Quaternion models of a rigid body rotation motion and their application for spacecraft attitude control

Yefymenko, Nikolay V.; Кудерметов, Равіль Камілович

doi:10.1016/j.actaastro.2022.01.029

Cited by 13 publications

(2 citation statements)

References 12 publications

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“…Unlike Euler angles, Euler parameters (quaternions) are suitable for large reorientation and attitude tracking maneuvers. Recently, Yefymenko and Kudermetov [17] proposed second-order quaternionic equations for attitude kinematics and dynamics. In the scientific literature, several contributions employed the Euler parameters as the kinematics variables [18][19][20].…”

Section: Introductionmentioning

confidence: 99%

Intersatellite and Downlink Agile Attitude Maneuvers

Posani,

Pontani,

Gasbarri

2023

Applied Sciences

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This research is focused on the problem of agile attitude maneuvering, aimed at the precise pointing of a satellite forming a typical constellation in low Earth orbit. We consider two different operational scenarios: (a) pointing toward a specific ground station, located on the Earth surface (for downlink data routing), and (b) pointing toward a companion satellite (for establishing an intersatellite connection). The two preceding operational requirements can both be formulated as attitude tracking problems. In this study, we use an inertia-free nonlinear attitude control algorithm based on rotation matrices and possessing remarkable stability properties, in conjunction with a pyramidal array of single-gimbal control momentum gyroscopes. Numerical simulations, in both nominal and nonnominal flight conditions, demonstrate that the attitude control architecture proposed in this work is effective for the purpose of performing agile attitude maneuvering, aimed at precise pointing during downlink and intersat data routing.

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Section: Introductionmentioning

confidence: 99%

Intersatellite and Downlink Agile Attitude Maneuvers

Posani,

Pontani,

Gasbarri

2023

Applied Sciences

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“…is the initial position of the spacecraft. Moreover, Q = diag ([20,20,20, 1500, 1500, 2000, 1, 1, 1, 1, 1, 1]), R = diag ([1, 1, 1,10,10,10]) and ρ = 500000 are the obstacle avoidance weight matrices of the spacecraft. However, the weight matrices are adjusted to 0 if there are no obstacles on the trajectory of the spacecraft.Then, to show the effectiveness of the obstruct avoidance of the spacecraft, the parameters of the four obstacles are shown as follow:…”

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confidence: 99%

SE(3) Based LTV-MPC Algorithm for Multi-Obstacle Trajectory Tracking of Fully Driven Spacecraft

Wang,

Peng,

et al. 2024

IEEE Access

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A linear time-varying model predictive control (LTV-MPC) method based on SE(3) is proposed, to solve the problem of the control accuracy and energy consumption of spacecraft. First, left-invariant principle of Lie group, Lie algebra SO(3), and other differential geometry theories are applied to extend LTV-MPC to SE(3). Then, considering the obstacle avoidance problem of the spacecraft in space, a suitable optimization function is selected to ensure smooth tracking of the desired working trajectory. By controlling the incremental output with the fastest convergence rate, the controller enables effective trajectory tracking. Finally, the effectiveness and applicability of the controller are verified by simulation experiments. These simulations validate the controller's ability to achieve constraint satisfaction, optimize transient processes, and enhance control accuracy. The results provide compelling evidence of the controller's potential for real-world spacecraft control applications.

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Quaternion Differential Matrix Equations with Singular Coefficient Matrices

Kyrchei

2024

Qual. Theory Dyn. Syst.

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Quaternion models of a rigid body rotation motion and their application for spacecraft attitude control

Cited by 13 publications

References 12 publications

Intersatellite and Downlink Agile Attitude Maneuvers

Intersatellite and Downlink Agile Attitude Maneuvers

SE(3) Based LTV-MPC Algorithm for Multi-Obstacle Trajectory Tracking of Fully Driven Spacecraft

Quaternion Differential Matrix Equations with Singular Coefficient Matrices

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