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High accuracy attitude control of a micro-satellite

Kim, Byung Jin; (2002) High accuracy attitude control of a micro-satellite. Doctoral thesis (Ph.D), UCL (University College London). Green open access

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Abstract

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 result. Initial detumbling and momentum dumping laws were proposed to increase the control efficiency. Large angle manoeuvring scheme using error quaternion feedback control was modified for small satellite application where torque and momentum capacities were severely limited. Kalman filtering technique was applied for gyro bias estimation and compensation. Actual in-flight attitude telemetry data were analysed to verify the control performance.

Type: Thesis (Doctoral)
Qualification: Ph.D
Title: High accuracy attitude control of a micro-satellite
Open access status: An open access version is available from UCL Discovery
Language: English
Additional information: Thesis digitised by ProQuest.
Keywords: Applied sciences; Satellite miniaturisation
URI: https://discovery.ucl.ac.uk/id/eprint/10097272
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