Active spacecraft potential control for Cluster - implementation and first results

TLDR: In this article, the design and principles of the operation of the instrument for active spacecraft potential control (ASPOC) are presented in detail, and the instrument is oper- ated with constant ion current for most of the time, but tests have been carried out with varying currents and a feedback mode with the instrument EFW, which measures the space- craft potential.

Abstract: Electrostatic charging of a spacecraft modifies the distribution of electrons and ions before the particles enter the sensors mounted on the spacecraft body. The floating potential of magnetospheric satellites in sunlight very often reaches several tens of volts, making measurements of the cold (several eV) component of the ambient ions impossi- ble. The plasma electron data become contaminated by large fluxes of photoelectrons attracted back into the sensors. The Cluster spacecraft are equipped with emitters of the liquid metal ion source type, producing indium ions at 5 to 9 keV energy at currents of some tens of microampere. This current shifts the equilibrium potential of the spacecraft to moderately positive values. The design and principles of the operation of the instrument for active spacecraft poten- tial control (ASPOC) are presented in detail. Experience with spacecraft potential control from the commissioning phase and the first two months of the op- erational phase are now available. The instrument is oper- ated with constant ion current for most of the time, but tests have been carried out with varying currents and a "feedback" mode with the instrument EFW, which measures the space- craft potential . That has been reduced to values according to expectations. In addition, the low energy electron measure- ments show substantially reduced fluxes of photoelectrons as expected. The flux decrease in photoelectrons returning to the spacecraft, however, occurs at the expense of an en-