Formation Control of Satellites in Low Earth Orbit by Using Moving Masses

Abstract This paper investigates a formation control technique based on the use of moving masses. First, the mechanism of the moving mass control is conducted to reveal the relation between the attitude and the offsets of moving masses. Then, to achieve the desired formation control, the aerodynamic force generated by the change of attitudes is used as the control input to implement the orbit control. The moving masses and magnetic torquers constitute a combined actuator to drive the satellite attitude. To deal with the offset saturation of moving masses, an adaptive controller is investigated. Finally, a simulation on two satellites formation is provided, demonstrating the feasibility of the proposed method.

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Model predictive orbit control of a Low Earth Orbit satellite using Gauss’s variational equations

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/0954410013516252 ◽

2013 ◽

Vol 228 (13) ◽

pp. 2385-2398 ◽

Cited By ~ 4

Author(s):

MM Tavakoli ◽

N Assadian

Keyword(s):

Model Predictive Control ◽

Control Problem ◽

Predictive Control ◽

Optimization Problems ◽

Low Earth Orbit ◽

Control Technique ◽

Earth Orbit ◽

Reference Orbit ◽

Variational Equations ◽

Orbit Control

In this paper, an autonomous orbit control of a satellite in Low Earth Orbit is investigated using model predictive control. The absolute orbit control problem is transformed to a relative orbit control problem in which the desired states of the reference orbit are the orbital elements of a virtual satellite which is not affected by undesirable perturbations. The relative motion is modeled by Gauss’s variational equations including J2 and drag perturbations which are the dominant perturbations in Low Earth Orbit. The advantage of using Gauss’s variational equations over the Cartesian formulations is that not only the linearization errors are much smaller, but also each orbital element can be controlled independently. Model predictive control finds the finite horizon optimal firing times of the satellite thrusters. The problem of orbit control has been cast as a linear programming which is a subset of convex optimization problems. As a result, model predictive control can maintain and control orbits of Low Earth Orbit satellites in optimal way, and this modern control technique can be an alternative for traditional analytical-based orbit control methods. Also, a comparison between model predictive control and linear quadratic regulator orbit control showed the superiority of MPC in fuel consumption.

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Comparison of low-earth-orbit satellite attitude controllers submitted to controllability constraints

Journal of Guidance Control and Dynamics ◽

10.2514/3.21269 ◽

1994 ◽

Vol 17 (4) ◽

pp. 795-804 ◽

Cited By ~ 40

Author(s):

Willem H. Steyn

Keyword(s):

Low Earth Orbit ◽

Earth Orbit ◽

Satellite Attitude ◽

Orbit Satellite ◽

Low Earth Orbit Satellite

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A Distributed Formation Control Scheme with Obstacle Avoidance for Multiagent Systems

Mathematical Problems in Engineering ◽

10.1155/2019/3252303 ◽

2019 ◽

Vol 2019 ◽

pp. 1-16 ◽

Cited By ~ 1

Author(s):

Xiaowu Yang ◽

Xiaoping Fan

Keyword(s):

Obstacle Avoidance ◽

Multiagent Systems ◽

Formation Control ◽

Adaptive Controller ◽

Control Input ◽

Control Laws ◽

Integral Term ◽

Control Scheme ◽

The Stability ◽

Avoidance Problem

This study considers the problem of formation control for second-order multiagent systems. We propose a distributed nonlinear formation controller where the control input of each follower can be expressed as a product of a nonlinear term that relies on the distance errors under the leader–follower structure. In the leader–follower structure, a small number of agents are assumed to be the leaders, and they are responsible for steering a group of agents to the specific destination, while the rest of the agents are called followers. The stability of the proposed control laws is demonstrated by utilizing the Lyapunov function candidate. To solve the obstacle avoidance problem, the artificial potential approach is employed, and the agents can avoid each possible obstacle successfully without getting stuck in any local minimum point. The control problem of multiagent systems in the presence of unknown constant disturbances is also considered. To attenuate such disturbances, the integral term is introduced, and the static error is eliminated through the proposed PI controller, which makes the system stable; the adaptive controller is designed to reduce the effect of time-varying disturbances. Finally, numerical simulation results are presented to support the obtained theoretical results.

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Orbit Control Manoeuvre Strategy for Post-Mission De-Orbiting of a Low-Earth-Orbit Satellite

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.781.495 ◽

2015 ◽

Vol 781 ◽

pp. 495-499

Author(s):

Manop Aorpimai ◽

Pornthep Navakitkanok

Keyword(s):

Space Debris ◽

Electronic Devices ◽

Low Earth Orbit ◽

Propulsion System ◽

Passive State ◽

Earth Orbit ◽

Orbit Control ◽

Practical Strategy ◽

Chemical Propulsion ◽

Debris Mitigation

In this paper, we investigate a practical strategy for de-orbiting the retired satellite in low-Earth orbit for the space debris mitigation. The only means available onboard the spacecraft for performing the task is the chemical propulsion system with limited propellant provided. It is proposed to reduce the orbital perigee to reach a certain level where the atmospheric drag can play its role in lowering the satellite altitude, and eventually bringing it to re-entry within a defined period of time. The required delta-V is divided into a series under the constraints on the propulsion system and orbit control manoeuvre implementation. The results from the flight dynamics simulator suggest that a fraction of the remaining propellant available on the demonstrating mission, the Thaichote satellite, would be sufficient to accomplish the task. The strategy implementation will be another vital step in transferring the spacecraft to a safe passive state, where the fuel tank is empty, all batteries are discharged and all electronic devices are deactivated.

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