Sub-optimal fixed-finite-horizon spacecraft configuration control on SE(3)

Wang, Yulin; Shang, Wei; Hong, Haichao

doi:10.1016/j.cja.2021.07.023

Cited by 3 publications

(4 citation statements)

References 35 publications

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“…( 11) -( 14 Remark1: The model predictive control does not take into account the problem of fuel minimization and is not efficient in calculation. Wang proposed model predictive static programming control on SE(3) [28]. Although the problem of fuel minimization is effectively solved, MPSP can only solve a class of control problems with terminal constraints.…”

Section: Control Law Designmentioning

confidence: 99%

“…And the optimal control problem for the combined three-dimensional orbital and rotational motion of a rigid body is presented in the literature [27], and an effective computational method is given. In [28], model predictive static programming (MPSP) is applied to SE(3) to optimize the spacecraft operation with the critical energy consumption as the objective function, so as to achieve optimal control. However, the methods mentioned above have the following drawbacks: The methods in [24], [25] are all based on linearization, which can only solve a class of linearization problem, and the applicable range is too small.…”

Section: Introductionmentioning

confidence: 99%

“…However, the methods mentioned above have the following drawbacks: The methods in [24], [25] are all based on linearization, which can only solve a class of linearization problem, and the applicable range is too small. The method designed in [27] needs to solve the two-point edge value problem, which has a high computational complexity and is not conducive to using in practical engineering applications.The MPSP proposed in the literature [28] does not consider the control input constraint problem in the control process. This can lead to the problem of unconstrained input as well as input discontinuity.…”

Section: Introductionmentioning

confidence: 99%

“…Compared with the methods studied in the previous section [24], [25], [27], [28], the innovations of this paper are as follows:…”

Section: Introductionmentioning

confidence: 99%

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Integrated Geometric Optimal Control of Spacecraft Attitude and Orbit Based on SE(3)

et al. 2023

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A model predictive convex programming (MPCP) on SE(3) parametrized by trigonometric series control is proposed in this paper, to solve the optimal control problem of spacecraft attitude orbit integration. Firstly, the geometric modeling of the spacecraft with six degrees of freedom for the attitude orbit integration is performed by the differential manifold SE(3) , which can effectively avoid the problems of ambiguity, receding winding, and singularity that occurs in the conventional methods for rigid body attitude description. Then, based on differential geometric theories, such as the variational principle, the left-invariant principle of Lie group, and the topology of Lie algebraic space, MPCP is applied to SE(3) . It can solve a class of optimization problems with process constraints and control input constraints during spacecraft flight. Furthermore, a control framework of trigonometric series is constructed, which is seamlessly integrated into MPCP to achieve smoother trajectory optimization control. Finally, the practicality and effectiveness of the proposed method are verified by numerical simulation.

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Section: Control Law Designmentioning

confidence: 99%