Hypervelocity Impact Experiment on High Voltage Solar Array for High Power Satellite

Paper number

IAC-08.A6.3.3

Author

Dr. Koji Tanaka, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Mr. Youichi Nagaoka, The Graduate University for Advanced Studies (Sokendai Univ.) / JAXA, Japan

Coauthor

Dr. Akira Yamori, Japan Aerospace Exploration Agency (JAXA), Japan

Coauthor

Prof. Susumu Sasaki, Japan Aerospace Exploration Agency (JAXA), Japan

Year

2008

Abstract

Space dusts, such as natural meteoroids or man made orbiting debris, are recognized as a serious and growing threat to man’s utilization and exploration of space. Debris larger than 10 cm in diameter is detected by ground based radars and optical observations. But it is impossible to detect debris smaller than 10 cm by ground-based observations using existing technologies. Typical debris impacts are thought to occur at a velocity of around 10 km/s. Hypervelocity impact caused extreme damage to the spacecraft’s subsystems. In addition, the plasma production by the hypervelocity impact can trigger electrical breakdown and cause serious damage to the high power spacecraft.
We carried out the experiments for the research on the debris impacts concerning the high voltage solar array using a railgun accelerator of ISAS/JAXA and a pulsed laser. A flexible thin film amorphous silicon solar cell, a simulated solar array and some thin film materials were used as a target. The simulated solar array consists of a cover glass, metal plate in place of a solar cell and inter-connectors. The simulated solar array was applied voltage during an impact experiment.
We observed phenomena when the projectile penetrated a target using a high speed video camera, and plasma probes. After the projectile impacted against the target, a bright cloud was generated and moved both forward and backward directions from the target. Electron temperature and density were estimated by the plasma probes. Discharge between the solar arrays was observed and discharge current was measured by the current probe. Evaluation of the impact effect will be reported.

Abstract document

IAC-08.A6.3.3.pdf

Manuscript document

IAC-08.A6.3.3.pdf (🔒 authorized access only).

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