Attitude stabilization of a satellite by magnetic coils

American Control Conference, 1998. …, 1998

Abstmct: This study presents a method to control the attitude of spacecraft using only magnetorquers without the gravity gradient boom. The main challenge is that the control torque can only be generated perpendicular to the geomagnetic field. If the dynamic model is expressed in the ...

2011

The active magnetic attitude control technique is a promising attitude control option for small satellites operated in Low Earth Orbit (LEO). It is accomplished using sets of magnetic torquer that can generate a mechanical torque thus producing control actions when the torquers interact with the geomagnetic field. The magnetic attitude control structure can be developed based only on the magnetic torquers or in conjunction with other actuators. The purpose of this thesis is to develop and evaluate the options for the active magnetic attitude control system of low-cost small satellite missions. Three options of control algorithms have been developed for a gravity-gradient satellite and a momentum bias satellite. The first algorithm is structured for the gravity-gradient satellite employing three magnetic torquers onboard (Option A). The algorithm has been configured for controlling roll, pitch and yaw attitudes using a proportional-derivative (PD) controller. The second and the third...

Journal of Guidance, Control, and Dynamics, 2015

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.

2014

The active magnetic attitude control technique is a recognized attitude control option for small satellites operated in Low Earth Orbit (LEO). The purpose of this thesis is to control a nano-satellite that is operated in LEO so that it always pointing toward the Earth. Two options of control algorithms have been considered for a gravity-gradient satellite. The first control is a passive type, structured for the gravity-gradient satellite (Satellite A). It relies totally on the orbited body's mass distribution and gravitational field. The second control is an active type, structured for the gravity-gradient satellite employing three magnetic torquers onboard (Satellite B). The control is accomplished using a set of magnetic torquers that can generate a mechanical torque thus producing control actions when the torquers interact with the geomagnetic field. The algorithm used in Satellite B is configured for controlling roll, pitch and yaw attitudes using a proportional-derivative (...

Automatica, 1999

Interaction between control-current in coils and the geomagnetic xeld can be the means to stabilize a satellite about three axes. Nonlinear time-varying analysis shows how this new result is obtained.

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.

This work reproduces an active magnitude attitude control system that has been designed and simulated for a microsatellite onto a 3U CubeSat. The control is accomplished using sets of magnetic torquer that can generate a mechanical torque thus producing control actions when the torquers interact with the geomagnetic field. Algorithm used for the active magnetic attitude control technique is structured for the gravity-gradient satellite employing three magnetic torquers onboard. The algorithm is configured for controlling roll, pitch and yaw attitudes using a proportional-derivative (PD) controller. The satellite is operated in Low Earth Orbit (LEO) and is pointing to Earth. For simulation purpose, a simplified geomagnetic field is first modeled. Then mathematical model of a gravity gradient satellite is established. In orbit external disturbances is also considered. Subsequently attitude control algorithms for a gravity gradient satellite with respect to a simplified geomagnetic field models is developed and modeled using the MATLAB® SIMULINK®. Attitude performance of the 3U CubeSat shows good comparative results with previous work done for microsatellites which can provide us the guidance when designing the magnetic attitude control subsystem for nano-satellites.

Progress in Aerospace Sciences, 2019

Control algorithms for the active magnetic attitude control systems are covered in the survey. Three different situations in the magnetic system implementation are considered. First, angular velocity damping is covered. Second part is devoted to the combined operation of the active magnetic system with other actuators and with the help of some passive stabilization concepts. Magnetic control torque is restricted in its direction, as it cannot be implemented along the geomagnetic induction vector. This restriction may be lifted by enhancing the active magnetic attitude control with other actuators and concepts. This comes at the cost of restrictions on the available attitude modes of the satellites. Namely, passive gravity-gradient stabilization provides the nadir pointing; bias momentum satellites are restricted by the wheel axis pointing along the orbital normal; spin stabilized satellites acquire only one axis attitude. Finally, solely three-axis magnetic attitude control is considered. Different approaches to the control torque restriction problem are covered, with distinction between the local feedback laws and optimization methods. The survey does not cover passive magnetic control concepts and auxiliary role in the reaction wheels momentum unload. Comparison of the covered algorithms is provided to highlight the authors' opinion on the algorithms modern implementation and further research directions.

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.