Close proximity formation flying via linear quadratic tracking controller and artificial potential function

Palacios, Leonel; Ceriotti, Matteo; Radice, Gianmarco

doi:10.1016/j.asr.2015.09.005

Cited by 43 publications

(7 citation statements)

References 20 publications

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“…This has some similarities with the existing motion planning methods like artificial potential function-based and rapidly exploring random tree-based methods. 13,14 However, there are some differences between the PPC and motion planning methods. On one hand, the performance envelope is a time-dependent one, while the feasible space generated by the motion planning is dependent on the system state, which is often related to the two- or three-dimensional positions.…”

Section: Introductionmentioning

confidence: 99%

An overview of prescribed performance control and its application to spacecraft attitude system

Wei

Chen

Liu

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part I:

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High-quality control method is of great importance for the attitude determination and maneuvering of spacecraft in the on-orbit servicing technology. Prescribed performance control methodology, as a potential way, has gained considerable attention due to its quantitative description for the transient and steady-state control performance in recent years. Thus, this article constructs a survey for the prescribed performance control methodology along with the detailed analysis of the attitude control methods in the existing reported works. Then, the basic structure of prescribed performance control methodology is discussed in theory, and application to the attitude control of postcapture spacecraft works as an example to further explain the procedure of prescribed performance control methodology. Finally, with consideration of some vital aerospace applications, potential open issues of the prescribed performance control methodology are analyzed.

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Section: Introductionmentioning

confidence: 99%

An overview of prescribed performance control and its application to spacecraft attitude system

Wei

Chen

Liu

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part I:

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“…The convergence rate of the control algorithm for obstacles avoidance was improved. In Palacios et al (2015), an LQR/APF control law was developed and verified for satellite formation on elliptical orbit.…”

Section: Introductionmentioning

confidence: 99%

Suboptimal obstacles avoidance control of spacecraft rendezvous

Cao¹,

Xiao

2020

Transactions of the Institute of Measurement and Control

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Spacecraft on-orbital services and docking require their autonomous rendezvous control system to have obstacle avoidance capability. Motivated by this, a suboptimal velocity artificial potential function-based control scheme is presented. An ellipsoid model is applied to describe the outer envelopes of the service spacecraft and the obstacles via an eigenvalue algorithm. This has better description precision than the traditional methods. The potential sigmoid function is used to generate repulsive force to avoid obstacles collision. A velocity artificial potential function-based controller is finally developed to ensure that the relative speed of the service spacecraft is reduced to zero before reaching the outer envelops of obstacles. The shaping parameters of the attractive potential function are adaptively optimized. Numerical simulations are performed to demonstrate that the approach can achieve a safe and autonomous rendezvous with fuel cost saved.

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“…Flight safety is the major consideration in the approach. The keep-out zone that covers the outer surface of the target is always used for collision avoidance [10,11]. Most related studies adopted a sphere envelope to model target's keep-out zone [12,13] although this is unsuitable for the approach problem discussed in the study.…”

Section: Introductionmentioning

confidence: 99%

Model Predictive Control to Autonomously Approach a Failed Spacecraft

Wang

Zhang

2018

International Journal of Aerospace Engineering

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In this study, a model predictive control (MPC) method is developed for a servicer spacecraft autonomously approaching a tumbling failed spacecraft at an ultraclose range. Flight safety and collision avoidance are basic requirements during the approach. Two types of a failed spacecraft with complex configurations are considered, and a double-ellipsoid composite envelope strategy is designed to model their keep-out zones. Given the keep-out zone of the servicer, two expanded ellipsoids are subsequently introduced to determine the collision and sufficient conditions for collision avoidance are derived by using the form of concave constraint. The tumbling motion of the target is considered, and a CW-based translational dynamics and derived attitude dynamics of the target are formulated to predict the motion of the docking point and keep-out zone. The MPC is formulated to drive the servicer tracking the docking point with collision avoidance and handle constraints including control input saturation and relative velocity bound. Convexification of the collision avoidance constraint and sequential convex programming are adopted for the implementation of MPC. Scenarios on the servicer with different initial positions approaching the target with different angular velocities are simulated, and the simulation results indicate that the proposed MPC method is effective.

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Close proximity formation flying via linear quadratic tracking controller and artificial potential function

Cited by 43 publications

References 20 publications

An overview of prescribed performance control and its application to spacecraft attitude system

An overview of prescribed performance control and its application to spacecraft attitude system

Suboptimal obstacles avoidance control of spacecraft rendezvous

Model Predictive Control to Autonomously Approach a Failed Spacecraft

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