Attitude Coordination Control for Flexible Spacecraft Formation Flying With Guaranteed Performance Bounds

Xiao, Yan; Ruiter, Anton de; Ye, Dong; Sun, Zhaowei

doi:10.1109/taes.2022.3201812

Cited by 8 publications

(5 citation statements)

References 36 publications

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“…In equation (15), under the certain premise of m, the algorithm time complexity increases exponentially with the increase of n. Therefore, the time complexity of the SQP algorithm is negligible compared to that of the DFS algorithm, 25,26 which is…”

Section: Analysis Of the Time Complexitymentioning

confidence: 99%

“…When ε2 in equation (2) is 0, the orbit extrapolation equation (5) and component equation (6) can be numerically integrated. 15,16 This can calculate the observation time Ti which satisfies the observation constraint conditions. Let the shortest time to complete orbital phase modulation be Tmin, and the shortest time Ti is T when the Ti>Tmin condition is satisfied…”

Section: Problem Description and Constraintsmentioning

confidence: 99%

See 1 more Smart Citation

Research on optimization method for flyby observation mission adapted to satellite on-board computation

Wang,

Xiao,

et al. 2024

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this paper, the optimization problem of orbital transfer strategy for orbital flyby observation missions is studied. A hybrid optimization method is proposed, which is improved to make it more suitable for satellite on-board computing. This new algorithm is designed to solve the initial value sensitivity problem of the sequential quadratic programming algorithm (SQP). It is consisted of the depth-first search algorithm (DFS) and the SQP algorithm and thus has the characteristics of fast convergence, high reliability, and good robustness. With this method, the DFS with a large step size is calculated first, and then the optimal value in the calculation result is used as the initial value of the SQP algorithm for further optimization. This method can obtain the approximate optimal solution available in engineering. The numerical simulation of an orbital transfer optimization problem is set to verify the effectiveness of the new hybrid algorithm. The simulation results compared with the genetic algorithm (GA) show that the proposed hybrid algorithm can effectively reduce the on-board resource occupation when getting similar results and thus can meet the needs of satellite on-board computing.

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Section: Analysis Of the Time Complexitymentioning

confidence: 99%

Section: Problem Description and Constraintsmentioning

confidence: 99%

Research on optimization method for flyby observation mission adapted to satellite on-board computation

Wang,

Xiao,

et al. 2024

Proceedings of the Institution of Mechanical Engineers, Part G:

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show abstract

“…Generally, the initial values of the control parameters are set based on theoretical analysis and engineering experience, then these parameters are adjusted through many numerical simulations until the relevant dynamic indicators of the system satisfy the project requirements [16]. Such an operation that presets partial parameters not only restricts the coupling relationship between the error states in the controller but also predetermines the stable hovering accuracy of the system states, thus affecting the robustness of the designed controller [17,18]. In addition, the expression of the unmatched disturbance is also determined by the prescribed control parameters.…”

Section: Introductionmentioning

confidence: 99%

Feasibility Analysis and Synchronization Control for Underactuated Spacecraft Formation Hovering

Shao

Zhou

et al. 2024

IEEE Trans. Contr. Syst. Technol.

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This paper develops a synchronization control scheme for underactuated spacecraft formation hovering in the case without along-track thrust. The feasible sets of initial positions for this underactuated case are derived based on the nonlinear and linear relative orbital dynamics. Then, a nonpreset parameter underactuated controller is designed to deal with the unmatched disturbances caused by the loss of alongtrack control. Moreover, a synchronization item is added to the above controller to synchronize the hovering motion between the follower spacecraft. The Lyapunov-based analysis indicates that the minimum nonzero eigenvalue of the Laplace matrix corresponding to the synchronization item determines the stable hovering accuracy of the system states. Numerical simulations also demonstrate the validity of the presented underactuated synchronization controller.

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“…The command filter backstepping control method was employed to address the limitations of other methods such as dynamic surface control and tracking-differentiator-based control. On the other hand, it is important to acknowledge that unmodeled dynamics are inherent in real-world systems owing to various factors such as modeling inaccuracies, external disturbances, and measurement noise [14][15][16][17][18]. These unmodeled dynamics can significantly degrade system performance and even cause instability.…”

Section: Introductionmentioning

confidence: 99%

Adaptive Fuzzy Fixed-Time Control for Nonlinear Systems with Unmodeled Dynamics

Luo,

Zhang,

et al. 2024

Symmetry

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This article concentrates on the problem of fixed-time tracking control for a certain class of nonlinear systems with unmodeled dynamics. Unmodeled dynamics are prevalent in practical engineering systems, such as axially symmetric systems like robotic arms, spacecraft, and missiles. In this paper, the fuzzy-logic systems (FLSs) are implemented to address the challenge of accurately approximating the unknown nonlinear terms that arise during the derived control algorithm process. By employing fixed-time command filters (FTCF), the “explosion of complexity” issues encountered in traditional backstepping methods will be effectively resolved. Moreover, error compensation mechanisms are derived to effectively mitigate the filtering errors that may arise from the FTCFs. The computational burden associated with FLSs is reduced through the utilization of the weight vector estimation method based on the maximal norm and an adaptive approach. A fixed-time adaptive fuzzy tracking controller is developed within the backstepping control framework to ensure the boundedness of all signals and achieve fixed-time convergence of the tracking error for the controlled system. Illustrative examples are conducted to illustrate the viability of the derived controller.

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Attitude Coordination Control for Flexible Spacecraft Formation Flying With Guaranteed Performance Bounds

Cited by 8 publications

References 36 publications

Research on optimization method for flyby observation mission adapted to satellite on-board computation

Research on optimization method for flyby observation mission adapted to satellite on-board computation

Feasibility Analysis and Synchronization Control for Underactuated Spacecraft Formation Hovering

Adaptive Fuzzy Fixed-Time Control for Nonlinear Systems with Unmodeled Dynamics

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