目的 针对空间微小碎片高速撞击威胁航天器高压太阳电池阵在轨安全的问题,开展微米级铝颗粒撞击诱发二次放电特性的试验研究,揭示放电时间随电路参数变化的非线性演化规律。方法 利用激光驱动飞片技术构建地面模拟试验系统,开展微米级铝颗粒高速撞击三结砷化镓太阳电池阵试验。通过获取不同工况下的放电波形与电弧图像,结合微观形貌分析,研究太阳电池阵串间电流与二次放电特性的非线性耦合关系。结果 在太阳电池阵串间电压一定时,串间电流是决定二次放电持续时间的主要因素。随着串间电流增大,放电持续时间显著增长。当电流较低时,持续时间受颗粒动力学参数影响;当电流超过2.0 A时,电路注入的焦耳热效应占据主导,表现为持续性放电,极易导致永久性短路。此外,根据放电时间将损伤形貌明确划分为热扩散、基板初步热溶解与基板碳化3个阶段。结论 空间碎片撞击诱发的持续性放电存在明显的电流阈值效应。该研究建立的损伤演化规律及获取的2.0 A串间电流阈值,可为航天器太阳电池阵的空间碎片防护设计及在轨风险评估提供试验依据。
Abstract
The study aims to conduct experimental research on the characteristics of secondary discharge induced by micron-sized aluminum particles to reveal the nonlinear evolution law of discharge duration with the variation of circuit parameters, and address the threat of space micro-debris hypervelocity impacts on the on-orbit safety of spacecraft high-voltage solar cell arrays. A ground simulation experimental system was established utilizing the laser-driven flyer technique to conduct experiments on micron-scale aluminum particles impacting triple-junction gallium arsenide (GaAs) solar cell arrays. By acquiring discharge waveforms and arc images under various operating conditions and combining them with microscopic morphology analysis, the non-linear coupling relationship between the inter-string current of the solar cell array and the secondary discharge characteristics was investigated. Experimental results indicated that, under a constant inter-string voltage, the inter-string current was the primary factor determining the duration of secondary discharge. The discharge duration increased significantly with the increase of the inter-string current. At lower current levels, the duration was influenced by particle dynamic parameters; however, when the current exceeded 2.0 A, the Joule heating effect injected by the circuit became dominant, manifesting as a sustained discharge that easily led to a permanent short circuit. Furthermore, based on the discharge duration, the damage morphology was explicitly classified into three stages: thermal diffusion, initial thermal melting of the substrate, and substrate carbonization. A distinct current threshold effect exists for sustained discharge induced by the space debris impact. The damage evolution laws established and the 2.0 A inter-string current threshold identified in this study provide an experimental basis for the space debris protection design and on-orbit risk assessment of spacecraft solar cell arrays.
关键词
超高速撞击 /
太阳电池阵 /
二次放电 /
串间电流 /
等离子体 /
空间碎片
Key words
hypervelocity impact /
solar cell array /
secondary discharge /
inter-string current /
plasma /
space debris
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