目的 针对高轨航天器在复杂等离子体环境中运行时,不同航天器之间因表面充电产生电位差,在对接过程中可能引发静电放电的问题,开展相关研究。方法 基于PIC方法,采用SPIS软件平台建立高轨航天器充电过程仿真模型,模拟航天器在恶劣和平静等离子体环境中的充电特性。通过等效电路简化方法,研究航天器对接的放电过程,分析直连电阻和绝缘电容对放电电流的影响。设计并实施地面模拟试验,利用高压源对2个航天器模拟件充电,通过移动装置模拟航天器对接,并通过示波器记录放电过程。结果 阴影条件下,2个航天器电位差可达12 200 V;光照条件下,2航天器电位差稳定后约4 880 V,平静期等离子体环境中电位差仅4~6 V。等效电路仿真显示,保护电阻从100 kΩ增至10 000 kΩ、接触电容从1 μF降至100 pF时,最大放电电流脉冲峰值从9.85 A降至0.55 A,降低94.4%。地面试验研究表明,放电瞬间电压在kV量级,目标航天器瞬时放电电流峰值为6.87 A,对接航天器瞬时放电电流峰值为5.31 A。结论 高轨航天器在恶劣等离子体环境中充电电位差显著,对接过程存在严重静电放电风险,可通过增大直连电阻或降低绝缘电容可有效抑制放电电流。地面模拟试验成功复现了航天器悬浮充电状态和对接放电特性,验证了地面模拟方法的有效性,为高轨航天器对接静电防护设计提供了试验依据和参考。
Abstract
The work aims to conduct research on the issue of electrostatic discharge that may occur during docking operations when spacecrafts operating in complex plasma environments develop potential differences due to surface charging between different spacecrafts. Based on the PIC method, a simulation model of the charging process for high-orbit spacecrafts was established with the SPIS software platform to simulate the charging characteristics of spacecrafts in harsh and calm plasma environments. The discharge process during spacecraft docking was studied with an equivalent circuit simplification method and the effects of direct-connection resistance and insulation capacitance on discharge current were analyzed. A ground simulation test was designed and conducted and two spacecraft mock-ups were charged with a high-voltage source. A mobile device was used to simulate spacecraft docking, and the discharge process was recorded via an oscilloscope. Simulation results indicated that under shadow conditions, the potential difference between the two spacecrafts reached 12 200 V. Under illumination conditions, the potential difference stabilized at approximately 4 880 V. In a calm plasma environment, the potential difference was only 4-6V. Equivalent circuit simulations revealed that increasing the protective resistor from 100 kΩ to 10 000 kΩ and decreasing the contact capacitance from 1 μF to 100 pF reduced the peak discharge current pulse from 9.85 A to 0.55 A, representing a 94.4% decrease. Ground test revealed that the instantaneous discharge voltage reached the kV level, with the target spacecraft experiencing a peak instantaneous discharge current of 6.87 A and the docking spacecraft experiencing a peak instantaneous discharge current of 5.31 A. High-orbit spacecrafts exhibit significant potential differences due to charging in harsh plasma environments, posing severe electrostatic discharge risks during docking operations. Discharge currents can be effectively suppressed by increasing direct-connection resistance or reducing insulation capacitance. Ground simulation tests successfully replicate the spacecraft's suspended charging state and docking discharge characteristics, validating the effectiveness of the ground simulation methodology. This provides experimental basis and reference for electrostatic protection design in high-orbit spacecraft docking operations.
关键词
航天器 /
表面充电 /
等离子体环境 /
等效电路 /
PIC仿真方法 /
航天器对接
Key words
spacecraft /
surface charging /
plasma environment /
equivalent circuit /
PIC simulation method /
spacecraft docking
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