Document Type : Scientific extension

Authors

1 M.Sc., Malek Ashtar University,Isfahan, Iran.

2 Associate Professor, Department, Dynamic of Flight and Control, Maleke-ashtar University of technology Isfahan,Iran.

Abstract

 One of the important factors in the design of spacecraft is the efficient selection of spacecraft attitude control system. In some cases, due to the mission of spacecraft, several status control systems are used in combination. The achievement of practical and efficient methods as well as new methods in subsystem of state control is of particular importance. Therefore, studies and researches carried out in this field are often applied to improve the efficiency of state control and optimization methods from parameters such as fuel consumption, time, and cost. In this research, possibility of realizing the design of the spacecraft control system through the displacement of main engine will be examined. It is necessary to reduce equipment and systems of the state control subsystem, including: (thrusters, fuel transfer pipes, automatic valves, nozzles, power transmission cables, control signals, and structural complexities). Realizing the above-mentioned requirement in spacecraft will reduce the weight, cost, and complexity of the instruments.

Keywords

[1]   Kaplan, M.H., Modern spacecraft dynamics & control, 1st Ed., John Wiley & Sons, New York, 1976.
[2]   Markley, F.L., Fundamentals of Spacecraft Attitude Determination and control, 1st Ed., Springer, New York, 2014.
[3]   Brown, C.D., Elements of Space Design, 1st Ed., American Institute of Aeronautics and Astronautics, Virginia, 2002.
[4]   Yang, Y., “Spacecraft attitude and reaction wheel desaturation combined,” Journal of Control Method, Vol.11, 2016, pp. 54-59.
[5]   Borissov, S., Wu, Y. andMortari, D., “East–West GEO satellite station-keeping with degraded thruster Response,” Journal of Aerospace, Vol. 2, 2015, pp. 581-601.
[6]   Kosari, A., Kaviri, S.,Moshiri, B. and Fakoor, M., “Design of optimal thruster configuration for attitude control of geostationary satellite,” Journal of Modares Mechanical Engineering, Vol.13, 2014, pp.67-77.
[7]   Cassady, R.J., Meckel, N.J., Hoskins, W.A. and McGuire, M.L., “Pulsed Plasma Thruster Systems for Spacecraft Attitude Control,” ocobr 2014.
[8]   Sabgatullahi, F., vertical flight aircraft, patent number 48464, country's documents and real estate registration organization, general department of industrial property, patent registration, Tehran, Iran, 2009 (In Persian).
[9]   Chung, S.J., “Propellant free control of tethered formation flight,” Journal of guidance control and dynamics, Vol.31, 2008, pp. 390-400.
[10]  Pourtakdoust, S. H. andJalali, M. A., “Thrust-Limited optimal Three-Dimensional spacecraft trajectories,” Journal of American Institute of Aeronautics and Astronautics, Vol. 14,  2000,  pp.81-89.
[11]  Martinsfilho, L. S. and Santana, A,. “Optimal On-Off Attitude Control for the Brazilian Multimission Platform Satellite,” Journal of Mathematical Problems in Engineering, Vol.17, 2009, pp.55-68.
[12]  Sidi, M.J., Spacecraft dynamics & control a practical engineering approach, 1st Ed., Press Syndicate of the University of Cambridge, New York, 1997.