development of spacecraft charging measuring instrument with parallel plate electrostatic energy analyzer

Paper number

IAC-08.C2.6.11

Author

Ms. Naomi Kurahara, Kyushu Institute of Technology, Japan

Year

2008

Abstract

Electric discharges on spacecraft have become a serious problem as the spacecraft bus voltage has increased in recent space development. The increased power means an increase in the charging potential and the risk of catastrophic failure, which was demonstrated by the loss of ADEOS-II. A therough understanding of spacecraft charging is very important for the safe operation of spacecraft.

In-orbit measurements of spacecraft charging have been performed in the past two decades, but it should become a more long-term and practical measurement. The on-board charging meter must not only acquire spacecraft charging data, but also act as a warning device for charging-arcing problems.

In order to do orbital experiments more frequently, small satellites are very useful tools. The charging measurement device has been downsized with the evolution of semiconductor and IC technology, but it is still too cumbersome for small satellites or multiple uses on a spacecraft. Further miniaturization of the device is necessary. The purpose of this research is to develop a small size charging measurement device which allows it to be carried on a small satellite.

In this research, the basic equipment for charging measurement is the similar to an electrostatic energy analyzer. Two-stage parallel plate is used for ion energy analysis. Spacecraft charging is measured by analyzing the energy spectrum change for the ion sheath around a spacecraft. The target size of the measurement device is 5x5x5cm. The goal is for it to be carried on a CubeSat class satellite. The system details and verification test results will be presented at the conference.

Abstract document

IAC-08.C2.6.11.pdf

Manuscript document

IAC-08.C2.6.11.pdf (🔒 authorized access only).

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