A new variant of the B-dot control for spacecraft magnetic detumbling

Desouky, Mohammed A. A.; Abdelkhalik, Ossama

doi:10.1016/j.actaastro.2020.02.030

Cited by 10 publications

(6 citation statements)

References 23 publications

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“…As illustrated here, the main feature is that the B-dot controller does not need to measure the satellite's angular rates [8]. However, B-dot controller might lead to a suboptimal torque vector, especially in small angular velocities, as the generated dipole moment might not be orthogonal to the geomagnetic field [8]. Therefore, we augment the B-dot controller with a proportional integral derivative (PID) controller that is expressed as…”

Section: Detumbling Control Approachesmentioning

confidence: 99%

Designing attitude controller for nano/pico satellites at detumbling mode using magnetic sensor and actuator

Mohsen,

Ibrahim,

Kamel

et al. 2023

J. Phys.: Conf. Ser.

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Recently, satellites have been becoming economically attractive in many applications using the advanced technologies and payloads. Practically, the launching process of any satellite passes through some stages under different conditions. For example, the satellite might be uncontrollable in the detumbling mode. Thus, it might be a risk of accident with space debris and the satellite can not complete the specified mission. So it is necessary to design an attitude controller to stabilize the satellite after the separation phase, i.e., in the detumbling mode. In this paper, we design an attitude controller to bring the satellite to the desired condition with a minimum angular momentum. The magnetorquers and magnometers are an effective solution for the satellite in low-Earth orbits because they are smaller and lighter than others. Simulation studies are presented to validate the proposed attitude control approaches.

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Section: Detumbling Control Approachesmentioning

confidence: 99%

Designing attitude controller for nano/pico satellites at detumbling mode using magnetic sensor and actuator

Mohsen,

Ibrahim,

Kamel

et al. 2023

J. Phys.: Conf. Ser.

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“…After the surface parameter matrix in the current iteration is calculated, the control torque is also calculated according to (9). It is then used to find the control dipole moment as a projection on the plane perpendicular to the geomagnetic induction vector m = B × M/|B| 2 . The same procedure is used during the optimization process to find the dipole moment in condition 3.…”

Section: New Sliding Surface Design (Sc Construction)mentioning

confidence: 99%

“…Magnetic control systems excel at certain specific tasks. Angular velocity damping can be effectively performed after a satellite's separation from the launch vehicle [1,2]. Likewise, it is used for the unloading of the reaction wheels' angular momentum.…”

Section: Introductionmentioning

confidence: 99%

Comparison of Feedback Three-Axis Magnetic Attitude Control Strategies

Roldugin,

Okhitina,

Monakhova

et al. 2023

Aerospace

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In this article, five feedback magnetic attitude control algorithms are compared in terms of stabilization accuracy and implementation problems. The control strategies are classic Lyapunov control with scalar gain; the same control strategy with matrix gain and a specific gain-tuning procedure; sliding control with a variable surface; a linear quadratic regulator constructed for a special time-invariant system of a higher degree than the initial time-varying system; and a special controllable trajectory developed using particle swarm optimization. A new sliding surface construction method is proposed in this paper. Surface parameters were changed in every control iteration to ensure that the required control torque component along the geomagnetic induction vector was small. The advantages and drawbacks of the considered methods and their applicability for different target attitudes are discussed.

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“…As pointed out in [35], this fact is accounted for with the inclusion of a low pass filter, easily integrable into a CubeSat. Robustness of the B-dot controller in the presence of noise is also studied in [36], [37], and [38].…”

Section: Spin-stabilization Controllermentioning

confidence: 99%

Gyroless Spin-Stabilization Controller and Deorbiting Algorithm for CubeSats

Morales

Kim

Richardson

2020

Int. J. Aeronaut. Space Sci.

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CubeSats are becoming increasingly popular in the scientific community. While they provide a whole new range of opportunities for space exploration, they also come with their own challenges. One of the main concerns is the negative impact which they can have in the space debris problem. Commonly lacking from attitude determination and propulsion capabilities, it has been difficult to provide CubeSats with means for active deorbiting. While electric propulsion technology has been emerging for its application in CubeSats, little or no literature is available on methods to enable it to be used for deorbiting purposes, especially within the tight constraints faced by these nanosatellites. We present a new and simple algorithm for CubeSat deorbiting, which proposes the use of novel electric propulsion technology with minimum sensing and actuation capabilities. The algorithm is divided into two stages: a spin-stabilization control; and a deorbiting-phase detection. The spin-stabilization control is inspired by the B-dot controller. It does not require gyroscopes, but only requires magnetometers and magnetorquers as sensors and actuators, respectively. The deorbiting-phase detection is activated once the satellite is spin-stabilized. The algorithm can be easily implementable as it does not require any attitude information other than the orbital information, e.g., from the Global Positioning System receiver, which could be easily installed in CubeSats. The effectiveness of each part of the algorithms is validated through numerical simulations. The proposed algorithms outperform the existing approaches such as deorbiting sails, inflatable structures, and electrodynamic tethers in terms of deorbiting times. Stability and robustness analysis are also provided. The proposed algorithm is ready to be implemented with minimal effort and provides a robust solution to the space junk mitigation efforts.

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A new variant of the B-dot control for spacecraft magnetic detumbling

Cited by 10 publications

References 23 publications

Designing attitude controller for nano/pico satellites at detumbling mode using magnetic sensor and actuator

Designing attitude controller for nano/pico satellites at detumbling mode using magnetic sensor and actuator

Comparison of Feedback Three-Axis Magnetic Attitude Control Strategies

Gyroless Spin-Stabilization Controller and Deorbiting Algorithm for CubeSats

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