Relevant bibliographies by topics / Magnetorquer

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Book chapters
  4. Conference papers

Academic literature on the topic 'Magnetorquer'

Author: Grafiati
Published: 4 June 2021
Last updated: 20 February 2023

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Journal articles on the topic "Magnetorquer"

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Bai, Bo, Jun Zhou, and Shengyun Wang. "Design of High-Performance Magnetorquer with Air Core for CubeSat." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 36, no. 1 (February 2018): 1–6. http://dx.doi.org/10.1051/jnwpu/20183610001.

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To solve the problem that how to design a big magnetic moment, small size, light weight, low power consumption magnetorquer with air core under the constraint of limited volume and power in CubSate, multiobjective optimization design method is used. Firstly, based on the structure of the square support with multiple layer of the enameled wire wrapped, the magnetic moment model, power consumption model and mass model are deduced from square support size, enameled wire diameter and turn number, respectively. Secondly, according to the model of magnetic moment and power consumption, the multi-objective optimization design of magnetorquer with genetic algorithm (GA) is used under the constraint of limited mass and volume. Thirdly, based on the relation between the magnetic moment and the magnetic induction intensity, the measurement method of the magnetic moment is designed. Finally, the designed parameter is implemented. The test result showed that the designed magnetorquer has the qualities of high linearity, low remanence, and it well met the requirements of CubeSat standard. The designed magnetorquer successfully applied in several CubeSats indicates the reliability of this design scheme.
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Si, Juntian, Yang Gao, and Abadi Chanik. "Slew Control of Prolate Spinners Using Single Magnetorquer." Journal of Guidance, Control, and Dynamics 39, no. 3 (March 2016): 719–27. http://dx.doi.org/10.2514/1.g001035.

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MIYATA, Kikuko, Tomohiro NARUMI, and Jozef C. van der HA. "Comparison of Different Magnetorquer Control Laws for QSAT." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7, ists26 (2009): Pd_43—Pd_48. http://dx.doi.org/10.2322/tstj.7.pd_43.

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Kuiper, Hans, and Dennis Dolkens. "A cutting edge 6U CubeSat ADCS design for Earth observation with sub-meter spatial resolution at 230–380 km altitude." CEAS Space Journal 12, no. 4 (June 18, 2020): 613–21. http://dx.doi.org/10.1007/s12567-020-00323-7.

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Abstract A 6U CubeSat for Earth observation in 230–350 km orbits with sub-meter resolution is presented. The proposed Stable and Highly Accurate Pointing Earth-Imager (SHAPE) system’s attitude determination and control system (ADCS) is composed of a single momentum bias wheel with magnetic bearings at rotational speeds of 6000–7000 rpm and refined magnetorquers. Reaction wheels as instability source are absent. The ADCS stabilizes the spacecraft attitude by counteracting the torques from external disturbances in the thermosphere down to < 1° pointing accuracy and < 0.1° instability. The momentum wheel was sized to an angular momentum of 1 Nms based on the worst-case atmospheric density of the next solar cycle. The 0.5 Am2 magnetorquer dipole moment provides with low power consumption, mass and cost, high reliability and sufficient torque. The ADCS initialisation study revealed three stable start-up modes, while the all-spun state is achieved using a set of thrusters. De-tumbling analysis show that the magnetorquers reduce the tumbling rates with magnitudes of up to 35°/s to mean motion values in less than an orbit using a static gain B-dot controller. A 3U camera design capable of sub-meter spatial resolution at 230 km altitude is presented which complies with the SHAPE spacecraft system design. The instrument has a single deployable primary mirror enabled by a deployment hinge design with hysteresis < 0.5 μ. This payload combined with air-breathing electric propulsion technology at 230 km nominal altitude boosts the SHAPE system Earth observation potential down to sub-meter spatial resolution and enables tuning of the mission lifetime by orbit keeping.
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Hou, Xu Guang, Jian Yan, Jin Jin, and Shun Liang Mei. "Magnetorquer Based Vertical Damping Method for Microsatellite Attitude Control." Applied Mechanics and Materials 263-266 (December 2012): 584–87. http://dx.doi.org/10.4028/www.scientific.net/amm.263-266.584.

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Aiming at a three-axis stabilized microsatellite, a novel attitude control method, called magnetorquer based vertical damping, is proposed to avoid the occurrence of the worst situation that the non-solar-battery-plane spins towards the sun. DSP based simulation results based on DSP show that the vertical damping method outperforms the simple damping method when no orbit information is available, simultaneously the whole attitude control scheme is simple and effective. The proposed solution guarantees a stable power supply from the electrical source even under the extreme situation, which improves the reliability of the whole microsatellite system.
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Ali, Anwar, Shoaib Ahmed Khan, M. Usman Khan, Haider Ali, M. Rizwan Mughal, and Jaan Praks. "Design of Modular Power Management and Attitude Control Subsystems for a Microsatellite." International Journal of Aerospace Engineering 2018 (December 17, 2018): 1–13. http://dx.doi.org/10.1155/2018/2515036.

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The Electric Power System (EPS) and attitude control system (ACS) are the essential components of any satellite. EPS and ACS efficiency and compactness are substantial for the proper operation and performance of the satellite’s entire mission life. So, realizing the significance of EPS and ACS subsystems for any satellite, they have been assimilated and developed in modular forms focusing on efficiency and compactness. The EPS is comprised of three modules called the solar panel module (SPM), power conditioning module (PCM), and power distribution module (PDM) while the ACS has an embedded magnetorquer coil. For compactness and miniaturization purposes, the magnetorquer coil is embedded inside the SPM. The components used are commercial off-the-shelf (COTS) components emphasizing on their power efficiency, small dimensions, and weight. Latch-up protection systems have been designed and analyzed for CMOS-based COTS components, in order to make them suitable for space radioactive environment. The main design features are modularity, redundancy, power efficiency, and to avoid single component failure. The modular development of the EPS and ACS helps to reuse them for future missions, and as a result, the overall budget, development, and testing time and cost are reduced. A specific satellite mission can be achieved by reassembling the required subsystems.
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Utama, S., P. R. Hakim, and M. Mukhayadi. "Quarter orbit maneuver using magnetorquer to maintain spacecraft angular momentum." IOP Conference Series: Earth and Environmental Science 284 (May 31, 2019): 012046. http://dx.doi.org/10.1088/1755-1315/284/1/012046.

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Kondo, Kota, Ilya Kolmanovsky, Yasuhiro Yoshimura, Mai Bando, Shuji Nagasaki, and Toshiya Hanada. "Nonlinear Model Predictive Detumbling of Small Satellites with a Single-Axis Magnetorquer." Journal of Guidance, Control, and Dynamics 44, no. 6 (June 2021): 1211–18. http://dx.doi.org/10.2514/1.g005877.

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Ali, Anwar, M. Rizwan Mughal, Haider Ali, Leonardo M. Reyneri, and M. Naveed Aman. "Design, implementation, and thermal modeling of embedded reconfigurable magnetorquer system for nanosatellites." IEEE Transactions on Aerospace and Electronic Systems 51, no. 4 (October 2015): 2669–79. http://dx.doi.org/10.1109/taes.2015.130621.

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Asadabadi, Amirhossein, and Amir M. Anvar. "Small Satellite Modelling and Three-Axis Magnetorquer-Based Stabilisation Using Fuzzy Logic Control." Applied Mechanics and Materials 152-154 (January 2012): 1639–44. http://dx.doi.org/10.4028/www.scientific.net/amm.152-154.1639.

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Recently small satellites have become increasingly popular because of their ability to provide educational institutes with the chance to design, construct, and test their spacecraft from beginning to the possible launch due to the low launching cost and development of microelectronics (Figure 1). Clearly, using only electromagnetic coils instead of different types of actuators will serve the purpose of weight reduction where every grams counts. But some restrictions described in the paper limit utilising only “Electromagnetic” actuation for 3D stabilisation and adversely affects the efficiency of the controller. However, there are some theories developed recently that have made the aforementioned purpose feasible. In this paper a new control method based on Fuzzy Logic Control (FLC) is presented that keeps the satellite in desired conditions only by electromagnetic coils. More precisely, an approach of Fuzzy control which is incorporated with electromagnetic actuation is presented for the in-orbit attitude control of a small satellite. The design is developed to stabilize the spacecraft against disturbances with a three-axis stabilizing capability. The paper also describes the required hardware and the design and development of the magnetic torquers.
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Dissertations / Theses on the topic "Magnetorquer"

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Elmas, Tuba Cigdem. "Development Of Control Allocation Methods For Satellite Attitude Control." Master's thesis, METU, 2010. http://etd.lib.metu.edu.tr/upload/12611649/index.pdf.

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This thesis addresses the attitude control of satellites with similar and dissimilar actuators and control allocation methods on maneuvering. In addition, the control moment gyro (CMG) steering with gyroscopes having limited gimbal angle travel is also addressed. Full Momentum envelopes for a cluster of four CMG'
s are obtained in a pyramid type mounting arrangement. The envelopes when gimbal travel is limited to plus-minus 90 degree are also obtained. The steering simulations using Moore Penrose (MP) pseudo inverse as well as blended inverse are presented and success of the pre planned blended inverse steering in avoiding gimbal angle limits is demonstrated through satellite slew maneuver simulations, showing the completion of the maneuver without violating gimbal angle travel restrictions. Dissimilar actuators, CMG and magnetic torquers are used as an approach of overactuated system. Steering simulations are carried out using different steering laws for constant torque and desired satellite slew maneuver scenarios. Success of the blended inverse steering algorithm over MP pseudo inverse is also demonstrated
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Bellini, Niccolo'. "Magnetic actuators for nanosatellite attitude control." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2014. http://amslaurea.unibo.it/7506/.

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The research and the activities presented in the following thesis report have been led at the California Polytechnic State University (US) under the supervision of Prof. Jordi Puig Suari. The objective of the research has been the study of magnetic actuators for nanosatellite attitude control, called magnetorquer. Theese actuators are generally divided in three different kinds: air core torquer, embedded coil and torquerod. In a first phase of the activity, each technology has been analyzed, defining advantages and disadvantages, determining manufacturing procedures and creating mathematical model and designing equation. Dimensioning tools have been then implemented in numerical software to create an instrument that permits to determine the optimal configuration for defined requirements and constraints. In a second phase of the activities the models created have been validated exploiting prototypes and proper instruments for measurements. The instruments and the material exploited for experiments and prototyping have been provided by the PolySat and CubeSat laboratories. The results obtained led to the definition of a complete designing tool and procedure for nanosatellite magnetic actuators, introducing a cost analysis for each kind of solution. The models and the tools have been maintained fully parametric in order to offer a universal re-scalable instrument for satellite of different dimension class.
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Lehner, Maximilian Jacob. "Study and design of magnetic attitude control systems for nanosatellites." Bachelor's thesis, Alma Mater Studiorum - Università di Bologna, 2019.

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The objective of this bachelor thesis was to display all the attitude and control systems (ACS) available for CubeSats and how magnetic ACS are the most convenient option in terms of volume. Precisely this project focused on the procedure, the design and the laws of physics that are behind the creation of a torque rod, a magnetic attitude and control system conceived for nanosatellites. After discussing the magnetic laws, the different types of materials of the core, and the geometric parameters of the core and of the wire, all of which determine the operating area of the system, a theoretical model for a torque rod was devised. This was done by using the models present in Niccolò Bellini’s master thesis “Magnetic actuators for nanosatellite attitude control”, 2014. This bachelor thesis ended with the gathering of some experimental data on an embedded magnetorquer collected through a Helmholtz cage.
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Curatolo, Andrea. "Development and experimental testing of nanosatellites attitude control using mixed magnetic/mechanical actuation." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2021. http://amslaurea.unibo.it/24337/.

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The Attitude Control System is one of the most important subsystems yet one of the least developed for what concerns the CubeSats. Magnetorquers are often employed as main actuators, thanks to their reduced dimensions. However, a spacecraft actuated by magnetorquers alone suffer from an instantaneous underactuation. Reaction wheels offer better performance but are prone to failure and must be desaturated periodically. It's possible to overcome the limits of both types of actuators by employing an ACS equipped with both types of actuators. In this work, an attitude control law integrating three orthogonally placed mangnetorquers and one reaction wheel is studied and experimentally tested on a dynamic simulator. The first part of the thesis regards the design of the control law. The required control is distributed between actuators using a geometric approach. The control approach is studied through numerical simulations and tuned for a spacecraft of a nanosatellite class. Nonlinear spacecraft dynamical model is considered, as well as worst-case external disturbances, magnetic field and attitude estimation error. The stability of the control law with respect to parameters variations is studied by means of Monte-Carlo approach. In the second part, the designed control law is validated through Hardware-in-the-loop testing on an attitude simulator testbed developed at the University of Bologna. Before-use facility calibration is described. In particular, to provide almost disturbance-free rotational dynamics, the gravity torque acting on the platform have to be compensated. This is done using a novel approach employing jointly shifting masses and magnetorquers (responsible for angular velocity damping). Then, the proposed control law is implemented on-board of the simulator and experimentally assessed. The results show high accuracy and robustness with respect disturbances.
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Trégouët, Jean-François. "Synthèse de correcteurs robustes périodiques à mémoire et application au contrôle d'attitude de satellites par roues à réaction et magnéto-coupleurs." Thesis, Toulouse, ISAE, 2012. http://www.theses.fr/2012ESAE0033/document.

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Les travaux présentés dans ce mémoire constituent une contribution à la conception de méthodes systématiques pour l’analyse et la commande de systèmes périodiques et incertains. Une partie importante de cette thèse est également consacrée au contrôle d’attitude de satellites dont la dynamique se prête naturellement à une représentation sous forme de modèles périodiques soumis à des incertitudes. La première partie propose une présentation unifiée des résultats d’analyse et de synthèse de modèles périodiques et incertains à temps-discret via des méthodes basées sur des inégalités linéaires matricielles (LMI) et en s’appuyant sur la théorie de Lyapunov. Par la suite, l’accent est mis sur une nouvelle classe de correcteurs périodiques à mémoire pour lesquels l’entrée de commande est construite en utilisant l’historique des états du système conservés en mémoire. Des exemples numériques démontrent que ces nouveaux degrés de liberté permettent de repousser les limites des performances robustes. La seconde partie s’intéresse aux aspects de périodicité et de robustesse du contrôle d’attitude de satellite rencontrés notamment lors de l’utilisation des magnéto-coupleurs. Ces actionneurs s’appuient sur le champ géomagnétique variant périodiquement le long de l’orbite du satellite. Différentes stratégies de commande sont mises en œuvre et comparées entre elles avec le souci constant de tenir compte des principales limitations des actionneurs. Cette démarche conduit à une nouvelle loi de commande périodique régulant le moment cinétique des roues à réactions sans perturber le contrôle d’attitude dont l’effort de commande est réparti sur l’ensemble des actionneurs
This manuscript reviews contributions to the development of systematic methods for analysis and control of periodic uncertain systems. An important part of this thesis is also dedicated to the design of attitude control systems for satellites whose dynamics is naturally represented as a periodic model subject to uncertainties. The first part is devoted to the developpement of a unifying presentation of the analysis and synthesis results of periodic, uncertain and discrete-time models via methods relying on linear matrix inequalities (LMI) and based on Lyapunov theory. Subsequently, the focus is on a new class of periodic control laws with memory for which the control input is constructed using history of the states of the system kept in memory. Numerical experiments show that these new degrees of freedom can outperformed the existing results. The second part deals with periodic and robustness aspects of attitude control of a satellite using magnetorquers. These actuators use the geomagnetic field that varies periodically along the orbital trajectory. Different control strategies are implemented and compared with one another with the constant concern of taking the main limitations of the actuators into account. This approach leads to a new control law regulating the momentum of the reaction wheels without disturbing attitude control for which the control effort is shared by all actuators
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Greene, Michael R. "The Attitude Determination and Control System of the Generic Nanosatellite Bus." Thesis, 2009. http://hdl.handle.net/1807/18942.

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The Generic Nanosatellite Bus (GNB) is a spacecraft platform designed to accommodate the integration of diverse payloads in a common housing of supporting components. The development of the GNB at the Space Flight Laboratory (SFL) under the Canadian Advanced Nanospace eXperiment (CanX) program provides accelerated access to space while reducing non-recurring engineering (NRE) costs. The work presented herein details the development of the attitude determination and control subsystem (ADCS) of the GNB. Specific work on magnetorquer coil assembly, integration, and testing (AIT) and reaction wheel testing is included. The embedded software development and unit-level testing of the GNB sun sensors are discussed. The characterization of the AeroAstro star tracker is also a major focus, with procedures and results presented here. Hardware models were developed and incorporated into SFL's in-house high-fidelity attitude dynamics and control simulation environment. This work focuses on specific contributions to the CanX-3, CanX-4&5, and AISSat-1 nanosatellite missions.
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Gondar, Rui Manuel Gomes. "Decentralized Control of Electromagnetic ChipSat Swarm Formations." Master's thesis, 2021. http://hdl.handle.net/10400.6/11700.

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Small satellite formation missions offer new options for space exploration and scientific experiments. Groups of satellites flying within short relative distances allow various important applications, such as spatially distributed instruments for atmospheric sampling or remote sensing systems. The ability to independently control the relative motion of each satellite is crucial to establish a swarm formation, using a large number of satellites moving along bounded relative trajectories. This type of mission poses several constraints on mass, size, and energy consumption; therefore, an autonomous and selfsufficient approach is necessary to assure relative motion control. A novel concept of miniaturized satellites, referred to as ChipSats, consists of a single printed circuit board which can be equipped with different sets of microelectronic components including power and communication systems, a variety of sensors, and a microcontroller. This study considers a swarm of ChipSats equipped with magnetorquers, operating at extremely short relative distances, and using the electromagnetic interaction force for relative motion and attitude control, assuming the absolute position and relative state of each unit is known. Despite the limitations imposed by using magnetorquers as the sole actuators onboard, the dipole interaction between drifting satellites can be used to achieve bounded relative trajectories, and to establish and maintain a compact swarm. Following a decentralized approach, the ChipSats are periodically linked in interchangeable pairs in order to apply the Lyapunov-based control algorithm and prevent relative drift between all satellites in the swarm. The magnetic dipole moments are used for angular velocity damping when orbit control is not required, and a repulsive collision avoidance electromagnetic control force is applied when two ChipSats are within dangerously close proximity to each other. The performance assessment is conducted through Monte Carlo simulations using MATLAB, by analyzing operational parameters and the effect of initial conditions after deployment.
Formações de pequenos satélites oferecem novas opções para exploração espacial e experiências científicas. Grupos de satélites, operando a curtas distâncias relativas, possibilitam importantes aplicações tais como instrumentação espacialmente distribuída para amostragem atmosférica ou sistemas de sensoriamento remoto. A capacidade de controlar de forma independente o movimento de cada satélite é crucial para establecer uma formação em enxame, utilizando um grande número de satélites movendo-se ao longo de trajetórias relativas limitadas. Este tipo de missão impõe várias restrições ao nível do consumo de energia, da massa e do tamanho dos satélites, consequentemente, é necessária uma abordagem autónoma e auto-sustentável para assegurar o controlo das trajetórias relativas. Um novo conceito de satélite miniatura, denominado ChipSat, consiste de uma única placa de circuito impresso que pode ser equipada com diferentes conjuntos de componentes microelectrónicos. Este estudo considera um enxame de ChipSats equipados com magnetorquers, operando a distâncias relativas extremamente reduzidas, e usando a força de interação eletromagnética para controlo do movimento relativo e orientação dos satélites, assumindo que a posição absoluta e relativa de cada unidade é conhecida. Apesar das limitações impostas por usar os magnetorquers como únicos atuadores a bordo, a interação magnética dipolar pode ser usada para limitar trajetórias relativas e establecer um enxame compacto. Seguindo uma abordagem descentralizada, os ChipSats são periodicamente ligados em pares intermutáveis de modo a aplicar o algoritmo de control baseado no teorema de Lyapunov, impedindo o aumento da distância relativa entre todos os satélites no enxame. O momento magnético dipolar é usado para amortecimento da velocidade angular quando o control orbital não é necessário, e uma força eletromagnética repulsiva é usada para controlo de colisão quando dois ChipSats estão perigosamente próximos. A análise de performance é feita através de simulações Monte Carlo no MATLAB, estudando os parâmetros operacionais e o efeito das condições iniciais após o lançamento.
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Book chapters on the topic "Magnetorquer"

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Eun, Youngho, Zihao Wang, and Xiaofeng Wu. "Parametric Study on the Magnetic Properties of the Electropermanent Magnetorquer." In Lecture Notes in Electrical Engineering, 283–97. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-2635-8_21.

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Xiao, Wen, Xin Li, Ningning Zhang, Pengyu Zhang, Yinghui Gong, and Rongyan Ma. "A Distributive Control Method for Microsatellite Using the Biased Momentum Wheel and Magnetorquers." In Lecture Notes in Electrical Engineering, 2323–32. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-15-8155-7_195.

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Bruni, Renato, and Fabio Celani. "Parameter Optimization for Spacecraft Attitude Stabilization Using Magnetorquers." In Advances in Spacecraft Attitude Control. IntechOpen, 2020. http://dx.doi.org/10.5772/intechopen.89197.

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Conference papers on the topic "Magnetorquer"

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Carabellese, Davide, Joshua S. Umansky-Castro, and Mason A. Peck. "Magnetorquer-only Nonlinear Attitude Control for CubeSats." In AIAA Scitech 2021 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-1099.

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Meili, Zhou, and Qi Hongyu. "Design of Three Axis Magnetorquer for Microsatellites." In 2013 Third International Conference on Instrumentation, Measurement, Computer, Communication and Control (IMCCC). IEEE, 2013. http://dx.doi.org/10.1109/imccc.2013.130.

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Eun, Youngho, Zihao Wang, and Xiaofeng Wu. "Performance Measure of the Novel Electropermanent Magnetorquer." In AIAA SCITECH 2023 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2023. http://dx.doi.org/10.2514/6.2023-0936.

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Torczynski, Daniel, Rouzbeh Amini, and Paolo Massioni. "Magnetorquer Based Attitude Control for a Nanosatellite Testplatform." In AIAA Infotech@Aerospace 2010. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-3511.

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Ali, Anwar, Leonardo Reyneri, Juan Carlos de los Rios, Haider Ali, and M. Rizwan Mughal. "Reconfigurable magnetorquer for the CubePMT module of CubeSat satellites." In 2012 15th International Multitopic Conference (INMIC). IEEE, 2012. http://dx.doi.org/10.1109/inmic.2012.6511478.

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"Small-satellite magnetorquer attitude control system modelling and simulation." In 20th International Congress on Modelling and Simulation (MODSIM2013). Modelling and Simulation Society of Australia and New Zealand (MSSANZ), Inc., 2013. http://dx.doi.org/10.36334/modsim.2013.c10.yi.

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Sokal, Ewelina, Roman Wawrzaszek, Grzegorz Juchnikowski, Jakub Adamiec, and Tomasz Zawistowski. "Design and test of magnetorquer in PCB technology for nanosatellites." In Photonics Applications in Astronomy, Communications, Industry, and High-Energy Physics Experiments 2019, edited by Ryszard S. Romaniuk and Maciej Linczuk. SPIE, 2019. http://dx.doi.org/10.1117/12.2537411.

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Eun, Youngho, Zhicheng Xie, Zihao Wang, and Xiaofeng Wu. "Operational Capabilities on the Nanosatellite Attitude Control Actuated by Electropermanent Magnetorquer." In 2022 22nd International Conference on Control, Automation and Systems (ICCAS). IEEE, 2022. http://dx.doi.org/10.23919/iccas55662.2022.10003682.

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Haryadi, Defrandi Renanda, Heroe Wijanto, Budi Syihabuddin, and Agus D. Prasetyo. "Design of attitude determination and control system using microstrip magnetorquer for nanosatellite." In 2016 International Conference on Control, Electronics, Renewable Energy and Communications (ICCEREC). IEEE, 2016. http://dx.doi.org/10.1109/iccerec.2016.7814974.

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Sugimura, Nobuo, Toshinori Kuwahara, and Kazuya Yoshida. "Attitude determination and control system for nadir pointing using magnetorquer and magnetometer." In 2016 IEEE Aerospace Conference. IEEE, 2016. http://dx.doi.org/10.1109/aero.2016.7500665.

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