NanoSats/CubeSats ADCS survey

Xia, Xiwang; Sun, Guowen; Zhang, Keke; Wu, Shufan; Wu, Tian; Lei, Xia; Liu, Shanwu

doi:10.1109/ccdc.2017.7979410

Cited by 32 publications

(11 citation statements)

References 4 publications

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“…This shift offers a more immediate and visually intuitive interpretation of the results, simplifying the process of verifying compliance with the stipulated requirements. Figures 10,11,12,and 13 show these indicators with a focus on the steady-state region. The diagrams also show the boundaries within which the requirement is fulfilled.…”

Section: Simulation Resultsmentioning

confidence: 99%

“…The active determination and control system of a CubeSat is a well‐established technology available on the market 10 . According to the CubeSats ADCS survey statistics in Reference 11, almost every CubeSat employs magnetometers, sun sensors, and gyroscopes for attitude determination. A low percentage of CubeSats adopt passive control techniques, while most use reaction wheels‐based active attitude control strategies for precise pointing.…”

Section: Introductionmentioning

confidence: 99%

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Novel extended Kalman filter + H∞$$ {\mathbf{H}}_{\infty } $$ optimal output feedback control configuration for small satellites with high pointing stability requirements

Pecorilla,

Stesina

2023

Intl J Robust & Nonlinear

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SummaryOne of the most challenging subsystems for the CubeSats is the attitude determination and control system (ADCS) because it involves hardware and software integration, advanced strategies and algorithms to determine and control the attitude that impacts on space maneuvering and well working of a large set of payload (e.g., the optical payload). Although ADCS is largely studied, it still requires further investigations and analysis in order to achieve high‐performance and a reduced efforts. This paper presents an effective and reliable solution for the ADCS of CubeSats involved in Earth observation missions. The solution is based on an innovative framework that leverages the strengths of two distinct methodologies—H‐infinity optimal output feedback control and the extended Kalman filter (EKF)‐to significantly enhance the pointing stability of satellite systems. While H‐infinity optimal output feedback control is traditionally associated with partial state knowledge, we intentionally extend its application to scenarios with complete state information. The study includes a comparative performance analysis involving three algorithm configurations: the classic combination of EKF and model predictive control (MPC), the utilization of H‐infinity optimal output feedback control without EKF, and our proposed integrated approach. Performance evaluations are based on extrinsic indicators, demonstrating the advantages of our method in terms of pointing stability and overall control system performance. This research underscore the significance of combining innovative thinking with well‐established methodologies, unlocking new possibilities for stability enhancement in a range of engineering applications.

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Section: Simulation Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Novel extended Kalman filter + H∞$$ {\mathbf{H}}_{\infty } $$ optimal output feedback control configuration for small satellites with high pointing stability requirements

Pecorilla,

Stesina

2023

Intl J Robust & Nonlinear

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“…Due to the above-mentioned difficulties, even today, many cubesats continue to opt for passive control. About 23% of the nanosats/cubesats launched in the last years have adopted passive attitude control strategies [18]. Among the missions that use active controls, the option of using integrated ADCS units is expanding (about 50% of the missions analyzed in Ref.…”

Section: Introductionmentioning

confidence: 99%

Magnetic control without attitude determination for spinning spacecraft

Cubas

Ruiter

2020

Acta Astronautica

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“…One of the main challenges to use thrusters for deorbiting purposes, is that CubeSats often lack attitude determination and control capabilities [23]. In such cases, an alternative method is required to ensure that the thrusters are pointed in such a way that the thrust vector opposes in some degree to the velocity vector, causing the loss of orbital energy, eventually deorbiting the spacecraft.…”

Section: Introductionmentioning

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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NanoSats/CubeSats ADCS survey

Cited by 32 publications

References 4 publications

Novel extended Kalman filter + H∞$$ {\mathbf{H}}_{\infty } $$ optimal output feedback control configuration for small satellites with high pointing stability requirements

Novel extended Kalman filter + H∞$$ {\mathbf{H}}_{\infty } $$ optimal output feedback control configuration for small satellites with high pointing stability requirements

Magnetic control without attitude determination for spinning spacecraft

Gyroless Spin-Stabilization Controller and Deorbiting Algorithm for CubeSats

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