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Journal articles on the topic 'Active magnetic attitude control'

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Author: Grafiati

Published: 4 June 2021

Last updated: 7 February 2022

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1

Ovchinnikov, M. Yu, D. S. Roldugin, and V. I. Penkov. "Three-axis active magnetic attitude control asymptotical study." Acta Astronautica 110 (May 2015): 279–86. http://dx.doi.org/10.1016/j.actaastro.2014.11.030.

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2

Jan, Y. W., and J. R. Tsai. "Active control for initial attitude acquisition using magnetic torquers." Acta Astronautica 57, no. 9 (November 2005): 754–59. http://dx.doi.org/10.1016/j.actaastro.2005.03.067.

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3

Arduini, Carlo, and Paolo Baiocco. "Active Magnetic Damping Attitude Control for Gravity Gradient Stabilized Spacecraft." Journal of Guidance, Control, and Dynamics 20, no. 1 (January 1997): 117–22. http://dx.doi.org/10.2514/2.4003.

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4

Ovchinnikov, M. Yu, and D. S. Roldugin. "A survey on active magnetic attitude control algorithms for small satellites." Progress in Aerospace Sciences 109 (August 2019): 100546. http://dx.doi.org/10.1016/j.paerosci.2019.05.006.

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5

Tang, Jiqiang, Jiancheng Fang, and Shuzhi Sam Ge. "Roles of superconducting magnetic bearings and active magnetic bearings in attitude control and energy storage flywheel." Physica C: Superconductivity 483 (December 2012): 178–85. http://dx.doi.org/10.1016/j.physc.2012.07.007.

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6

Jiqiang Tang, Jiancheng Fang, and Wen Wen. "Superconducting Magnetic Bearings and Active Magnetic Bearings in Attitude Control and Energy Storage Flywheel for Spacecraft." IEEE Transactions on Applied Superconductivity 22, no. 6 (December 2012): 5702109. http://dx.doi.org/10.1109/tasc.2012.2218245.

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7

Psiaki, Mark L. "Nanosatellite Attitude Stabilization Using Passive Aerodynamics and Active Magnetic Torquing." Journal of Guidance, Control, and Dynamics 27, no. 3 (May 2004): 347–55. http://dx.doi.org/10.2514/1.1993.

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8

Yao, Xuan, and Zhaobo Chen. "Sliding mode control with deep learning method for rotor trajectory control of active magnetic bearing system." Transactions of the Institute of Measurement and Control 41, no. 5 (June 20, 2018): 1383–94. http://dx.doi.org/10.1177/0142331218778324.

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Active magnetic bearing (AMB) is competent in rotor trajectory control for potential applications such as mechanical processing and spindle attitude control, while the highly nonlinear and coupled dynamic characteristics especially in the condition of rotor large motion are obstacles in controller design. In this paper, a controller of AMB is proposed to achieve rotor 3D trajectory control. First, the dynamic model of the AMB-rotor system containing a nonlinear electromagnetic force model is introduced. Then the DCNN-SMC (deep convolutional neural network - sliding mode control) controller is proposed. Sliding mode control is used to achieve the tracking control with high robustness and responsiveness, and a deep convolutional neural network based on deep learning method is designed to compensate the uncertainties of the system. Finally, simulation of a 5-degree of freedom (DOF) system on various trajectories demonstrates evident control effect of the proposed controller in precision and significant effect of DCNN based on deep learning method in compensation control.

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9

Cui, Peiling, Jingxian He, Jiancheng Fang, Xiangbo Xu, Jian Cui, and Shan Yang. "Research on method for adaptive imbalance vibration control for rotor of variable-speed mscmg with active-passive magnetic bearings." Journal of Vibration and Control 23, no. 2 (August 8, 2016): 167–80. http://dx.doi.org/10.1177/1077546315576430.

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Imbalance vibration control for rotor is the main factor affecting attitude control performance for satellite using magnetically suspended control moment gyro (MSCMG). The method for adaptive imbalance vibration control for the rotor of variable-speed MSCMG with active-passive magnetic bearings is investigated in this paper. Firstly, on the basis of feedforward compensation, a rotor model for the imbalance vibration of variable-speed MSCMG with active-passive magnetic bearings is built, and the main factor affecting imbalance vibration compensation is also analyzed. Then, power amplifier parameter modifier with control switches is designed to eliminate the effects of time-varying parameters on the imbalance vibration compensation precision. The adaptive imbalance vibration control based on this modifier not only has high compensation precision, but also can control the frequency of parameter adjustment according to the compensation precision. Besides, since the passive magnetic bearing displacement stiffness of the rotor of variable-speed MSCMG with active-passive magnetic bearings cannot be obtained accurately, displacement stiffness modifier is employed. Finally, stability analysis is made on the imbalance vibration control system, and the range of rotation speed to ensure system stability is derived. Simulation results show that, imbalance vibration control method proposed in this paper can suppress the imbalance vibration of the rotor of variable-speed MSCMG with active-passive magnetic bearings effectively and has high precision.

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10

Polyakov, Miroslav, Anatoliy Lipovtsev, and Vladimir Lyanzburg. "Mathematical model of a flexible asymmetrical rotor for active magnetic bearing reaction wheel." MATEC Web of Conferences 158 (2018): 01025. http://dx.doi.org/10.1051/matecconf/201815801025.

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The paper introduces the mathematical model of rotor for active magnetic bearing reaction/momentum wheels, used as actuator in spacecraft attitude and orbit control system. Developed model is used for estimation of critical speeds and forced oscillation magnitudes with a glance of the rotor modes. Rotor is considered as a two-mass system, consisting of a shaft and a rim, active magnetic bearings are assumed to be a linear elastic springs. The equations of the rotor motion are derived using the Lagrange equation. Developed model is verified by comparing the calculated Campbell diagrams with the results of the finite-element modal analysis, performed in the ANSYS software.

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11

Yin, Xinfan, Xianmin Peng, Guichuan Zhang, Binghui Che, and Chang Wang. "Flight Control System Design and Autonomous Flight Control of Small-Scale Unmanned Helicopter Based on Nanosensors." Journal of Nanoelectronics and Optoelectronics 16, no. 4 (April 1, 2021): 675–88. http://dx.doi.org/10.1166/jno.2021.2996.

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Due to the limitation of the size and power, micro unmanned aerial vehicle (MUAV) usually has a small load capacity. Aiming at the problems of limited installation space and easy being interfered in flight attitude measurement of the small-scale unmanned helicopter (SUH), a low-cost and lightweight flight control system of the SUH based on ARM Cortex-M4 core microcontroller and Micro-Electro-Mechanical Systems (MEMS) sensors is developed in this paper. On this basis, in order to realize the autonomous flight control of SUH, firstly, the mathematical model of the SUH is given by using the Newton-Euler formulation. Secondly, a cascade flight controller consisting of the attitude controller and the position controller is developed based on linear active disturbance rejection control (LADRC) and proportional-integral-derivative (PID) control. Furthermore, simulations are conducted to validate the performance of the attitude controller and the position controller in MATLAB/SIMULINK simulation environment. Finally, based on the Align T-REX 470L SUH experimental platform, the hovering experiment and the route flight experiment are also carried out to validate the performance of the designed flight control system hardware and the proposed control algorithm. The results show that the flight control system designed in this paper has high reliability and strong anti-interference ability, and the control algorithm can effectively and reliably realize the attitude stabilization control and route control of the SUH, with high control accuracy and small error.

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12

Miranda, Francisco. "Guidance Stabilization of Satellites Using the Geomagnetic Field." International Journal of Aerospace Engineering 2012 (2012): 1–9. http://dx.doi.org/10.1155/2012/231935.

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In the last years the small satellites have played an important role in the technological development. The attractive short period of design and low cost of them and the capacity to solve problems that are usually considered as problems to big and expensive spacecrafts lead us to study the control problem of these satellites. Active three-axis magnetic attitude stabilization of a low Earth orbit satellite is considered in this work. The control is created by interaction between the magnetic moment generated by magnetorquers mounted on the satellite body and the geomagnetic field. This problem is quite complex and difficult to solve. To overcome this difficulty guidance control is considered, where we use ε-strategies introduced by Pontryagin in the frame of differential games theory. Qualitative analysis and results of numerical simulation are presented.

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13

Cui, Peiling, and Jian Cui. "Harmonic current suppression of active-passive magnetically suspended control moment gyro based on variable-step-size FBLMS." Journal of Vibration and Control 23, no. 8 (September 3, 2015): 1221–30. http://dx.doi.org/10.1177/1077546315602153.

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Due to the limitation of the machining accuracy, there exist mass imbalance and sensor runout in magnetically suspended rotor system, which will result in harmonic current in the rotor system. Harmonic current can not only increase the power consumption but also induce harmonic vibration which will be transmitted to spacecraft by magnetic bearings and affect the attitude stability of spacecraft. In order to analyze and reduce harmonic current, the model of magnetically suspended rotor system is built and analyzed. Variable-step-size FBLMS algorithm is proposed in this paper to suppress harmonic current simultaneously. According to the proposed algorithm, step size variation depending on harmonic current and individual step size is figured out for each weight vector so that each frequency component in the block can be adjusted. As a result, convergence performances are further improved by adjusting the weight vectors adaptively. The validity of the proposed method is testified by simulation. Simulation results show that variable-step-size FBLMS algorithm can reduce the harmonic current further and increase the convergence rate.

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14

Abbas, Naqvi Najam, Han Xiao, Li Yan Jun, and Muhammad Raza. "An Architecture Analysis of ADCS for CubeSat: A Recipe for ADCS Design of ICUBE." Applied Mechanics and Materials 110-116 (October 2011): 5397–404. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.5397.

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This research article presents the architecture analysis and design of Attitude determination and control subsystem (ADCS) of the Pico-Satellites especially the CubeSat, developed and launched into the Low Earth orbit (LEO). ADCS is not a stringent requirement for all the CubeSat missions but several missions were specifically designed to test and validate the ADCS. This paper contributes in evaluating the previous ADCS of CubeSat and presents an optimal ADCS design and a recipe for any CubeSat mission and specifically for the upcoming ICUBE of the Institute of Space Technology (IST), Pakistan. The proposed ADCS for ICUBE includes GPS receiver as position sensor while magnetometer as attitude sensor and magnetic coils as the active actuators. The determination will be done by Kalman filter and LQR will be used as a controller.

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15

Wang, Weijie, Xiaocen Chen, Qiang Liu, and Yahong Fan. "Optimal design and experiment study of the double spherical rotor of the MSCSG." Science Progress 104, no. 1 (January 2021): 003685042199848. http://dx.doi.org/10.1177/0036850421998488.

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The magnetically suspended control and sense gyroscope (MSCSG) integrates spacecraft attitude measurement and control function; this paper proposes a double spherical rotor (DSR) for MSCSG. The DSR realizes the five degrees of freedom (DOFs) full active control and full channel magnetic path decoupling by the following design: the spherical axial/radial reluctance magnetic bearings are adopted to control the 3DOFs translation of rotor in the range of double spherical envelope, Lorentz force magnetic bearing (LFMB) is used to precisely drive the 2DOFs universal deflection of rotor. The optimization model is established based on the structural mechanical analysis, taking the deviation between rotor centroid and shape center as the optimization objective, choosing the first order resonance frequency, maximum equivalent stress, rigid body displacement, polar moment of inertia and inertia ratio as constraints. Then the DSR is optimized and simulated by the finite element, the MSCSG principle prototype based on DSR is successfully developed, the online dynamic balance experiment and modal test of the DSR are conducted, where the vibration amount of the DSR decreases from 20 μm before the experiment to 0.14 μm after the experiment, which decreases by 99.3%, the first test modal is 2881 Hz which is 5% different from the finite element simulation value of 3034 Hz. The results show that the DSR has the good mechanical properties and magnetic circuit decoupling characteristics.

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16

Wisniewski, Rafal, and F. Landis Markley. "Optimal Magnetic Attitude Control." IFAC Proceedings Volumes 32, no. 2 (July 1999): 7991–96. http://dx.doi.org/10.1016/s1474-6670(17)57363-2.

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17

VENHOVENS, P. J. TH, A. C. M. VAN DER KNAAP, and H. B. PACEJKA. "Semi-Active Attitude and Vibration Control." Vehicle System Dynamics 22, no. 5-6 (January 1993): 359–81. http://dx.doi.org/10.1080/00423119308969037.

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18

Liquornik, David J., Feng Wei Yang, Mark C. Zwiener, and Richard A. Hayami. "Active attitude control of gun launched projectiles." International Journal of Impact Engineering 23, no. 1 (December 1999): 561–72. http://dx.doi.org/10.1016/s0734-743x(99)00104-9.

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19

Forbes, James Richard. "Attitude control with active actuator saturation prevention." Acta Astronautica 107 (February 2015): 187–95. http://dx.doi.org/10.1016/j.actaastro.2014.10.006.

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20

Damaren, C. J. "Hybrid magnetic attitude control gain selection." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 223, no. 8 (August 1, 2009): 1041–47. http://dx.doi.org/10.1243/09544100jaero641.

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For spacecraft in low Earth orbits, attitude control via the torques provided by the geomagnetic field is an attractive option. Recent research has demonstrated that asymptotic pointing of attitude setpoints is possible using a linear combination of Euler parameter and angular velocity feedback. However, given the time-varying nature of the magnetic field, the size of the gains leading to stability is restricted. The present work looks at a hybrid scheme consisting of magnetic control using on-board dipole moments and an independent three-axis actuation scheme (i.e. reaction wheels or thrusters). A stability analysis is presented using passivity concepts that shows that the limitation on magnetic control gains can be removed if a minimum level of three-axis actuation augments the magnetic scheme.

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21

Zanchettin, Andrea Maria, Alberto Calloni, and Marco Lovera. "Robust Magnetic Attitude Control of Satellites." IEEE/ASME Transactions on Mechatronics 18, no. 4 (August 2013): 1259–68. http://dx.doi.org/10.1109/tmech.2013.2259843.

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22

Lovera, M., and A. Astolfi. "Spacecraft attitude control using magnetic actuators." Automatica 40, no. 8 (August 2004): 1405–14. http://dx.doi.org/10.1016/j.automatica.2004.02.022.

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23

Cai, Xiao Xiao, Jin Jie Wu, and Kun Liu. "Attitude Active Disturbance Rejection Control of Agile Satellite." Applied Mechanics and Materials 419 (October 2013): 673–81. http://dx.doi.org/10.4028/www.scientific.net/amm.419.673.

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Based on the mission requirements of agile satellite, the control method of large angle maneuver was investigated in this paper. The single gimbal control moment gyroscope (sgcmg) of pyramid configuration is taken as the executor of the satellite. In order to avoid the singularity of sgcmgs, robust pseudo-inverse steering logic is used. An attitude active disturbance rejection controller (adrc) was designed. The expected attitude maneuver information that got by gauss pseudo-spectral method (gpm) took the place of that got by tracking differentiator (td). The constraints of satellite and sgcmgs are considered. Dynamics decoupling and disturbance observation of satellite were realized by using nonlinear extended state observer (neso). Then based on neso, nonlinear error feedback controller (nlsef) effectively suppresses the disturbance. The simulation results show that the attitude active disturbance rejection controller has steady control performance and can reject the disturbance better.

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24

Pittet, C., J. Mignot, and F. Viaud. "Attitude and active payload control: the H ∞ revolution." IFAC-PapersOnLine 50, no. 1 (July 2017): 6440–45. http://dx.doi.org/10.1016/j.ifacol.2017.08.1033.

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25

Bianchi, D., A. Borri, B. Castillo–Toledo, M. D. Di Benedetto, and S. Di Gennaro. "Active Control of Vehicle Attitude with Roll Dynamics." IFAC Proceedings Volumes 44, no. 1 (January 2011): 7174–79. http://dx.doi.org/10.3182/20110828-6-it-1002.03678.

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26

Voskuijl, M., D. J. Walker, and B. J. Manimala. "Helicopter load alleviation using active control." Aeronautical Journal 112, no. 1137 (November 2008): 663–72. http://dx.doi.org/10.1017/s0001924000002633.

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Abstract This paper discusses how structural load objectives can be included in a rotorcraft flight control system design in an efficient and straightforward way using multivariable control techniques. Several research studies have indicated that pitch link loads for various rotorcraft types can reach high or even unacceptable values, both in steady state and maneuvering flight. This is especially the case for high-speed aggressive maneouvers. Pitch link loads at high-speed flight are therefore taken as a case study. A novel longitudinal control system is presented, designed to reduce helicopter pitch-link loads during high-speed longitudinal manoeuvres whilst providing a pitch attitude command attitude hold response type. The design is based on a high-order model of a helicopter representative of the UH-60 Black Hawk. New metrics are presented for the analysis of structural loads that can be used in combination with ADS-33 handling qualities requirements.

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27

Ousaloo, H. S., M. T. Nodeh, and R. Mehrabian. "Verification of Spin Magnetic Attitude Control System using air-bearing-based attitude control simulator." Acta Astronautica 126 (September 2016): 546–53. http://dx.doi.org/10.1016/j.actaastro.2016.03.028.

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28

Findlay, Everett J., Anton de Ruiter, James R. Forbes, Hugh H. T. Liu, Christopher J. Damaren, and James Lee. "Magnetic Attitude Control of a Flexible Satellite." Journal of Guidance, Control, and Dynamics 36, no. 5 (September 2013): 1522–27. http://dx.doi.org/10.2514/1.57300.

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29

VENHOVENS, P. J. TH, A. C. M. van der KNAAP, A. R. SAVKOOR, and A. J. J. van der WEIDEN. "Semi-Active Control of Vibration and Attitude of Vehicles." Vehicle System Dynamics 23, sup1 (January 1994): 522–40. http://dx.doi.org/10.1080/00423119308969538.

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30

Bai, Yuliang, James D. Biggs, Xiaogang Wang, and Naigang Cui. "A singular adaptive attitude control with active disturbance rejection." European Journal of Control 35 (May 2017): 50–56. http://dx.doi.org/10.1016/j.ejcon.2017.01.002.

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31

Arai, Masataka. "The Possibility of Active Attitude Control for Fuel Spray." Engineering 5, no. 3 (June 2019): 519–34. http://dx.doi.org/10.1016/j.eng.2019.04.010.

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32

Jastrzebski, Rafal P., Katja M. Hynynen, and Alexander Smirnov. "control of active magnetic suspension." Mechanical Systems and Signal Processing 24, no. 4 (May 2010): 995–1006. http://dx.doi.org/10.1016/j.ymssp.2009.10.008.

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33

Salleh, Mohd Badrul, Nurulasikin Mohd Suhadis, and Renuganth Varatharajoo. "An active force controlled of small CMG-based satellite." Aircraft Engineering and Aerospace Technology 93, no. 7 (June 15, 2021): 1183–92. http://dx.doi.org/10.1108/aeat-01-2020-0017.

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Purpose This paper aims to investigate the attitude control pointing improvement for a small satellite with control moment gyroscopes (CMGs) using the active force control (AFC) method. Design/methodology/approach The AFC method is developed with its governing equations and integrated into the conventional proportional-derivative (PD) controller of a closed-loop satellite attitude control system. Two numerical simulations of an identical attitude control mission namely the PD controller and the PD+AFC controller were carried out using the MATLAB®-SimulinkTM software and their attitude control performances were demonstrated accordingly. Findings Having the PD+AFC controller, the attitude maneuver can be completed within the desired slew rate, which is about 2.14 degree/s and the attitude pointing accuracies for the roll, pitch and yaw angles have improved significantly by more than 85% in comparison with the PD controller alone. Moreover, the implementation of the AFC into the conventional PD controller does not cause significant difference on the physical structure of the four single gimbal CMGs (4-SGCMGs). Practical implications To achieve a precise attitude pointing mission, the AFC method can be applied directly to the existing conventional PD attitude control system of a CMG-based satellite. In this case, the AFC is indeed the backbone for the satellite attitude performance improvement. Originality/value The present study demonstrates that the attitude pointing of a small satellite with CMGs is improved through the implementation of the AFC scheme into the PD controller.

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34

Kertész, Milan, Radko Kozakovič, Luboš Magdolen, and Michal Masaryk. "Active Displacement Control of Active Magnetic Bearing System." Scientific Proceedings Faculty of Mechanical Engineering 22, no. 1 (December 1, 2014): 32–37. http://dx.doi.org/10.2478/stu-2014-0006.

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AbstractThe worldwide energy production nowadays is over 3400 GW while storage systems have a capacity of only 90 GW [1]. There is a good solution for additional storage capacity in flywheel energy storage systems (FES). The main advantage of FES is its relatively high efficiency especially with using the active magnetic bearing system. Therefore there exist good reasons for appropriate simulations and for creating a suitable magneto-structural control system. The magnetic bearing, including actuation, is simulated in the ANSYS parametric design language (APDL). APDL is used to create the loops of transient simulations where boundary conditions (BC) are updated based upon a “gap sensor” which controls the nodal position values of the centroid of the shaft and the current density inputs onto the copper windings.

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35

Yu, Z., Y. Guo, L. Wang, and L. Wu. "Adaptive robust attitude control and active vibration suppression of flexible spacecraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 6 (May 18, 2016): 1076–87. http://dx.doi.org/10.1177/0954410016648349.

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This paper presents the large angle attitude manoeuvre control design of a single-axis flexible spacecraft system that consists of a central rigid body and a cantilever beam with bonded piezoelectric sensor/actuator pairs as a flexible appendage. The proposed control strategy combines the attitude controller designed by the adaptive robust control technique with the active vibration controller designed by the positive position feedback control method. The desired angular position of the spacecraft is planned and an adaptive robust attitude control approach based on a projection type adaptation law is proposed to track the planned path and to achieve precise attitude manoeuvre control. Meanwhile, the positive position feedback control method is applied to actively increase the damping of the flexible appendage and to suppress the residual vibration induced by manoeuvre. Improved transient and steady state performance during and after large angle attitude manoeuvre can be both achieved by integration of the technical merits of all these control methods. Analytical and numerical results illustrate the effectiveness of this approach.

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36

de Angelis, Emanuele L., Fabrizio Giulietti, Anton H. J. de Ruiter, and Giulio Avanzini. "Spacecraft Attitude Control Using Magnetic and Mechanical Actuation." Journal of Guidance, Control, and Dynamics 39, no. 3 (March 2016): 564–73. http://dx.doi.org/10.2514/1.g000957.

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37

Chabot, Joshua, and Hanspeter Schaub. "Spherical Magnetic Dipole Actuator for Spacecraft Attitude Control." Journal of Guidance, Control, and Dynamics 39, no. 4 (April 2016): 911–15. http://dx.doi.org/10.2514/1.g001471.

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38

Lovera, Marco, and Alessandro Astolfi. "Global Magnetic Attitude Control of Inertially Pointing Spacecraft." Journal of Guidance, Control, and Dynamics 28, no. 5 (September 2005): 1065–72. http://dx.doi.org/10.2514/1.11844.

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39

Wiśniewski, Rafał. "Sliding Mode Attitude Control for Magnetic Actuated Satellite." IFAC Proceedings Volumes 31, no. 21 (August 1998): 179–84. http://dx.doi.org/10.1016/s1474-6670(17)41076-7.

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40

Das, S., M. Sinha, K. D. Kumar, and A. Misra. "Reconfigurable magnetic attitude control of Earth-pointing satellites." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 224, no. 12 (June 7, 2010): 1309–26. http://dx.doi.org/10.1243/09544100jaero681.

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41

Pulecchi, Tiziano, and Marco Lovera. "ATTITUDE CONTROL OF SPACECRAFT WITH PARTIALLY MAGNETIC ACTUATION." IFAC Proceedings Volumes 40, no. 7 (2007): 609–14. http://dx.doi.org/10.3182/20070625-5-fr-2916.00104.

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42

Lovera, M., and A. Varga. "OPTIMAL DISCRETE-TIME MAGNETIC ATTITUDE CONTROL OF SATELLITES." IFAC Proceedings Volumes 38, no. 1 (2005): 157–62. http://dx.doi.org/10.3182/20050703-6-cz-1902.01987.

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43

Cubas, Javier, and Anton de Ruiter. "Magnetic control without attitude determination for spinning spacecraft." Acta Astronautica 169 (April 2020): 108–23. http://dx.doi.org/10.1016/j.actaastro.2019.12.029.

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44

Colagrossi, Andrea, and Michèle Lavagna. "Fully magnetic attitude control subsystem for picosat platforms." Advances in Space Research 62, no. 12 (December 2018): 3383–97. http://dx.doi.org/10.1016/j.asr.2017.10.022.

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45

Hemmati, Saeed, Morteza Shahravi, and Keramat Malekzadeh. "Active Vibration Control of Satellite Flexible Structures during Attitude Maneuvers." Research Journal of Applied Sciences, Engineering and Technology 5, no. 15 (April 25, 2013): 4029–37. http://dx.doi.org/10.19026/rjaset.5.4472.

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46

Qu, Fa Yi, Liang Kuan Zhu, and Wen Long Song. "Fuzzy Adaptive Variable Structure Active Attitude Control of Flexible Spacecraft." Applied Mechanics and Materials 44-47 (December 2010): 2070–74. http://dx.doi.org/10.4028/www.scientific.net/amm.44-47.2070.

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This paper presents a novel control system design method for the three-axis-rotational tracking and vibration stabilization of a spacecraft with flexible appendages. Based on the sliding control theory, a robust attitude control law is derived to control the attitude motion of spacecraft. For actively suppressing the induced vibration, both fuzzy methods and strain rate feedback (SRF) control methods are presented. Numerical simulations are performed to show the feasibility and effeteness of the proposed methods.

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47

Steyn, Willem Herman, and Hendrik Willem Jordaan. "An active attitude control system for a drag sail satellite." Acta Astronautica 128 (November 2016): 313–21. http://dx.doi.org/10.1016/j.actaastro.2016.07.039.

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48

Bianchi, D., A. Borri, M. D. Di Benedetto, and S. Di Gennaro. "Active Attitude Control of Ground Vehicles with Partially Unknown Model." IFAC-PapersOnLine 53, no. 2 (2020): 14420–25. http://dx.doi.org/10.1016/j.ifacol.2020.12.1440.

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49

Penkov, Vladimir Ivanovich, and Dmitry Sergeevich Roldugin. "Active inertial magnetic attitude of a satellite in gravitational field." Keldysh Institute Preprints, no. 163 (2018): 1–18. http://dx.doi.org/10.20948/prepr-2018-163.

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Su, Zhi-qiang, Meng Zhou, Fang-fang Han, Yi-wu Zhu, Da-lei Song, and Ting-ting Guo. "Attitude control of underwater glider combined reinforcement learning with active disturbance rejection control." Journal of Marine Science and Technology 24, no. 3 (August 10, 2018): 686–704. http://dx.doi.org/10.1007/s00773-018-0582-y.

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