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月面任务将面临月球车车轮与月尘摩擦充放电风险, 初步的理论研究表明金属材质的车轮可能会充电至–5000 V量级, 放电脉冲电流可达0.1 A量级, 严重威胁航天员生命安全和器件电路的正常工作. 本文采用地面实验手段研究了真空、太阳风等离子体环境下月球车车轮摩擦充放电风险. 研究结果表明, 真空环境下, 直径为136 mm的铝合金月球车车轮以0.003 m/s在月尘层上行驶时会快速充电至几百伏正电位, 车轮行驶距离至约20 m, 电位为550 V时即发生放电击穿, 此时捕捉到的放电电流脉冲幅值可达1.5 A, 脉冲持续时间约100 ns; 增加摩擦频率充电速率明显增加, 放电更频繁的发生; 在模拟的太阳风等离子体环境下, 车轮以0.003 m/s行驶时环境和摩擦共同作用使充电电位为负, 平衡后电位约–830 V左右, 且放电更加频繁, 行驶至8.5 m时即发生放电击穿, 放电电流脉冲幅值可达0.3 A, 脉冲持续时间100 ns. 该放电脉冲对线性电路造成了电磁干扰, 导致信号的异常输出. 本研究表明月球车摩擦充放电风险较高, 需在后续工程任务中关注并进一步评估其危害程度.
With China’s lunar exploration program steadily advancing from the landmark orbiting missions of Chang’e-1 to the historic sample-return feats of Chang'e-5 and the groundbreaking far-side landing of Chang’e-4, China has entered a critical phase of deepening lunar exploration, including preparations for crewed lunar missions. Among these ambitious endeavors, identifying and mitigating potential operational risks is crucial to ensuring the success of these ambitious efforts. This work focuses on a critical hazard unique to China’s lunar surface exploration efforts: the triboelectric charging and discharging phenomenon between lunar rover wheels and lunar dust, which has a significant impact on astronaut safety and the reliability of onboard electronic systems. Lunar surface missions will face the risk of triboelectric charging and discharging resulting from friction between lunar rover wheels and lunar dust. Preliminary theoretical studies indicate that metal wheels may become charged to a level of approximately –5000 V, with discharge pulse currents reaching an order of magnitude of 0.1 A, posing a severe threat to astronaut safety and the normal operation of device circuits. This paper employs ground-based experimental methods to investigate the triboelectric charging and discharging risks of lunar rover wheels in vacuum and simulated solar wind plasma environments. The research findings are given below. In a vacuum environment, when an aluminum alloy lunar rover wheel (136 mm in diameter) travels on a lunar dust layer at a speed of 0.003 m/s, it rapidly charges to a positive potential of several hundred volts. Discharge breakdown occurs when the wheel travels approximately 20 m and reaches a potential of 550 V. At this point, the captured discharge current pulse amplitude can reach 1.5 A, with a pulse duration of about 100 ns. Increasing the friction frequency significantly accelerates the charging rate and leads to more frequent discharges. In a simulated solar wind plasma environment, when the wheel travels at 0.003 m/s, the combined effect of the environment and friction results in a negative charging potential. After reaching equilibrium, the potential stabilizes at approximately –830 V, and discharges occur more frequently than in a vacuum environment. Discharge breakdown takes place when the wheel travels just 8.5 m, with the discharge current pulse amplitude reaching up to 0.3 A and a pulse duration of 100 ns. These discharge pulses cause electromagnetic interference to linear circuits, leading to abnormal output of voltage signals in subsequent modes. The abnormal signals have an amplitude on the order of 10 V and a duration of 29 ms. This study confirms that the risk of triboelectric charging and discharging in lunar rovers is relatively high. Although theoretical models predict that the lunar roving vehicle (LRV) would experience rapid dissipation of triboelectric charges (with no charging/discharging risk) when operating at 0.03 m/s, the experiments show that even at a slow speed of 0.003 m/s, the wheels still accumulate charges and experience frequent discharge breakdowns. The amplitude of discharge pulse can reach the level of 1 ampere, causing significant electromagnetic interference to nearby circuits. Clearly, theoretical models underestimate the risk of triboelectric charging and discharging in lunar surface environments. It is recommended that future engineering tasks pay close attention to this issue and further evaluate the extent of its hazards. -
Keywords:
- charging and discharging /
- friction /
- lunar rover /
- lunar environment
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图 1 材料与月尘摩擦充电试验装置图
Fig. 1. Schematic diagram of the triboelectric charging test device for materials and lunar dust.
图 2 在20 ℃条件下, 真空和大气环境中铝材料摩擦充电电位随摩擦次数的变化(紫色方框代表此次摩擦后探测到放电信号)
Fig. 2. Curve of triboelectric charging potential of aluminum material vs. friction cycles under vacuum and atmospheric environments at 20 ℃.
图 3 铝材料摩擦放电脉冲电流波形
Fig. 3. Triboelectric discharge pulse current waveform of aluminum material.
图 4 不同摩擦周期铝材料摩擦充电特性(真空, 20 ℃)
Fig. 4. Triboelectric charging characteristics of aluminum material under different friction cycles (vacuum environment, 20 ℃).
图 5 太阳风环境下铝材料摩擦充电电位随摩擦次数的变化(真空, 20 ℃, 其中紫色方框代表此次摩擦后发生了放电)
Fig. 5. Curve of triboelectric charging potential of aluminum material vs. friction cycles under solar wind environment (Vacuum, 20 ℃).
图 6 太阳风环境下铝材料与月尘摩擦放电脉冲电流波形(6×10–3 Pa, 20 ℃; 电子密度约108 cm–3量级, 电子能量约4 eV, 离子能量约1 eV)
Fig. 6. Triboelectric discharge pulse current waveform of aluminum material rubbed against lunar dust under solar wind environment (6×10–3 Pa, 20 ℃; electron density ~108 cm–3, electron energy ~4 eV, ion energy ~1 eV).
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