Affiliation:
1. Universiti Sains Malaysia
2. Universiti Putra Malaysia
Abstract
In this paper, the Proportional-Derivative (PD) based attitude control algorithm of the gravity gradient stabilized satellite has been developed. The satellite is equipped with 3 magnetic torquers where each of the magnetic torquer is placed along the +x, +y, +z axes. The control torque is generated when the magnetic field generated by the magnetic torquers couples with the geomagnetic fields, whereby the vector of the generated torque is perpendicular to both the magnetic fields. The developed control algorithm was simulated using the complex and simplified geomagnetic field models for a Low Earth Orbit (LEO) satellite mission in a nominal attitude operation. Results from simulations exhibit the effectiveness of the attitude control torque generation that fulfills the mission attitude control requirements.
Publisher
Trans Tech Publications, Ltd.
Reference13 articles.
1. M.J. Sidi, Spacecraft Dynamics and Control, Cambridge University Press, (1997).
2. K. Maeda, T. Hidaka, M. Uo, A magnetic libration control scheme for gravity-gradient stabilized satellite, Advances in the Astronautical Sciences, Vol. 96(6), (1997) p.887 – 896.
3. N. Mohd Suhadis, R. Varatharajoo, Satellite Attitude Performance during the Momentum dumping Mode, International Review of Aerospace Engineering, Vol. 3(2), (2009) pp.133-138.
4. Z. Sun, Y. Cheng, Y. Geng, and X. Cao, The Active Magnetic Control Algorithm for HITSAT-1, Journal of Aircraft Engineering and Aerospace Technology, Vol. 72, No. 2, (2000) p.137 – 141.
5. R. Wisnieskiand M. Blanke, Fully Magnetic Attitude Control for Spacecraft Subject to Gravity Gradient, Automatica, Vol. 35, (1999) pp.1201-1214.
Cited by
3 articles.
订阅此论文施引文献
订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献