Satellite Dynamics and Control in a Quaternion Formulation (2nd edition)

Mogens Blanke, Martin Birkelund Larsen

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    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 languageEnglish
    PublisherTechnical University of Denmark, Department of Electrical Engineering
    Number of pages50
    Publication statusPublished - 2010

    Bibliographical note

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

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