Safety-Critical Attitude Tracking of Spacecraft With Data-Based Parameter Identification

This article proposes a safety-critical control strategy for the attitude tracking issue of a rigid spacecraft subject to orientation and angular velocity constraints. To compensate for the unknown inertial matrix parameters, an online identification algorithm with a data-based selection criteria is...

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Vydané v:IEEE transactions on aerospace and electronic systems Ročník 61; číslo 2; s. 1353 - 1362
Hlavní autori: Xia, Kewei, Wang, Jianan, Liu, Fuxiang
Médium: Journal Article
Jazyk:English
Vydavateľské údaje: New York IEEE 01.04.2025
The Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Predmet:
Algorithms
Angular velocity
Attitude control
Closed loops
Constraints
Control barrier function (CBF)
Feedback control
Iron
Logic programming
Parameter identification
Quadratic programming
Quaternions
Safety critical
Simulation
Space vehicles
Spacecraft attitude control
spacecraft attitude tracking
Spacecraft tracking
state constraints
Torque
Tracking control
unwinding avoidance
Vectors
ISSN:0018-9251, 1557-9603
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Abstract This article proposes a safety-critical control strategy for the attitude tracking issue of a rigid spacecraft subject to orientation and angular velocity constraints. To compensate for the unknown inertial matrix parameters, an online identification algorithm with a data-based selection criteria is first designed, which shows that the estimate error is exponentially convergence if a finite excitation condition is satisfied. Then, by introducing the identified parameters, an adaptive hybrid attitude tracking control torque is developed, where a binary logic switch framework is employed to avoid the unwinding phenomenon. For the sake of safety-critical tracking subject to state constraints, a control barrier function quadratic programming optimization is developed, where the nonconvex orientation constraints are losslessly replaced by convex quadratic ones. The uniform asymptotic stability of the closed-loop system is proved, and the preassigned safety sets are forward invariant with the largest safe region. Simulation results validate and access the proposed control strategy.
AbstractList This article proposes a safety-critical control strategy for the attitude tracking issue of a rigid spacecraft subject to orientation and angular velocity constraints. To compensate for the unknown inertial matrix parameters, an online identification algorithm with a data-based selection criteria is first designed, which shows that the estimate error is exponentially convergence if a finite excitation condition is satisfied. Then, by introducing the identified parameters, an adaptive hybrid attitude tracking control torque is developed, where a binary logic switch framework is employed to avoid the unwinding phenomenon. For the sake of safety-critical tracking subject to state constraints, a control barrier function quadratic programming optimization is developed, where the nonconvex orientation constraints are losslessly replaced by convex quadratic ones. The uniform asymptotic stability of the closed-loop system is proved, and the preassigned safety sets are forward invariant with the largest safe region. Simulation results validate and access the proposed control strategy.
Author Wang, Jianan
Liu, Fuxiang
Xia, Kewei
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SubjectTerms Algorithms
Angular velocity
Attitude control
Closed loops
Constraints
Control barrier function (CBF)
Feedback control
Iron
Logic programming
Parameter identification
Quadratic programming
Quaternions
Safety critical
Simulation
Space vehicles
Spacecraft attitude control
spacecraft attitude tracking
Spacecraft tracking
state constraints
Torque
Tracking control
unwinding avoidance
Vectors
Title Safety-Critical Attitude Tracking of Spacecraft With Data-Based Parameter Identification
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https://www.proquest.com/docview/3188884818
Volume 61
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