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Satellite formation flying simulator development
2008 (English)Independent thesis Advanced level (degree of Master (Two Years)), 20 credits / 30 HE creditsStudent thesis
Abstract [en]

Formation flying is a key technology for future space application. For precise positioning requirements of formation flying, there is a need for the high fidelity of propagator tool. In order to meet this need, a Matlab /Simulink orbit propagator for formation flying applications has been developed over three consecutive years by MSc student. This paper presents the work realized during the forth iteration of the orbit propagator life cycle, and a controller architecture was built for feedback control loop. The old version of the propagator selected a multi-step integration method, 8th order Gauss-Jackson, as the algorithm which needs the integrated function must be smooth and continuous, and this lead it can not capture the complex perturbed LEO environment. New version propagator through switching the algorithm between Runge-Kutta (single-step) and Gauss-Jackson to introduce the control forces to the propagator for each simulated satellite successfully. The sensor and thruster model now can be easily described in the controller with M codes. New data resource, control accelerations, drag and non-spherical effects etc, also added to the outputs. Finally, a series of simulations were carried out to prove that the new version propagator and controller are suitable for the research of formation keeping and reconfiguration in LEO.

Place, publisher, year, edition, pages
Keyword [en]
Technology, propagator, numerical, integration, Matlab, Simulink, LEO, feedback, control
Keyword [sv]
URN: urn:nbn:se:ltu:diva-58495ISRN: LTU-PB-EX--08/026--SELocal ID: f142cc03-4910-47cd-b1e9-7d9cc364ad84OAI: diva2:1031883
Subject / course
Student thesis, at least 30 credits
Educational program
Space Engineering, master's level
Validerat; 20101217 (root)Available from: 2016-10-04 Created: 2016-10-04Bibliographically approved

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