Technical Papers
Mar 10, 2020

Vibration Transport of Lunar Regolith for In Situ Resource Utilization Using Piezoelectric Actuators with Displacement-Amplifying Mechanism

Publication: Journal of Aerospace Engineering
Volume 33, Issue 3

Abstract

In situ resource utilization on the Moon increases mission capability in lunar exploration and colonization. Lunar regolith is the most promising substance that can be used as a building material; its chemical composition includes metals, oxygen, helium-3, and water. Because the transportation of regolith is an essential and intricate part of its utilization, the author investigates a vibration transport system that uses a piezoelectric actuator combined with a displacement-amplifying mechanism. Although the load capacity of the piezoelectric actuator is substantially high, its movable displacement is low. Therefore, the displacement of the piezoelectric actuator was amplified approximately five times in the direction normal to the extending direction of the piezoelectric actuator to generate a high magnitude of vibration. A vibrational acceleration of approximately 7 g of the conveyor was achieved by optimizing the structure of the displacement-amplifying mechanism. The system has no frictional parts and does not require complicated controls or a significant amount of power; thus, it is compatible with space applications. We demonstrated both a flat and an inclined transport path through a small conveyor tube with a 26-mm inner diameter and 300-mm length. The results indicated a mass flow rate of approximately 7  g/s of the lunar regolith simulant at a reasonable speed (150  mm/s) through the tube on the horizontal conveyance and a maximum conveyance tilt angle of 24° in Earth conditions. In addition to the regolith transport, large particles in the regolith were observed to be susceptible to a downward fall in the tube, given the Brazil nut effect, and this feature was proposed to be used as a beneficiation system.

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Data Availability Statement

Some data and models used during the study are available from the corresponding author by request, including the data in Figs. 27.

Acknowledgments

The author would like to express his gratitude to Koki Hamazawa, Hayato Ogawa, Hiroaki Kaku, Yuki Takeda, and Dai Yunda (Waseda University) for their support in conducting the experiment. A part of this work was supported by JSPS KAKENHI Grant No. 17K06276 and the Iwatani Naoji Foundation.

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Journal of Aerospace Engineering
Volume 33Issue 3May 2020

History

Received: Jul 15, 2019
Accepted: Nov 15, 2019
Published online: Mar 10, 2020
Published in print: May 1, 2020
Discussion open until: Aug 10, 2020

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Authors

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Hiroyuki Kawamoto [email protected]
Professor, Dept. of Applied Mechanics and Aerospace Engineering, Waseda Univ., 3-4-1, Okubo, Shinjuku, Tokyo 169-8555, Japan. Email: [email protected]

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