J］. Missiles and Space Vehicles， 2019（3）： 29-35 （in Chinese）. | |
| [26] | SHI W H， YUE S， WU C B， et al. Temperature influences of the recoil characteristics for aluminum honeycomb buffer in the tether-net launcher［J］. Defence Technology， 2023， 29： 39-54. |
| [27] | MAO L J， ZHAO W， HE J， et al. Study on material J-C parameter fitting and cushioning characteristics of 2A12 aluminum honeycomb sandwich under impact environment［J］. Journal of Sandwich Structures & Materials， 2025， 27（4）： 813-842. |
| [28] | PANG Z J， MAO L J， HU T， et al. Study on the penetration-harpoon attachment characteristics of a space harpoon to an aluminum honeycomb sandwich plate［J］. Journal of Sandwich Structures & Materials， 2025， 27（7）： 1404-1435. |
| [29] | WU C B， YUE S， SHI W H， et al. Research on adaptive penetration characteristics of space harpoon based on aluminum honeycomb buffer［J］. Advances in Space Research， 2024， 74（10）： 5100-5117. |
| [30] | FAN Z， SONG Z， XIAO D， et al. Influence of deformation temperature on flow stress and dislocation structure of 2A12 aluminum alloy under quasi-static and dynamic compression［J］. Experimental Mechanics， 2023， 63（4）： 703-714. |
| [31] | 杭宇， 孔德仁， 商飞. 串联发射弹丸内弹道力学特性测试方法研究［J］. 振动与冲击， 2022， 41（3）： 1-7， 26. |
| HANG Y， KONG D R， SHANG F. Test method for interior ballistic mechanical characteristics of series launched projectile［J］. Journal of Vibration and Shock， 2022， 41（3）： 1-7， 26 （in Chinese）. | |
| [32] | ZHANG C， SUN Y Y， BUI T Q， et al. Crushing performance and energy absorption characteristics of aluminum/CFRP hybrid thin-walled tubes： Experimental and numerical investigations［J］. Composites Communications， 2024， 51： 102089. |
| [33] | 王冠. 铝合金薄壁梁结构轻量化设计及其变形行为的研究［D］. 长沙： 湖南大学， 2013： 102-103. |
| WANG G. Lightweight design and deformation behavior of aluminum thin-walled structure［D］. Changsha： Hunan University， 2013： 102-103 （in Chinese） . | |
| [34] | FARD S H M， SAJEDIN A， KHALKHALI A. Sensitivity analyzes turbocharging variables for optimum engine performance［J］. New York Science Journal， 2016，9（9）：96-102. |
/
| 〈 |
|
〉 |
CJA