### Abstract

This lecture note treats modelling and attitude control design using a quaternion description of attitude for a rigid body in space. Dynamics and kinematics of a satellite is formulated as a non-linear model from Euler’s moment equations and a description of kinematics using the attitude quaternion to represent rotation. A general linearised model is derived such that the user can specify an arbitrary point of operation in angular velocity and wheel angular momentum, specifying the a inertia matrix for a rigid satellite. A set of Simulink® models that simulate the satellite’s nonlinear behaviour are described and a Matlab® function is described that has been written to calculate the linear model in an arbitrary point of operation.

Original language | English |
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Publisher | Technical University of Denmark, Department of Electrical Engineering |
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Number of pages | 50 |

Publication status | Published - 2010 |

### Bibliographical note

Lecture note for course 31365. Version 2f - September, 2010## Cite this

Blanke, M., & Larsen, M. B. (2010).

*Satellite Dynamics and Control in a Quaternion Formulation (2nd edition)*. Technical University of Denmark, Department of Electrical Engineering.