Magnetic Gimbal Angle Compensator of CMG-Based Controlled Small Satellite
The presence of external disturbance torques causes the gimbals angle of Control Moment Gyros (CMG) used to control satellite drift from their preferred initial value. This scenario will drive the CMG into singular states or result in attitude error thus reducing the chance to do slew maneuver. In this paper, a novel method to compensate drifted gimbals of CMG based controlled small satellite operated in low earth orbit is adopted. The satellite is equipped with four Single Gimbal CMG (SGCMG) pyramid-array configuration. Three magnetic torquers are used to generate the compensation control torque where the controlleris designed based on the gimbal angle converging time. Simulations are performed using Matlab®/Simulink® software for various value of gimbals angle converging time to optimize the compensator performance. Results from simulation show that the optimal performance of the system is when the converging time is set at100s.
Copyright © 2015 Praise Worthy Prize - All rights reserved.
Salleh M.B., and MohdSuhadis. N., Three-Axis Attitude Control Performance of a Small Satellite Using Control Moment Gyroscope, Applied Mechanics and Materials, Vol. 629, 2014, pp 286-290.
Bong Wie, David Bailey, and Christoper Heiberg, Rapid Multitarget Acquisition and Pointing Control of Agile Spacecraft, Journal of Guidance, Control, and Dynamics, Vol. 25, No. 1, (2008).
V. Lappas, WH Steyn and CI Underwood, Attitude Control for Small Satellites Using Control Moment Gyros, ActaAstronautica, Vol. 51, (2002), 101-111.
A. Defendini, K. Lagadec, P. Guay, T. Blais and G. Griseri, Low Cost CMG-Based AOCS Design, Proceedings 4th ESA International Conference on Spacecrft Guidance, Navigation and Control System, ESTEC, Noodwijk, The Netherlands, (1999).
K. Omagari, T. Usuda and S. Matunaga, Research of Control Momentum Gyros for Micro-Satellites and 3-DOF Attitude Dynamics Simulator Experiments, Proceedings of The 8th International Symposium on Artificial Intelligence, Robotics and Automation in Space-iSAIRAS, Munich, Germany, (2005).
R. Berner, Control Moment Gyro Actuator for Small Satellite Applications, Master Thesis, Dept. Elect. Eng., University of Stellenbosch, 2005.
Carron de La Morinais, G., Salenc, C., Privat, M., Mini CMG Development for Future European Agile Satellites, 5th ESA International Conference on Spacecraft Guidance, Navigation and Control Systems, 2002.
Salenc, C., Roser, X., AOCS for Agile Scientific Spacecraft with Mini CMGs, 4th ESA International Conference on Spacecrft Guidance, Navigation and Control System, ESTEC, Noodwijk, The Netherlands, (1999).
Patankar K., Fitz-Coy, N., Roithmayr C. M., Design Consideration for Miniaturized Control Moment Gyroscopes for Rapid Retargeting and Precision Pointing of Small Satellites, 28th Annual AIAA/USU, Conference on Small Satellites, SSC14-III-8, (2014).
Vadali S. R. et al, 1990, Preferred Gimbal Angles for Single Gimbal Control Moment Gyros, Journal of Guidance, Control and Dynamics, 13(6), (1990).
F. A. Leve and N. G. Fitz-Coy, Hybrid Steering Logic for Single-Gimbal Control Moment Gyroscopes, Journal of Guidance, Control, and Dynamics,Vol. 33, No. 4, July-August, (2010).
K. Takada, H. Kojima and N. Matsuda, Control Moment Gyro Singularity-Avoidance Steering Control Based on Singular-Surface Cost Function, Journal of Guidance, Control, and Dynamics, Vol. 33, No. 5, September-October, (2010).
Bedrossian, N. S. et al, Steering law design for redundant single gimbal moment gyroscope, Journal of Gidance, Control and Dynamics, 13(6), (1990).
Nurulasikin Mohd Suhadis, Renuganth Varatharajoo, Satellite Attitude Performance during the Momentum Dumping Mode, (2009) International Review of Aerospace Engineering (IREASE), 2 (3), pp. 133-138.
Robert J. Mcelvain, Satellite Angular Momentum Removal Utilizing the Earth's Magnetic Field,Applied Mathematics and Mechanics,Volume 7,( 1964), 137–158.
Azor, R., Momentum Management and Torque Distribution in a Satellite with Reaction Wheels, Israel Annual Conference on Aviation and Astronautics (25-25 February, Tel Aviv), Tel Aviv: Kenes, 1993, pp. 339-47.
V. Lappas, W. Steyn, C. Underwood, Control Moment Gyro Gimbal Angle Compensation Using Magnetic Control During External Disturbances, AIAA Guidance, Navigations, and Control and Exhibit, Canada, (2001).
Wie, B., Space Vehicle Dynamics and Control, (AIAA Education Series, 1998, pp. 667-708).
Blanke, M., Satellite Dynamics and Control in a Quaternion Formulation, Lecture Note for Course 31365, Spacecraft Dynamics and Control, Denmark, pp. 4-6, 2004.
V. J. Lappas, A Control Moment Gyro (CMG) Based Attitude Control System (ACS) for Agile Small Satellites, Doctoral Thesis, University of Surrey, 2002.
M.J. Sidi, Spacecraft Dynamics and Control, (Cambridge University Press, 1997 pp. 322-327).
Z. Ismail, and R. Varatharajoo, AStudy of Reaction Wheel Configuration for a 3-Axis Satellite Attitude Control, Advances in Space Research 45,750-759, 2010.
Omar, H.M., Developing geno-fuzzy controller for satellite stabilization with gravity gradient, (2014) International Review of Aerospace Engineering, 7 (1), pp. 8-16.
Ataei, M., Moallem, P., Mahsouri, R., A comprehensive model of a tracker system based on motion equations of a two degree-of-freedom gimbal system, (2014) International Review of Aerospace Engineering, 7 (4), pp. 134-141.
- There are currently no refbacks.
Please send any question about this web site to email@example.com
Copyright © 2005-2020 Praise Worthy Prize