Attitude Control of Spinning Satellite Subject to Actuators Restriction Using Eigen Structure Assignment

Bolandi, Hossein; Bayat, Farhad; Nasirian, Mehrzad

doi:10.1109/isscaa.2006.1627503

Cited by 4 publications

(4 citation statements)

References 3 publications

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“…Theorem 1. Assume the satellite's equations of attitude motions as presented in (2)- (4). Provided that the satellite angular velocities are kept on the fractional integral sliding surface S = 0 defined in (9) and the sliding surface is an invariant set (i.e.…”

Section: Controller Architecturementioning

confidence: 99%

“…Different controller architectures based on the different torque sources have been proposed in the literatures. For example reaction and momentum wheel-based [2][3][4], thruster-based [5,6] and magnetorquers-based approaches [7][8][9] have been proposed to solve satellite attitude control prob-Manuscript received October 22, 2017; revised April 8, 2018; accepted May 19, 2018.…”

Section: Introductionmentioning

confidence: 99%

“…Different controller architectures based on the different torque sources have been proposed in the literatures. For example reaction and momentum wheel‐based , thruster‐based and magnetorquers‐based approaches have been proposed to solve satellite attitude control problem. Amongst different actuators, the reaction wheels are acknowledged for their proven performance, relative simplicity, fast response and high pointing control accuracy.…”

Section: Introductionmentioning

confidence: 99%

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Two‐Layer Terminal Sliding Mode Attitude Control of Satellites Equipped with Reaction Wheels

Bayat

Javaheri

2018

Asian Journal of Control

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This paper addresses the global stability and robust attitude tracking problem of a near polar orbit satellite subject to unknown disturbances and uncertainties. It is assumed that the satellite is fully actuated by a set of reaction wheels (RW) as control actuators because of their relative simplicity, versatility and high accuracy. The terminal sliding mode control (TSMC) approach is utilized in a two-level architecture to achieve control objectives. In the lower layer a detumbling-like controller is designed which guarantees the finite-time detumbling and tracking of the desired angular velocities and based on this result a robust attitude tracking controller is designed in the upper layer to achieve 3-axis attitude tracking in the presence of unknown disturbances and bounded uncertainties. Robust stability and tracking properties of designed controllers are proved using the Lyapunov theory. Finally, a set of numerical simulation results are provided to illustrate the effectiveness and performance of the proposed control method.

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Section: Controller Architecturementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Two‐Layer Terminal Sliding Mode Attitude Control of Satellites Equipped with Reaction Wheels

Bayat

Javaheri

2018

Asian Journal of Control

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“…Different control strategies have been proposed to avoid these singularities or, at least, handle them efficiently (Kennel, 1970;Li and Bainum, 1990;Krishnan and Vadali, 1996;Kurokawa, 1997 A few researchers have suggested using double-gimbal CMGs to avoid singularities (Wie, 1998;Ahmed and Bernstein, 2002;Bolandi et al, 2006), a solution that is more costly and complex for the dynamical modeling view point (Wie, 1998). McMahon and Schaub (2010), Richie and Lappas (2007), and Jin and Hwang (2011) have designed variable-speed control moment gyroscopes to produce the exact effective torque required at the cost of increasing the difficulty of dynamical modelling and controller design.…”

Section: Control Moment Gyrosmentioning

confidence: 99%

Attitude Dynamics and Control of Satellites With Fluid Ring Actuators

Nobari

Misra

2012

Journal of Guidance, Control, and Dynamics

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Successful mission of a satellite depends on maintaining a fixed orientation with respect to the Earth. However, the attitude angles of a satellite can be perturbed because of various natural disturbance sources, such as the Earth's gravity gradient, solar radiation pressure, and the Earth's magnetic field. Modeling the attitude dynamics and developing a controller to stabilize the attitude motion are quite important steps in the design of satellites. Although several actuators exist to control the attitude motion, a novel type considered in the thesis, shows promise of producing a high torque to mass ratio. This potential justifies the in-depth study reported. The novel actuator in question consists of a ring containing fluid, whose flow is regulated by a pump. The control torque is produced due to the variation of the angular velocity of the fluid.In this thesis, first, a redundant actuator system composed of four fluid rings in a pyramidal configuration is studied. The dynamical model of the system is developed for a satellite travelling either in a circular or an elliptical orbit. The dynamical analysis of this system leads to an underdetermined system of nonlinear differential equations, whose solution without considering the control input (the torque produced by the pump pressure) shows that the fluid rings can damp out the attitude disturbances of a satellite in a circular orbit and the roll-yaw disturbances in an elliptical orbit. However, this passive damping effect is fairly slow; an active controller is hence designed in the next step. The effect of the failure of one fluid ring on the performance of the attitude control subsystem (ACS) of a satellite is also studied. It is observed that even in the case of failure of one fluid ring, the satellite can be stabilized by slight modification of the active controller.Later, a sliding mode controller is designed to cope with the uncertainties existing in the fluid model and in other parameters of the system. Although the results achieved are quite satisfactory, the chattering that exists in the steady response of the system is not i desirable; hence a switching controller consisting of a sliding mode and a PID control law is designed to eliminate this chattering effect.Next, the theoretical results obtained are validated by conducting several experiments. To this end, first, a setup with one fluid ring is designed and built. Here, a single fluid ring is attached to a disk so as to verify the controllability of the system with a fluid ring and also the validity of the theoretical model. Although the experimental results confirm the theory developed in this thesis, the large torque-to-mass ratio expected is revealed to be only possible at the cost of a quite high input voltage to the pumps regulating the flow. Therefore, two novel applications of fluid rings are proposed: as an actuator for spin stabilized satellites, or as an auxiliary actuator in satellites with magnetic torquers.Using fluid rings in spin stabilized satellites is proposed in the the...

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