Present and in perspective applications of low thrust ion propulsion on small satellites
Author(s)
Date Issued
1998-01-01
Abstract
In this paper LEO application missions on board small satellites are addressed, for which the compensation of the atmospheric drag in the range 300-500 km is accomplished using low thrust (1-10 mN) ion propulsion.
The advantages of using small satellites (500-600 kg) for performing multi-year earth observationtremote sensing missions are as well pointed out. A review on the drag simplified theory and parameters involved is, besides, presented, with the purpose of evaluating the range of drdg forces acting onto a small satellite in the specified altitude range. A preliminary mission analysis is also performed with reference to two sunsynchronous application orbits (" dawn dusk" and" near noon"), evaluating the necessary thrust levels and operation duty cycles for an ion propulsion system dedicated to the compensation of the atmospheric drag. The use of low thrust ion thruster (1-10 mN) is proposed and motivated for multi-year missions, in the frame of a full compliance with the small satellite philosophy.
The advantages of using small satellites (500-600 kg) for performing multi-year earth observationtremote sensing missions are as well pointed out. A review on the drag simplified theory and parameters involved is, besides, presented, with the purpose of evaluating the range of drdg forces acting onto a small satellite in the specified altitude range. A preliminary mission analysis is also performed with reference to two sunsynchronous application orbits (" dawn dusk" and" near noon"), evaluating the necessary thrust levels and operation duty cycles for an ion propulsion system dedicated to the compensation of the atmospheric drag. The use of low thrust ion thruster (1-10 mN) is proposed and motivated for multi-year missions, in the frame of a full compliance with the small satellite philosophy.