| 引用本文: | 孙文,迟润强,刘瑜妍,胡迪奇,曹武雄,庞宝君.毫米以下MM/SD撞击太阳翼的损伤评估方法[J].哈尔滨工业大学学报,2026,58(4):49.DOI:10.11918/202502035 |
| SUN Wen,CHI Runqiang,LIU Yuyan,HU Diqi,CAO Wuxiong,PANG Baojun.A damage assessment method of solar wings under submillimeter MM/SD impact[J].Journal of Harbin Institute of Technology,2026,58(4):49.DOI:10.11918/202502035 |
|
| |
|
|
| 本文已被：浏览 1177次 下载 26次 |
码上扫一扫！ |
|
|
| 毫米以下MM/SD撞击太阳翼的损伤评估方法 |
|
孙文1,2,迟润强1,3,刘瑜妍1,3,胡迪奇1,3,曹武雄1,3,庞宝君1,3
|
|
(1.哈尔滨工业大学 航天学院,哈尔滨 150001;2.中国科学院长春光学精密机械与物理研究所,长春 130033; 3.微小型航天器快速设计与智能集群全国重点实验室(哈尔滨工业大学),哈尔滨 150001)
|
|
| 摘要: |
| 为解决暴露面积较大的太阳能电池阵在微流星体和空间碎片（MM/SD）撞击下的损伤评估问题,针对毫米以下MM/SD,提出一种电池阵损伤评估方法。该方法考虑了撞击的不确定性以及损伤的累积效应,同时通过与NASA探测数据的对比,验证了电池阵撞击频次模型的有效性。以高度分别 为400、800、35 787 km的3条轨道上的太阳能电池阵为研究对象。首先,通过空间碎片环境工程模型和微流星体模型,确定了航天器轨道上MM/SD通量尺寸相对速度分布。其次,依照分布生成MM/SD数据,并随机选择撞击点进行模拟撞击试验,实现了累积效应的可视化。然后,基于电池阵的机械损伤特性和伏安特性,分析电池阵的撞击损伤特征以及功率损失。最后,以功率损失为防护指标,研究了玻璃盖片厚度对防护性能的影响。仿真试验结果表明:所提出的方法能够有效评估不同轨道上太阳能电池阵的撞击损伤情况,较为准确地刻画损伤特征,并体现出不同尺寸MM/SD对电池阵的撞击损伤差异,为航天器在轨任务损伤评估和防护结构设计提供参考。 |
| 关键词: MM/SD 太阳能电池阵 损伤评估 累积效应 不确定性 |
| DOI：10.11918/202502035 |
| 分类号:V528 |
| 文献标识码:A |
| 基金项目: |
|
| A damage assessment method of solar wings under submillimeter MM/SD impact |
|
SUN Wen1,2,CHI Runqiang1,3,LIU Yuyan1,3,HU Diqi1,3,CAO Wuxiong1,3,PANG Baojun1,3
|
|
(1.School of Astronautics, Harbin Institute of Technology, Harbin 150001, China;2. Changchun Institute of Optics, Fine Mechanics and Physics, Chinese Academy of Sciences, Changchun 130033, China; 3.State Key Laboratory of Micro-Spacecraft Rapid Design and Intelligent Cluster (Harbin Institute of Technology), Harbin 150001, China)
|
| Abstract: |
| To achieve damage assessment of solar arrays with large exposed areas under micro-meteoroid & space debris (MM/SD) impacts, this paper proposed a damage assessment method for solar arrays, focusing on submillimeter MM/SD impacts. This method considered the uncertainty of impacts and the cumulative damage effects. The effectiveness of the solar array impact frequency model was validated through comparison with NASA detection data. The study focused on solar arrays in three orbits with altitudes of 400 km, 800 km, and 35 787 km. First, the flux-size-velocity distributions of MM/SD on spacecraft orbits were determined using the space debris environment engineering model and micrometeoroid models. Then, MM/SD data were generated based on these distributions, and random impact points were selected for simulated impact experiments, achieving visualization of cumulative effects. Next, based on the mechanical damage characteristics and volt-ampere characteristics of the solar array, the impact damage features and power loss were analyzed. Finally, with power loss as a protective indicator, the effect of glass cover thickness on protection performance was studied. The simulation results show that the proposed method can effectively assess impact damage to solar arrays on different orbits, accurately characterize damage features, and reflect the differences in impact damage caused by MM/SD of varying sizes, providing references for on-orbit mission damage assessment and protective structure design for spacecraft. |
| Key words: MM/SD solar array damage assessment cumulative effect uncertainty |
|
|
|
|
