An impulsive model predictive static programming based station-keeping guidance for quasi-halo orbits

In this paper, a control effort minimizing optimal station-keeping guidance is designed and implemented to regulate a spacecraft around an L1 quasi-halo orbit in the Sun–Earth–Moon elliptic four-body problem. The station-keeping guidance is formulated as a finite time, non-linear optimal control pro...

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Veröffentlicht in:	Acta astronautica Jg. 188; S. 518 - 530
Hauptverfasser:	Vutukuri, Srianish, Padhi, Radhakant
Format:	Journal Article
Sprache:	Englisch
Veröffentlicht:	Elmsford Elsevier Ltd 01.11.2021 Elsevier BV
Schlagworte:	Algorithms Circular restricted three body problem Constraint modelling Cost function Elliptic four body problem Four body problem Iterative methods Maneuvers Model predictive static programming Nonlinear control Optimal control Optimization Quasi-halo orbits Spacecraft Spacecraft guidance Station-keeping Terminal constraints Circular restricted three body problem Elliptic four body problem Quasi-halo orbits Station-keeping Model predictive static programming
ISSN:	0094-5765, 1879-2030
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Abstract	In this paper, a control effort minimizing optimal station-keeping guidance is designed and implemented to regulate a spacecraft around an L1 quasi-halo orbit in the Sun–Earth–Moon elliptic four-body problem. The station-keeping guidance is formulated as a finite time, non-linear optimal control problem with hard terminal output constraints and Impulsive Model Predictive Static Programming (I-MPSP) is used to obtain station-keeping maneuvers. The algorithm is iterative, where the guessed station-keeping maneuvers are optimally updated by a simple closed-form equation until an output terminal constraint is satisfied and an optimal cost function is obtained. The technique involves the calculation of sensitivity matrices that is done in a computationally efficient manner owing to their recursive nature. Through extensive simulations, in the presence of disturbance forces and uncertainties, a closed-loop application of I-MPSP guidance results in a trajectory that remains tightly bound to the reference orbit over a long-duration mission. •Impulsive MPSP guidance is proposed for station keeping on quasi-halo orbits.•This computational guidance ensures control energy minimization.•It exhibits rapid convergence and demands minimal computational time.•Robustness analysis shows it can effectively handle disturbances and uncertainties.•Spacecraft trajectories are tightly bound to the reference orbit during the entire mission.
AbstractList	In this paper, a control effort minimizing optimal station-keeping guidance is designed and implemented to regulate a spacecraft around an L1 quasi-halo orbit in the Sun–Earth–Moon elliptic four-body problem. The station-keeping guidance is formulated as a finite time, non-linear optimal control problem with hard terminal output constraints and Impulsive Model Predictive Static Programming (I-MPSP) is used to obtain station-keeping maneuvers. The algorithm is iterative, where the guessed station-keeping maneuvers are optimally updated by a simple closed-form equation until an output terminal constraint is satisfied and an optimal cost function is obtained. The technique involves the calculation of sensitivity matrices that is done in a computationally efficient manner owing to their recursive nature. Through extensive simulations, in the presence of disturbance forces and uncertainties, a closed-loop application of I-MPSP guidance results in a trajectory that remains tightly bound to the reference orbit over a long-duration mission. In this paper, a control effort minimizing optimal station-keeping guidance is designed and implemented to regulate a spacecraft around an L1 quasi-halo orbit in the Sun–Earth–Moon elliptic four-body problem. The station-keeping guidance is formulated as a finite time, non-linear optimal control problem with hard terminal output constraints and Impulsive Model Predictive Static Programming (I-MPSP) is used to obtain station-keeping maneuvers. The algorithm is iterative, where the guessed station-keeping maneuvers are optimally updated by a simple closed-form equation until an output terminal constraint is satisfied and an optimal cost function is obtained. The technique involves the calculation of sensitivity matrices that is done in a computationally efficient manner owing to their recursive nature. Through extensive simulations, in the presence of disturbance forces and uncertainties, a closed-loop application of I-MPSP guidance results in a trajectory that remains tightly bound to the reference orbit over a long-duration mission. •Impulsive MPSP guidance is proposed for station keeping on quasi-halo orbits.•This computational guidance ensures control energy minimization.•It exhibits rapid convergence and demands minimal computational time.•Robustness analysis shows it can effectively handle disturbances and uncertainties.•Spacecraft trajectories are tightly bound to the reference orbit during the entire mission.
Author	Vutukuri, Srianish Padhi, Radhakant
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Cites_doi	10.1016/j.asr.2009.10.023 10.2514/1.G001850 10.1016/0094-5765(87)90175-5 10.1142/S230138501950002X 10.2514/1.28738 10.2514/1.G003115 10.2514/1.53647 10.2514/6.2012-4665 10.3182/20140313-3-IN-3024.00172 10.1016/j.actaastro.2013.01.022 10.1016/j.actaastro.2018.02.004 10.1016/j.asr.2013.09.021 10.2514/1.G003990 10.2514/1.G002845 10.2514/3.11440
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Keywords	Circular restricted three body problem Elliptic four body problem Quasi-halo orbits Station-keeping Model predictive static programming
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Snippet	In this paper, a control effort minimizing optimal station-keeping guidance is designed and implemented to regulate a spacecraft around an L1 quasi-halo orbit...
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SubjectTerms	Algorithms Circular restricted three body problem Constraint modelling Cost function Elliptic four body problem Four body problem Iterative methods Maneuvers Model predictive static programming Nonlinear control Optimal control Optimization Quasi-halo orbits Spacecraft Spacecraft guidance Station-keeping Terminal constraints
Title	An impulsive model predictive static programming based station-keeping guidance for quasi-halo orbits
URI	https://dx.doi.org/10.1016/j.actaastro.2021.07.041 https://www.proquest.com/docview/2584777517
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