Underactuated spacecraft formation reconfiguration with collision avoidance

Huang, Xu; Yan, Ye; Zhou, Yang

doi:10.1016/j.actaastro.2016.11.037

Cited by 48 publications

(24 citation statements)

References 32 publications

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“…Typically, for a relative distance within 100 km, the relative error resulting from the linearization is less than 0.03%. 27,28 Therefore, in view of the formation size discussed in this paper, which is about several kilometers, the linearization holds throughout this paper.…”

Section: Dynamical Analysis Of Underactuated Sff Dynamical Modelmentioning

confidence: 99%

Dynamics and control of underactuated spacecraft formation reconfiguration in elliptic orbits

Huang

Yan

Zhou

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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Feasibility of underactuated formation reconfiguration in elliptic orbits without radial or in-track thrust is investigated in this paper. For either underactuated case, by using a linear time-varying dynamical model of spacecraft formation, controllability and feasibility analyses are conducted, based on which the preconditions on reconfigurable formations are then derived. With the inherent coupling of system dynamics, the reduced-order sliding mode control technique is employed to design a closed-loop underactuated controller for either case. To ensure the stability of the closed-loop system, the conditions imposed on the controller parameters are derived, and the parameter adaptation laws are then solved analytically. Meanwhile, the explicit relationships between the steady accuracies of system states and the controller parameters are obtained via a Lyapunov-based approach. Numerical examples are simulated in a J 2-perturbed environment to validate the theoretical analyses. The results indicate that by using the proposed control schemes, underactuated reconfiguration in elliptic orbits is still feasible even in the absence of radial or in-track thrust and in the presence of unmatched disturbances.

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Section: Dynamical Analysis Of Underactuated Sff Dynamical Modelmentioning

confidence: 99%

Dynamics and control of underactuated spacecraft formation reconfiguration in elliptic orbits

Huang

Yan

Zhou

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Therefore, the requirements for satellite function and performance are getting higher and higher [4], [5]. Formation flying of multiple satellites can complete complex tasks with less fuel and higher efficiently than a single large satellite [6]. This paper mainly studies the formation reconfiguration of close-range formation flying of multiple satellites.…”

Section: Introductionmentioning

confidence: 99%

Fast Cooperative Trajectory Optimization for Close-Range Satellite Formation Using Bezier Shape-Based Method

Fan

Huo

et al. 2020

IEEE Access

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Close-range formation flying of multiple satellites is an important technology for future space missions, where formation reconfiguration is a very important field and needs to design suitable flight paths and consider the risk of collisions between satellites. This paper uses the Bezier shape-based (SB) method to rapidly generate the low-thrust collision-avoidance flight paths in the formation reconfiguration. The reconfiguration process of two satellite formations is considered and compared with the finite Fourier series (FFS) method. The simulation results show that the Bezier method spends less computation time to obtain better performance index than the FFS method. In order to verify the applicability of the results obtained by the Bezier method to a direct solver, the results are applied to the Gauss pseudospectral method (GPM) solver as an initial guess. The results show that the Bezier method can take a short time to design suitable initial collision-avoidance flight paths for an direct optimization solver. This is very important for the rapid feasibility evaluation of numerous flight scenarios at the stage of initial mission design and onboard flight paths generation. INDEX TERMS Bezier shape-based method, close-range satellites formation, collision-avoidance, low-thrust trajectory approximation, preliminary mission analysis.

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“…The capacity of accurate control and collision/obstacle avoidance is desperately required to guarantee the security of all the spacecraft in the SFR, but only limited solutions have been presented for this problem. ()…”

Section: Introductionmentioning

confidence: 99%

“…Comparison with existing results . In contrast with the coordination control algorithms for SFR,() we commit to reduce the algorithm conservatism and to achieve high control precision, which can be realized by the finite‐time control theory. Comparing with the optimal control strategy without obstacle/collision avoidance, we aim to design a new control scheme for SFR with finite‐time convergence and obstacle/collision avoidance.…”

Section: Introductionmentioning

confidence: 99%

Neural network–based reconfiguration control for spacecraft formation in obstacle environments

Zhou

Chen

Xia

et al. 2018

Intl J Robust & Nonlinear

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Summary This paper proposes an adaptive formation reconfiguration control scheme based on the leader‐follower strategy for multiple spacecraft systems. By taking the predesigned desired velocities and the trajectories as reference signals, a set of coordination tracking controllers is constructed by combining the reconstructed dynamic system and the neural network–based reconfiguration algorithm together. To avoid collisions between spacecraft and obstacles during the formation configuration process, the null space–based behavioral control is integrated into the control design. Since the spacecraft dynamics contains unknown nonlinearity and disturbance, it is challenging to make the system robust to uncertainties and improve the control precision simultaneously. To solve this problem, both the adaptive neural network strategy and the finite‐time control theory are employed. Finally, 2 simulation examples are carried out to verify the proposed algorithm, showing that the formation reconfiguration task can be executed successfully while achieving high control precision.

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Underactuated spacecraft formation reconfiguration with collision avoidance

Cited by 48 publications

References 32 publications

Dynamics and control of underactuated spacecraft formation reconfiguration in elliptic orbits

Dynamics and control of underactuated spacecraft formation reconfiguration in elliptic orbits

Fast Cooperative Trajectory Optimization for Close-Range Satellite Formation Using Bezier Shape-Based Method

Neural network–based reconfiguration control for spacecraft formation in obstacle environments

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