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Spacecraft control with constrained fast reorientation and accurate pointing

Published online by Cambridge University Press:  03 February 2016

G. Mengali
Affiliation:
Università di Pisa, Dipartimento di Ingegneria Aerospaziale, Pisa, Italy, London, UK
A. A. Quarta
Affiliation:
Università di Pisa, Dipartimento di Ingegneria Aerospaziale, Pisa, Italy, London, UK

Abstract

In this paper we study large angle rotational manoeuvres of spacecraft. The problem of attitude control is formulated and solved through potential functions, thus simplifying frequent reorientation manoeuvres. A combination of gas jet and FEEP thrusters is employed in order to obtain short settling times while meeting stringent pointing requirements. In this way, spacecraft reorientation is achieved in two integrated steps by means of a discrete/continuous control law. Autonomous avoidance of undesired space orientations is obtained and constraints due to the solar array pointing requirements are satisfied. A case study is discussed where the methodology is applied to a large space telescope.

Type
Research Article
Copyright
Copyright © Royal Aeronautical Society 2004

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References

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