The Microscope mission by CNES is a test of the Equivalence Principle with a microspacecraft in low Earth orbit. The propulsion system for this satellite has unique requirements: very low thrust, accurate thrust throttling, stringent mass and power constraints. The system will be used to compensate for non-gravitational forces on the spacecraft, enabling it to fly along an inertial trajectory, in the so called “drag-free” mode. This paper presents the architecture of the micronewton FEEP system for MicroScope, illustrating the configuration constraints and the resulting design choices.

FEEP System for the Microscope Mission

MARCUCCIO, SALVO;
2003-01-01

Abstract

The Microscope mission by CNES is a test of the Equivalence Principle with a microspacecraft in low Earth orbit. The propulsion system for this satellite has unique requirements: very low thrust, accurate thrust throttling, stringent mass and power constraints. The system will be used to compensate for non-gravitational forces on the spacecraft, enabling it to fly along an inertial trajectory, in the so called “drag-free” mode. This paper presents the architecture of the micronewton FEEP system for MicroScope, illustrating the configuration constraints and the resulting design choices.
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11568/80329
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