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Please use this identifier to cite or link to this item: http://hdl.handle.net/1807/29545

Title: Attitude Determination and Control Hardware Development for Small Satellites
Authors: Fournier, Marc
Advisor: Zee, Robert E.
Department: Aerospace Science and Engineering
Keywords: Attitude Determination and Control Hardware Development for Small Satellites
Issue Date: 24-Aug-2011
Abstract: The development of a small spacecraft attitude determination and control subsystem is described. This subsystem is part of The Space Flight Laboratory's Generic Nanosatellite Bus. With a 20cm3 body, the bus has an attitude determination and control subsystem capable of full three-axis stabilization and control enabling more advanced missions previously only possible with bulkier and more power-consuming attitude control hardware. Specific contributions to the Space Flight Lab's attitude control hardware are emphasised. Particularly, the full development of a 32g three-axis nanosatellite rate sensing unit is described. This includes embedded software development, skew calibration, hardware modeling and qualification testing for the unit. Development work on a three-axis boom-mounted magnetometer is also detailed. A full hardware design is also described for a new microsatellite-sized rate sensor. Larger and more powerful than the nanosatellite rate sensors, the design ensures a low noise, low drift architecture to improve attitude determination on future microsatellite missions.
URI: http://hdl.handle.net/1807/29545
Appears in Collections:Master

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