Back to Search
Start Over
Design of Spacecraft Momentum Unloading Using Discrete-Time Formulation.
- Source :
- Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering; Mar2011, Vol. 225 Issue 3, p312-324, 13p
- Publication Year :
- 2011
-
Abstract
- An approach for the design of a momentum unloading system for a spacecraft controlled by momentum exchange actuators is proposed. The approach is based on formulating momentum unloading as a control problem of a parametrically perturbed periodic system. An equivalent discrete-time robust control design problem is formulated using a point-mapping-based numerical algorithm. Established robust control analysis can then be used to develop and analyse the robustness of the unloading control law. The method is demonstrated on an Earth-pointing satellite with magnetic torquers serving as unloading actuators. Earth's magnetic field is modelled as a tilted dipole that consists of a periodic term and bounded perturbations. A discrete-time representation of the system is used to develop an unloading control law and the structured singular value theory is employed to analyse its robustness to parametric uncertainties. [ABSTRACT FROM AUTHOR]
Details
- Language :
- English
- ISSN :
- 09544100
- Volume :
- 225
- Issue :
- 3
- Database :
- Complementary Index
- Journal :
- Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
- Publication Type :
- Academic Journal
- Accession number :
- 70212973
- Full Text :
- https://doi.org/10.1243/09544100JAERO846