A fluid loop actuator for active spacecraft attitude control - A Parametric Sizing Model and the Design, Verification, Validation and Test with a Prototype on an Air Bearing

 

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dc.contributor.advisor Martinez, Peter
dc.contributor.author Martens, Bas
dc.date.accessioned 2020-03-18T13:52:55Z
dc.date.available 2020-03-18T13:52:55Z
dc.date.issued 2019
dc.identifier.citation Martens, B. 2019. A fluid loop actuator for active spacecraft attitude control - A Parametric Sizing Model and the Design, Verification, Validation and Test with a Prototype on an Air Bearing. . ,Engineering and the Built Environment ,Department of Electrical Engineering. en_ZA
dc.identifier.uri https://hdl.handle.net/11427/31621
dc.description.abstract Active spacecraft attitude control by using a pumped fluid as the inertial mass has potential advantages over reaction wheels, including high torque, lower power consumption, reduced jitter and prolonged lifetime. Previous work addressed conceptual and mission-specific control aspects, and one fluid loop has flown on a demonstration mission. In this dissertation, a parametric sizing model is developed that can optimize a fluid loop for any mission, based on pump capabilities and customer requirements. The model can be applied to circular, square and helical fluid loops, and includes the power consumption due to viscous friction. A configurable prototype was developed to verify the model, as well as a spherical air bearing to verify the rotational aspects of the various fluid loop configurations. The model was applied to various hypothetical missions. In conclusion, the fluid loop has the fundamental potential to replace reaction wheels in a wide variety of satellites above approximately 20 kg, if mass is carefully optimized and efforts are made to develop a suitable pump. This is considered worthwhile, as the actuator comes with many potential advantages.
dc.subject Space Studies
dc.title A fluid loop actuator for active spacecraft attitude control - A Parametric Sizing Model and the Design, Verification, Validation and Test with a Prototype on an Air Bearing
dc.type Thesis / Dissertation
dc.date.updated 2020-03-17T13:07:56Z
dc.language.rfc3066 eng
dc.publisher.faculty Engineering and the Built Environment
dc.publisher.department Department of Electrical Engineering
dc.type.qualificationlevel Masters
dc.type.qualificationname MPhil
dc.identifier.apacitation Martens, B. (2019). <i>A fluid loop actuator for active spacecraft attitude control - A Parametric Sizing Model and the Design, Verification, Validation and Test with a Prototype on an Air Bearing</i>. (). ,Engineering and the Built Environment ,Department of Electrical Engineering. Retrieved from en_ZA
dc.identifier.chicagocitation Martens, Bas. <i>"A fluid loop actuator for active spacecraft attitude control - A Parametric Sizing Model and the Design, Verification, Validation and Test with a Prototype on an Air Bearing."</i> ., ,Engineering and the Built Environment ,Department of Electrical Engineering, 2019. en_ZA
dc.identifier.vancouvercitation Martens B. A fluid loop actuator for active spacecraft attitude control - A Parametric Sizing Model and the Design, Verification, Validation and Test with a Prototype on an Air Bearing. []. ,Engineering and the Built Environment ,Department of Electrical Engineering, 2019 [cited yyyy month dd]. Available from: en_ZA
dc.identifier.ris TY - Thesis / Dissertation AU - Martens, Bas AB - Active spacecraft attitude control by using a pumped fluid as the inertial mass has potential advantages over reaction wheels, including high torque, lower power consumption, reduced jitter and prolonged lifetime. Previous work addressed conceptual and mission-specific control aspects, and one fluid loop has flown on a demonstration mission. In this dissertation, a parametric sizing model is developed that can optimize a fluid loop for any mission, based on pump capabilities and customer requirements. The model can be applied to circular, square and helical fluid loops, and includes the power consumption due to viscous friction. A configurable prototype was developed to verify the model, as well as a spherical air bearing to verify the rotational aspects of the various fluid loop configurations. The model was applied to various hypothetical missions. In conclusion, the fluid loop has the fundamental potential to replace reaction wheels in a wide variety of satellites above approximately 20 kg, if mass is carefully optimized and efforts are made to develop a suitable pump. This is considered worthwhile, as the actuator comes with many potential advantages. DA - 2019 DB - OpenUCT DP - University of Cape Town KW - Space Studies LK - https://open.uct.ac.za PY - 2019 T1 - A fluid loop actuator for active spacecraft attitude control - A Parametric Sizing Model and the Design, Verification, Validation and Test with a Prototype on an Air Bearing TI - A fluid loop actuator for active spacecraft attitude control - A Parametric Sizing Model and the Design, Verification, Validation and Test with a Prototype on an Air Bearing UR - ER - en_ZA


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