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首页> 外文期刊>IEEE Aerospace and Electronic Systems Magazine >Microsatellite combined attitude/energy systems
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Microsatellite combined attitude/energy systems

机译：微卫星组合姿态/能量系统

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We have constructed a high-temperature super conductor-magnet momentum wheel for microsatellites and propose a micro high-temperature superconductor energy storage and attitude control system for nano/pico satellites. The momentum wheel for micro satellites has a mass of 1.1 kg with an angular momentum capacity of 3.5 J sec. It occupies a volume of 12.7 cm in diameter and 5 cm in height. It operates within the restricted power budget of a microsatellite with a total power supply of only 10 watts. It consumes less than 1 watt for sustenance. The micro high-temperature superconductor flywheel for nano/pico satellites has an angular momentum capacity of 0.083 Js and stores 2.32 kJ at 530 krpm. Its energy storage capacity is approximately 45 Wh/kg with an energy density of around 370 kJ/L. The HTS systems can perform the dual function of a power/attitude control system and are ideally suited for low Earth orbit energy storage, power generation, and attitude control of spacecraft.
机译：我们已经为微卫星构造了一个高温超导体磁动量轮，并提出了一种用于纳米/微卫星的微型高温超导体能量存储和姿态控制系统。用于微型卫星的动量轮的质量为1.1 kg，角动量为3.5 J sec。它的直径为12.7厘米，高度为5厘米。它只能在总功率仅为10瓦的微卫星的受限功率预算内运行。它的耗电量不到1瓦。用于纳米/微微卫星的微型高温超导体飞轮的角动量容量为0.083 Js，在530 krpm的速度下存储2.32 kJ。它的能量存储容量约为45 Wh / kg，能量密度约为370 kJ / L。 HTS系统可执行电源/姿态控制系统的双重功能，非常适合于低地球轨道的能量存储，发电和航天器的姿态控制。

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