This paper describes the realization of a generic simulator for formation flying satellites, and the design and application of Embedded Model Control (EMC) to the spacecraft control, as potentially applicable to a constellation of drag-free satellites. They can be employed for scientific purposes: here it is presented the Satellite-Satellite Interferometry (SSI) mission for the measurement of the Earth’s gravitational field harmonics, which will follow the incoming gravimetric mission GOCE and the gravitational wave observatory LISA. The core drag-free controller (DFC) was partly validated by Preliminary Design Review of GOCE mission, and particular emphasize is given to the acceleration observer and to the command computation law. The measurement model and mission requirements are also presented, followed by the simulation results of the DFC, tuned ad-hoc in order to obtain accurate aiming target.

Embedded Model Control application to drag-free and satellite-to satellite tracking / Massotti, Luca; Canuto, Enrico; Silvestrin, P.. - STAMPA. - (2006), pp. 1-6. ((Intervento presentato al convegno 14th IEEE Mediterranean Conference on Control and Automation tenutosi a Ancona (Italy) nel June 28-30, 2006 [10.1109/MED.2006.328708].

Embedded Model Control application to drag-free and satellite-to satellite tracking

MASSOTTI, Luca;CANUTO, Enrico;
2006

Abstract

This paper describes the realization of a generic simulator for formation flying satellites, and the design and application of Embedded Model Control (EMC) to the spacecraft control, as potentially applicable to a constellation of drag-free satellites. They can be employed for scientific purposes: here it is presented the Satellite-Satellite Interferometry (SSI) mission for the measurement of the Earth’s gravitational field harmonics, which will follow the incoming gravimetric mission GOCE and the gravitational wave observatory LISA. The core drag-free controller (DFC) was partly validated by Preliminary Design Review of GOCE mission, and particular emphasize is given to the acceleration observer and to the command computation law. The measurement model and mission requirements are also presented, followed by the simulation results of the DFC, tuned ad-hoc in order to obtain accurate aiming target.
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11583/1409371
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