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CubeSat Lunar Mission Using a Miniature Ion Thruster

机译：使用微型离子推进器的CubeSat月球任务

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The feasibility of CubeSats utilizing the Miniature Xenon Ion (MiXI) thruster for lunar missions is the focus of this investigation. The successful heritage, simplicity, and low cost of CubeSats make them attractive candidates for scientific missions to the Moon. This investigation presents the first-order design process for developing a lunar mission CubeSat. The results from this process are then applied to a 3U CubeSat equipped with a MiXI thruster and specifically designed to reach the lunar surface from a low Earth orbit. The small, 3cm diameter MiXI thruster utilized is capable of producing 0.1-1.553mN of thrust with a specific impulse of over 3000s and is projected to be capable of generating over 7000m/s of AV for a CubeSat mission. With all margins and contingencies considered, the total power required for the CubeSat using a 40W ion thruster is approximately 92W during dayh'ght operations. With an assumed solar incidence angle of 45°, this power can be generated from a Spectrolab UTJ solar array of 0.35m2. Thermal calculations show an average spacecraft surface temperature of approximately 59 C during daylight operations and 0°C during eclipse, which are within the operational and survivable temperature ranges of the spacecraft subsystems. A low-thrust trajectory model is utilized to calculate and plot Earth-Moon trajectories.
机译：本研究的重点是，利用微型氙离子（MiXI）推进器进行CubeSats登月任务的可行性。 CubeSats的成功传承，简单和低成本使其成为进行月球科学飞行任务的有吸引​​力的候选人。这项调查介绍了开发月球任务CubeSat的一阶设计过程。然后，该过程的结果将应用于配备了MiXI推进器的3U CubeSat，该3U CubeSat经过专门设计可从低地球轨道到达月球表面。使用的直径3cm的小型MiXI推进器能够产生0.1-1.553mN的推力，具有超过3000s的比冲，并且预计能够为CubeSat任务产生超过7000m / s的AV。考虑到所有裕度和意外情况，在白天的操作过程中，使用40W离子推进器的CubeSat所需的总功率约为92W。在假定太阳入射角为45°的情况下，可以从0.35m2的Spectrolab UTJ太阳电池阵列中产生此功率。热计算表明，在日间运行期间，航天器的平均表面温度约为59℃，在日食运行期间，其平均温度为0°C，这在航天器子系统的运行温度和可承受温度范围内。利用低推力轨迹模型来计算和绘制月球轨迹。

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