MINIMUM ELECTRICAL ENERGY SPACECRAFT MANEUVERS: THEORY AND EXPERIMENTS
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Authors
Culton, Eryn A.
Subjects
energy efficient
attitude control
Optimal Control Theory
reaction wheel spacecraft
attitude control
Optimal Control Theory
reaction wheel spacecraft
Advisors
Karpenko, Mark
Date of Issue
2019-06
Date
Publisher
Monterey, CA; Naval Postgraduate School
Language
Abstract
Reaction wheels are popular satellite attitude control actuators that have been the subject of years of research. Recently, optimal control theory was applied to discover a new reaction wheel control algorithm that steers the spacecraft along an alternate path, minimizing power draw for a system of redundant (four or more) reaction wheels while completing a shortest-time maneuver. This thesis characterizes the energy draw of a particular slewing maneuver using both a conventional attitude maneuver trajectory and trajectories derived using the new concept. In particular, a minimum energy optimal control problem is solved to find efficient energy profiles for a realistic reaction wheel spacecraft attitude control system. These profiles build a maneuver cost tradespace, validating the nonlinear relationship between electrical energy consumption and maneuver duration. To bridge the gap between theory and practice, an experiment is also implemented to test the solutions involving a set of reaction wheels to measure power consumption. Ultimately, an optimal maneuver operating envelope is created and the power model is verified to accurately characterize the power draw of a momentum exchange attitude control system.
Type
Thesis
Description
Series/Report No
Department
Mechanical and Aerospace Engineering (MAE)
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NPS Report Number
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Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.