Document Type : Research Article

Authors

1 Ph.D. Candidate, Department of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran

2 Associate Professor, Department of Aerospace Engineering, Amirkabir University of Technology, Tehran, Iran

3 Associate Professor, Faculty of New Technologies Engineering, Shahid Beheshti University, Tehran, Iran

Abstract

In order to perform attitude control ground experiments, it is crucial to ensure the center of mass of the platform is coincident with the center of rotation as accurate as possible. In this paper, a linearized dynamic model of the imbalanced attitude platform is derived and a linear controller is methodically designed to stabilize the system by mass relocation. The stability conditions of the system under the proposed controller are derived. The balancing procedure starts with a parameter estimation method to estimate the center of mass offsets. Next, the PD controller is applied to align the platform’s horizontal plane with the local horizontal level. Finally, the imbalance in vertical axis can be estimated and compensated to complete the automatic mass balancing. Actuator limitations and nonlinear equations of motion are implemented in numerical simulations and the results demonstrate the effectiveness of the proposed method in significantly reducing the residual imbalance torque on the simulated platform.

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Main Subjects

[1]   J. L. Schwartz, M. A. Peck, and C. D. Hall, “Historical review of air-bearing spacecraft simulators,” J. Guid. Control. Dyn., vol. 26, no. 4, pp. 513–522, 2003, https://doi.org/10.2514/2.5085.
[2]   M. Wilde, C. Clark, and M. Romano, “Historical survey of kinematic and dynamic spacecraft simulators for laboratory experimentation of on-orbit proximity maneuvers,” Prog. Aerosp. Sci., vol. 110, p. 100552, 2019, https://doi.org/10.1016/j.paerosci.2019.100552.
[3]   J. S. Young, “Balancing of a small satellite attitude control simlator on an air bearing,” Utah State Univ., 1998.
[4]   A. Bahu and D. Modenini, “Automatic mass balancing system for a dynamic CubeSat attitude simulator: development and experimental validation,” CEAS Sp. J., vol. 12, pp. 597–611, 2020, https://doi.org/10.1007/s12567-020-00309-5.
[5]   R. Fullmer, “Dynamic ground testing of the skipper attitude control system,” in 34th Aerospace Sciences Meeting and Exhibit, p. 103, 1996, https://doi.org/10.2514/6.1996-103.
[6]   A. McCafferty-Leroux, A. Newton, and S. A. Gadsden, “An improved nanosatellite attitude control simulator for experimental research,” in Sensors and Systems for Space Applications XVI, SPIE, pp. 43–52, 2023, https://doi.org/10.1117/12.2675437.
[7]   H. T. Xuan et al., “From PID to L1 adaptive control for automatic balancing of a spacecraft three-axis simulator,” Int. J. Emerg. Technol. Adv. Eng, vol. 6, no. 1, pp. 77–86, 2016.
[8]   R. Silva, S. Battistini, R. Borges, and C. Cappelletti, “Center of mass compensation of a nanosatellite testbed based on the extended kalman filter,” in 4th IAA Conference on University Satellite Missions and CubeSat Workshop, 2017, pp. 595–606.
[9]   J. J. Kim and B. N. Agrawal, “Automatic mass balancing of air-bearing-based three-axis rotational spacecraft simulator,” J. Guid. Control. Dyn., vol. 32, no. 3, pp. 1005–1017, 2009, https://doi.org/10.2514/1.34437.
[10] S. Chesi et al., “Automatic mass balancing of a spacecraft three-axis simulator: Analysis and experimentation,” J. Guid. Control. Dyn., vol. 37, no. 1, pp. 197–206, 2014, https://doi.org/10.2514/1.60380.
[11] J. Prado et al., “Three-axis air-bearing based platform for small satellite attitude determination and control simulation,” J. Appl. Res. Technol., vol. 3, no. 3, pp. 222–237, 2005.
[12] J. Bryła et al., “Compact and lightweight 3D printed platform for testing attitude determination and control system of small satellites,” Int. J. Multiphys., vol. 15, no. 4, pp. 397–408, 2021, https://doi.org/10.21152/1750-9548.15.4.397.
[13] E. Alnaqbi et al., “Design and Implementation of an Attitude Determination and Control Subsystem testbed for up to 12-U CubeSat,” in AIAA AVIATION 2023 Forum, 2023, p. 3814. https://doi.org/10.2514/6.2023-3814.