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Efficient Trajectory Optimization for Constrained Spacecraft Attitude Maneuvers Using Momentum Exchange Devices.

Record Type:	Language materials, manuscript : Monograph/item
Title/Author:	Efficient Trajectory Optimization for Constrained Spacecraft Attitude Maneuvers Using Momentum Exchange Devices./
Author:	Dearing, Thomas Lee.
Description:	1 online resource (112 pages)
Notes:	Source: Dissertations Abstracts International, Volume: 84-11, Section: B.
Contained By:	Dissertations Abstracts International84-11B.
Subject:	Electrical engineering. -
Online resource:	click for full text (PQDT)
ISBN:	9798379528089

Efficient Trajectory Optimization for Constrained Spacecraft Attitude Maneuvers Using Momentum Exchange Devices.
Dearing, Thomas Lee.

Efficient Trajectory Optimization for Constrained Spacecraft Attitude Maneuvers Using Momentum Exchange Devices. - 1 online resource (112 pages)

Source: Dissertations Abstracts International, Volume: 84-11, Section: B.

Thesis (Ph.D.)--University of Colorado at Boulder, 2023.

Includes bibliographical references

Existing solutions for spacecraft attitude control have historically accommodated the limited processing power of spacecraft CPU's through the use of simplified dynamical models and traditional feedback laws. However, while such approximations improve the computational complexity (and reliability) of the resulting control solutions (a necessary feature for a viable Attitude Determination and Control System (ADCS)), the maximum performance of control strategies developed under these simplified dynamics is limited compared to the potential capabilities of the physical system. In contrast, this thesis examines the optimal control behaviors and performance capabilities of physical spacecraft dynamical models by developing and solving trajectory optimization problems for rest-to-rest attitude maneuvers under standard operational constraints on input saturation, maximum angular rates, and solar exclusion cones.In particular, this thesis examines three problems: (1) maneuvers planned using traditional abstract body torques and approximated dynamics (a model problem to validate the solver), (2) maneuvers planned using a comprehensive, momentum-conserving model for a spacecraft CMG array, and (3) the latter problem augmented with an accurate model for the array's energy usage. In each case, the optimal solutions guarantee constraint feasibility and present substantial performance improvements over the original guess (determined in most cases using accepted feedback solutions). Additionally, the proper energy penalty employed in the final case yields substantially improved performance and efficiency over the accepted Singularity-Robust (SR) feedback law, with this increased performance correlating with several notable control behaviors observed across the solution family: (a) a model torque profile for the CMG array analogous to the initial and final burns used in orbital transitions and (b) variable CMG wheel speed regulation which is largely inactive during the maneuver's 'cruise' phase. Finally, potential adaptations of existing feedback control solutions which incorporate the above behaviors are proposed, achieving the corresponding performance improvements without the computational burden of strict optimality.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2024

Mode of access: World Wide Web

ISBN: 9798379528089Subjects--Topical Terms:

596380
Electrical engineering.
Subjects--Index Terms:

Attitude controlIndex Terms--Genre/Form:

554714
Electronic books.

Efficient Trajectory Optimization for Constrained Spacecraft Attitude Maneuvers Using Momentum Exchange Devices.
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520 $a Existing solutions for spacecraft attitude control have historically accommodated the limited processing power of spacecraft CPU's through the use of simplified dynamical models and traditional feedback laws. However, while such approximations improve the computational complexity (and reliability) of the resulting control solutions (a necessary feature for a viable Attitude Determination and Control System (ADCS)), the maximum performance of control strategies developed under these simplified dynamics is limited compared to the potential capabilities of the physical system. In contrast, this thesis examines the optimal control behaviors and performance capabilities of physical spacecraft dynamical models by developing and solving trajectory optimization problems for rest-to-rest attitude maneuvers under standard operational constraints on input saturation, maximum angular rates, and solar exclusion cones.In particular, this thesis examines three problems: (1) maneuvers planned using traditional abstract body torques and approximated dynamics (a model problem to validate the solver), (2) maneuvers planned using a comprehensive, momentum-conserving model for a spacecraft CMG array, and (3) the latter problem augmented with an accurate model for the array's energy usage. In each case, the optimal solutions guarantee constraint feasibility and present substantial performance improvements over the original guess (determined in most cases using accepted feedback solutions). Additionally, the proper energy penalty employed in the final case yields substantially improved performance and efficiency over the accepted Singularity-Robust (SR) feedback law, with this increased performance correlating with several notable control behaviors observed across the solution family: (a) a model torque profile for the CMG array analogous to the initial and final burns used in orbital transitions and (b) variable CMG wheel speed regulation which is largely inactive during the maneuver's 'cruise' phase. Finally, potential adaptations of existing feedback control solutions which incorporate the above behaviors are proposed, achieving the corresponding performance improvements without the computational burden of strict optimality.
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653 $a Trajectory optimization
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