Single axis stabilization of a fast rotating satellite in the orbital frame using magnetorquers and a rotor (original) (raw)
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Mathematics, 2023
A spin stabilized satellite reorientation maneuver in the inertial space is investigated. Spin axis pointing and nutation damping magnetic attitude control algorithms are utilized. Evolutionary equations for the oscillations of a symmetrical satellite near the required position are derived. The exact solution for the wobble amplitude is obtained for the averaged equations of motion. Spin axis attitude angles relative to the required direction are analyzed. Optimal control gain is found for the reorientation maneuver. Theoretical results are verified with numerical simulation.
Magnetic attitude control and periodic motion for the in-orbit rotation of a dual-spin satellite
Acta Astronautica, 2021
Angular motion of a dual-spin satellite with a pitch flywheel with constant rotation rate is considered. While the satellite is equipped with magnetorquers, damping control ensures the stabilization in the orbital axes. Another type of control is proposed to rotate the satellite in the orbital plane in arbitrary direction. The resulting satellite motion is analyzed. Semi-analytic approach is developed to find the amplitudes of the periodic oscillations of the satellite in the vicinity of the required attitude. Planar motion on the polar orbit and small oscillations on the circumpolar orbit are covered. Results are verified with the numerical simulation.
Passive magnetic stabilization of the rotational motion of the satellite in its inclined orbit
Applied Mathematical Sciences, 2015
The problem of perturbed rotational motion of the satellite is one of the most interesting, important and, at the same time, mathematically complex problems of celestial mechanics and space flight dynamics. Among existing stabilization systems, a passive magnetic stabilization systems have a special place, since they have an exceptional reliability and are easy to manufacture. In this paper the problem of passive magnetic stabilization of the rotational motion of the satellite is studied. It is assumed that passive magnetic system provides its orientation along the vector of the geomagnetic field strength H. The geomagnetic field is simulated by the direct dipole model, considering different orbits of inclination. In the considered model an effect of the gravitational torque is taken into account. Results of computational experiments are presented.
Design and testing of magnetic controllers for Satellite stabilization
Acta Astronautica, 2005
A study was carried out of attitude control algorithms that are able to provide 3-axis stabilization of a satellite equipped with a magnetometer as the only sensor and magnetotorquers as the only actuators. Two different solutions to the problem were developed, namely Linear Quadratic Regulator and No Wheel controllers. Their aptitude to achieve the required performance was confirmed by multiple numerical simulations under different initial conditions and various scenarios. The new algorithms were tested onboard the Israeli Gurwin-TechSAT micro-satellite, nominally momentum-biased, stabilized within 2º-2.5º precision by the proportion-plus-derivative magnetic controller. In the flight tests of the new controllers, some valuable results were obtained, such as revealing the possibility to effectively maintain the satellite 3-axis stabilization even with a very small momentum bias, and the implementation and efficient performance of the properly modified extended and linear Kalman filters in the onboard computer.
Aerospace
We consider the problem of attitude stabilization for a low Earth orbit satellite having only electromagnetic actuation. Such a satellite is not fully actuated, as the control torque is the cross-product of magnetic moment due to magnetorquers and the geomagnetic field. The aim of this work is to study whether oscillating controls can be designed such that a satellite actuated via magnetorquers alone can achieve full three-axis control irrespective of the position of the satellite. To this end, we propose considering oscillating feedback controls which generate the motion of the closed-loop system in the direction of appropriate Lie brackets. Simulation studies show that the proposed control scheme is able to stabilize the considered system.
Spin-stabilized satellite magnetic attitude control scheme without initial detumbling
Acta Astronautica, 2014
The angular motion of an axisymmetrical satellite equipped with an active magnetic attitude control system is considered. The dynamics of the satellite are analytically studied on the whole control loop. The control loop is as follows: preliminary reorientation along with nutation damping, spinning about the axis of symmetry, then precise reorientation of the axis of symmetry in inertial space. Reorientation starts right after separation from the launch vehicle. Active magnetic attitude control system time-response with respect to its parameters is analyzed. It is proven that low-inclined orbit forces low control system time-response. Comparison with the common control scheme shows the time-response gain. Numerical analysis of the disturbances effect is carried out and good pointing accuracy is proved.
Comparison of two magnetic damping laws for the attitude acquisition of a dual spin satellite
International Journal of Space Science and Engineering, 2019
Dual spin satellite motion in the attitude acquisition phase is considered. Starting from the arbitrary rotation state, the satellite should end up with its angular momentum aligned with the orbit normal. The satellite is equipped with magnetorquers that provide the angular velocity damping. Two control strategies are compared, that is the simple exponential damping and "weighted" damping arising from the classical sliding control implementation. The time response of the control system depending on the satellite inertia moments is analyzed. Simple damping is proven to provide better results for the low control authority even for the significantly elongated satellite. This result is proved with the analytical solution for the characteristic exponents approximations. Weighted damping is shown to provide better results for significant control authority through numerical simulation.
A heuristic design method for attitude stabilization of magnetic actuated satellites
Acta Astronautica, 2009
In this paper a heuristic design strategy for stabilizing the satellite attitude has been proposed. It is assumed that the satellite is actuated by a set of mutually perpendicular magnetic coils. Using well-known Lyapunov direct stability method it is shown that the proposed controller causes to a global asymptotic stable system for all near polar orbits. The design procedure is based on analyzing of the conceptual effects of magnetic coils on the satellite attitude motion. Considering these effects lead to some intuitive results which determine the global stabilizing control law. The performance and robustness of the designed controller against actuators saturation and quantization error have been verified using a real-time-hardware-software in-loop (RTHSIL) simulation results. These results show that the global stability can be achieved although some disturbances and restrictions exist. This stabilizing controller can be simply combined with a linear explicit model predictive controller (EMPC) to achieve a full three-axis control law.
Choosing control parameters for three axis magnetic stabilization in orbital frame
Acta Astronautica, 2015
Three-axis magnetic control in orbital reference frame is considered. Magnetorquers are the only actuators and gravitational torque is the only disturbance source. Full attitude knowledge is assumed. Control is constructed on the basis of PD-controller. Stability is analyzed using Floquet theory. Optimal in terms of degree of stability control parameters are found using this approach. These parameters may be further adjusted using numerical simulation. Results for three typical satellites are provided. Numerical example with Kalman filter implementation and additional disturbance sources is provided.