Optimizing the electrodynamical stabilization method for a man-made Earth satellite

Тихонов, А. А.; Spasic, D. T.; Antipov, K. A.; Sablina, M. V.

doi:10.1134/s0005117911090116

Cited by 21 publications

(7 citation statements)

References 1 publication

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“…Therefore, we can write the torque of these forces relative to the spacecraft's center of mass as follows (Griffith 1989) where ρ is the radius vector of the screen's element dS relative to the spacecraft's center of mass and V is the velocity of the element dS relative to the geomagnetic field. As in Tikhonov et. al.…”

Section: Torque Due To Lorentz Forcementioning

confidence: 69%

Equilibria of a charged artificial satellite subject to gravitational and Lorentz torques

Abdel‐Aziz¹,

Shoaib²

2014

Res. Astron. Astrophys.

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Attitude Dynamics of a rigid artificial satellite subject to gravity gradient and Lorentz torques in a circular orbit is considered. Lorentz torque is developed on the basis of the electrodynamic effects of the Lorentz force acting on the charged satellite's surface. We assume that the satellite is moving in Low Earth Orbit (LEO) in the geomagnetic field which is considered as a dipole model. Our model of the torque due to the Lorentz force is developed for a general shape of artificial satellite, and the nonlinear differential equations of Euler are used to describe its attitude orientation. All equilibrium positions are determined and their existence conditions are obtained. The numerical results show that the charge q and radius ρ 0 of the charged center of satellite provide a certain type of semi passive control for the attitude of satellite. The technique for such kind of control would be to increase or decrease the electrostatic radiation screening of the satellite. The results obtained confirm that the change in charge can effect the magnitude of the Lorentz torque, which may affect the satellite's control. Moreover, the relation between the magnitude of the Lorentz torque and inclination of the orbits is investigated.

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Section: Torque Due To Lorentz Forcementioning

confidence: 69%

Equilibria of a charged artificial satellite subject to gravitational and Lorentz torques

Abdel‐Aziz¹,

Shoaib²

2014

Res. Astron. Astrophys.

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“…In the problem of satellite electrodynamic attitude stabilization [1], [2], [4], [6] it is required to generate the control torques providing the existence and the asymptotic stability of the satellite position in the König frame such that the equations (1) hold, and, moreover, the satellite angular velocity with respect to the König frame is equal to zero:…”

Section: Coordinate Systems and Programmed Motionmentioning

confidence: 99%

“…Later the concept of the electrodynamic attitude control system was improved in [2] and further used for solving the problems of three-axis stabilization of a satellite in the orbital coordinate system (see [3] and papers cited therein), monoaxial stabilization of a satellite in the orbital coordinate system [4], stabilization of a satellite in biaxial spin mode [5], three-axis stabilization of a satellite in the König coordinate system [6].…”

mentioning

confidence: 99%

On electrodynamical compensation of a torque disturbing satellite orientation

Тихонов

2015

2015 International Conference "Stability and Control Processes" in Memory of V.I. Zubov (SCP)

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“…A parametric approach for damping the AES oscillations in the orbital frame was proposed in [7] and developed in [8], where consideration was given to AES attitude stabilization in the direct equilibrium position in the orbital frame. The mathematical background of this approach relies on the differential equations of the linear approximation.…”

Section: Introductionmentioning

confidence: 99%

Monoaxial Electrodynamic Stabilization of an Artificial Earth Satellite in the Orbital Coordinate System via Control With Distributed Delay

Aleksandrov

Тихонов

2021

IEEE Access

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An artificial Earth satellite (AES) with three different principal central moments of inertia is under consideration. The AES moves along a Keplerian circular equatorial near-Earth orbit. The AES is equipped with electrodynamic attitude control system that simultaneously generates Lorentz and magnetic control torques. The possibility of using an electrodynamic attitude control system for monoaxial attitude stabilization of AES in the orbital coordinate system is analyzed. The development of the concept of electrodynamic attitude control, including the use of a restoring torque with a distributed delay (integral term), is proposed. The conditions are found under which the electromagnetic attitude control system with distributed delay solves the problem of AES monoaxial stabilization in the presence of the disturbing gravitational torque. In a nonlinear formulation, sufficient conditions for the asymptotic stability of the AES equilibrium position are obtained. A theorem on the asymptotic stability of the AES programmed attitude motion is proved. The effectiveness of the constructed attitude control with a distributed delay is confirmed by numerical modeling.

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Optimizing the electrodynamical stabilization method for a man-made Earth satellite

Cited by 21 publications

References 1 publication

Equilibria of a charged artificial satellite subject to gravitational and Lorentz torques

Equilibria of a charged artificial satellite subject to gravitational and Lorentz torques

On electrodynamical compensation of a torque disturbing satellite orientation

Monoaxial Electrodynamic Stabilization of an Artificial Earth Satellite in the Orbital Coordinate System via Control With Distributed Delay

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