Nonlinear Optimal Control of Relative Rotational and Translational Motion of Spacecraft Rendezvous

Navabi, M.; Akhloumadi, Mahdi

doi:10.1061/(asce)as.1943-5525.0000749

Cited by 31 publications

(6 citation statements)

References 24 publications

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“…A large number of guidance and control methods for orbital transfer have been researched in RVD missions [14,15]. Considering the collision avoidance with the target, optimal control based guidance methods have been widely used [16][17][18].…”

Section: Mathematical Problems In Engineeringmentioning

confidence: 99%

Automated Orbital Transfer and Hovering Control Using Artificial Potential

Wang

Zhang

2019

Mathematical Problems in Engineering

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On-orbit servicing for GEO targets has attracted great attention due to particular significance. In this study, the GEO nearby flying is considered, which denotes that the servicing spacecraft approaches GEO targets within tens of meters. Based on the analysis of differential spherical Earth gravity, J2 perturbation, third-body perturbation, and solar radiation pressure (SRP) between two spacecraft, a relative dynamics of GEO nearby flying is built, in which the differential SRP has great influence on relative motion. Therein, considering the differential SRP, an analytical solution to relative dynamics is obtained, which is an extension to CW equation’s solution. Based on the derived relative dynamics, a novel control method utilizing feedback compensation and artificial potential is developed for spacecraft orbital transfer and hovering at the desired position. During orbital transfer, a bounded space is constrained with maximum and minimum relative distance between two spacecraft. An improved repulsive potential based on Gauss function is designed to drive the servicer off the bound and guarantee the potential value converge to zero at the desired position. Meanwhile, a novel attractive potential about relative distance that drives the servicer to the desired position and to hover with high accuracy against perturbations is designed. Besides, a velocity potential with variable gain is designed to ensure that the servicer achieve the desired position without overshoot. The stability of the system is proved with Lyapunov theory, and the feasibility of the proposed control law is verified through numerical simulations with obvious advantages.

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Section: Mathematical Problems In Engineeringmentioning

confidence: 99%

Automated Orbital Transfer and Hovering Control Using Artificial Potential

Wang

Zhang

2019

Mathematical Problems in Engineering

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“…There are many linear controllers in previous decades for the linear relative orbital model, but they are unsuitable for the complicated and modern practical requirements for highperformance rendezvous and docking missions. Therefore, many advanced nonlinear controllers were proposed based on the nonlinear relative attitude and orbital dynamical mode in recent years, such as the adaptive output feedback controller [2], the line-of-sight based state feedback controllers [3], the model predictive controllers [4] [5], the classical proportionalintegrative-derivative controller [6], state-dependent Riccati equation based nonlinear optimal controller [7], the modelbased backstepping controller [8] and sliding mode controller [9]. However, since the convergent time of the system states are generally prescribed by the designers in advance such that the controlled spacecraft system should have a finite-time controller to achieve the missions from the initial system states.…”

Section: Introductionmentioning

confidence: 99%

Finite-Time Relative Pose Tracking Control for Uncertain Spacecraft Rendezvous and Docking

Sun

Wang

Jiang

2021

2021 33rd Chinese Control and Decision Conference (CCDC)

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This study investigates the robust finite-time pose tracking control for spacecraft autonomous rendezvous and docking with parametric uncertainties and bounded external disturbances. Based on the uncertainly coupled relative pose dynamics, a fast terminal sliding mode controller is developed to achieve the finite-time convergence of the pose tracking errors. To reduce the control chattering results from the signum function in the controller, an exponential reaching law is employed to achieve the decreasing of the reaching time towards the sliding surface. The explicit tuning rules for designing parameters are derived based on the stability analysis of the closed-loop system. It is proved in Lyapunov framework that all closed-loop signals are always kept bounded and the pose tracking error converges to small neighborhood of zero in finite time. Simulation results validate the performance of the proposed robust finite-time control strategy.

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“…Orbital transfer under continuous thrust can be carried out rapidly with strong maneuver ability and has been a hot topic in aerospace field research. 1–4 The spacecraft trajectory optimization problem under high continuous thrust poses more challenges and causes many difficulties in the optimization process due to the high non-linearity of control equations and the tendency to produce multi-peak results. Moreover, even if the optimal control result for the single continuous large thrust can be achieved theoretically, it is still difficult to achieve it in real-world space operation.…”

Section: Introductionmentioning

confidence: 99%

Optimal control of rapid cooperative spacecraft rendezvous with multiple specific-direction thrusts

Feng

Yang

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Focusing on the long-distance rapid cooperative rendezvous of two spacecraft under finite continuous thrust, this paper proposes a practical strategy for space operation using multiple specific-direction thrusts. Based on the orbital dynamic theory and Pontryagin’s maximum principle, the dynamic equations and optimal control equations for radial, circumferential, and normal thrust are determined. The optimization method is a hybrid algorithm. The initial costate variables for the fuel-optimal rapid cooperative rendezvous problem are obtained using quantum particle swarm optimization and subsequently set as the initial values in the sequence quadratic programming to search for the exact convergent solution. The elliptical and near-circular mission orbital rendezvous for spacecraft with multiple specific-direction thrusts are simulated and optimized. Numerical examples verifying the proposed method are provided. The results facilitate easier realization of rapid spacecraft maneuvering under continuous thrust conditions.

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Nonlinear Optimal Control of Relative Rotational and Translational Motion of Spacecraft Rendezvous

Cited by 31 publications

References 24 publications

Automated Orbital Transfer and Hovering Control Using Artificial Potential

Automated Orbital Transfer and Hovering Control Using Artificial Potential

Finite-Time Relative Pose Tracking Control for Uncertain Spacecraft Rendezvous and Docking

Optimal control of rapid cooperative spacecraft rendezvous with multiple specific-direction thrusts

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