There have been great efforts in the field of space technology to make space programmes more affordable ones. Smaller size design of spacecraft becomes a common goal for the mission planners and manufactures around the world. Currently developing technologies enable us to achieve a level of performance that was only feasible with large scale missions in the past. Attitude determination and control system(ADCS) is in the heart of the technical challenges for miniaturisation of a satellite. It is generally believed that higher accuracy control system requires massive and expensive sensing and actuating devices. This paper is focused on how a budget mission can overcome the limitation. The hardware and software designs involved in a micro-satellite programme, KITSAT-3, were explained to support this topic. The mission objectives of the satellite were overviewed including a brief introduction to the pushbroom type electro-optical camera and the space science experiment package. ADCS related requirements were analysed for payload operations. Derived requirements were examined with the performance analysis results considering design margins. Spacecraft attitude dynamics and description methods were presented for the control theory developments. The system design and test results of the attitude hardwares are the main part of this thesis. System architecture of a three-axis attitude control system was proposed. The design process of the magnetorquer system was described in detail. Test results of the reaction wheels and fibre optic gyros were provided and analysed. Based upon the actual experimental results, dynamic models of the hardwares were constructed. Command and data handling protocols of the ADCS were also established for proper data management. Environmental disturbance sources were modelled. The effects of micro vibrations induced by mechanically moving parts were assessed to verify the attitude stability requirements. Three-axis magnetorquering algorithm was suggested based on the actual implementation ...


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    High accuracy attitude control of a micro-satellite


    Beteiligte:
    Kim, Byung Jin (Autor:in)

    Erscheinungsdatum :

    2002-01-01


    Anmerkungen:

    Doctoral thesis, UCL (University College London).


    Medientyp :

    Hochschulschrift


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



    Klassifikation :

    DDC:    600 / 629



    High Accuracy Attitude Determination and Control of the Astronomy Satellite DIVA

    Winkler, Stefan / Theil, Stephan / Rath, H.J. | AIAA | 2002


    Three Axis Attitude Control of a Micro Satellite

    Terui, F. / Nakajima, A. | British Library Conference Proceedings | 1996


    Nonlinear Attitude Control of the Micro Satellite ESEO

    Topland, Morten Pedersen / Gravdahl, Jan Tommy | AIAA | 2004