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The Injection Velocity and Apogee Simulation for Transfer Elliptical Satellite Orbits

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DOI: 10.4236/ijcns.2012.53023    5,343 Downloads   8,705 Views   Citations

ABSTRACT

Basic resources for communication satellites are communication radio-frequencies and satellite orbits. An orbit is the trajectory followed by the satellite. The communication between the satellite and a ground station is established only when the satellite is consolidated in its own orbit and it is visible from the ground station. Different types of orbits are possible, each suitable for a specific application or mission. Most used orbits are circular, categorized as low, medium and geosynchronous (geostationary) orbits based on the attitude above the Earths surface. The launching process heading the satellite in geostationary orbit, by the first step places the satellite in a transfer orbit. The transfer orbit is elliptical in shape with low attitude at perigee, and the apogee of the geostationary orbit attitude. The apogee of the parking orbit depends on the injection velocity applied at perigee. Simulation approach of injection velocity at perigee to attain different apogees, considering an incremental step is presented in this paper.

Conflicts of Interest

The authors declare no conflicts of interest.

Cite this paper

S. Cakaj, B. Kamo, V. Koliçi and O. Shurdi, "The Injection Velocity and Apogee Simulation for Transfer Elliptical Satellite Orbits," International Journal of Communications, Network and System Sciences, Vol. 5 No. 3, 2012, pp. 187-191. doi: 10.4236/ijcns.2012.53023.

References

[1] O. Hoernig and D. Sood, “Military Applications of Commercial Communications Satellites”, Military Communications Conference Proceedings, Atlantic City, 31 October-3 November 1999, pp. 107-111.
[2] A. Maini and V. Agrawal, “Satellite Technology,” Wiley, London, 2010. doi:10.1002/9780470711736
[3] E. C. Lorenzini, et al., “Mission Analysis of Spinning Systems for Transfers from Low Orbits to Geostationary,” Journal of Spacecraft and Rockets, Vol. 37, No. 2, 2000, pp. 165-172. doi:10.2514/2.3562
[4] L. Jiancheng, “Separation of Geostationary Satellites with Eccentricity and Inclination Vector,” Proceedings: International Conferece on Measuring Technology and Mechatronics Automation, Changsha, 11-12 April 2009, pp. 855-858.
[5] D. Roddy, “Satellite Communications,” McGraw Hill, New York, 2006.
[6] M. Richharia, “Satellite Communication Systems,” McGraw Hill, New York, 1999.
[7] Sh. Cakaj, “Intermodulation Interference Modelling for Low Earth Orbiting Satellite Ground Stations,” Modelling, Simulation and Optimization, I-Tech, Vienna, 2009, pp. 1-20.
[8] Sh. Cakaj, “Horizon Plane and Communication Duration for Low Earth Orbiting (LEO) Satellite Ground Stations,” Transactions on Communications, Vol. 8, No. 4, 2009, pp. 373-383.
[9] Z. Ismail and R. Varatharajoo, “A Study of Reaction Wheel Configuration for a 3-Axis Satellite Attitude Control,” Advances in Space Research, Vol. 45, No. 6, 2009, pp. 750-759. doi:10.1016/j.asr.2009.11.004
[10] R. Esmailzadeh, H. Arefkhani and S. Davoodi, “Active Control and Attitude Stabilization of a Momentum-Biased Satellite without Yaw Measurements,” Proceedings of 19th Iranian Conference on Electrical Engineering, Tehran, 17-19 May 2011, pp. 1-6.
[11] M. Reyhanoglu and S. Drakunov, “Attitude Stabilization of Small Satellites Using Only Magnetic Actuation,” 34th Conference on Industrial Electronics, Orlando, 10-13 November 2008, pp. 103-107. doi:10.1109/IECON.2008.4757936
[12] H. Min, et al., “Optimal Collision Avoidance Maneuver Control for Formation Flying Satellites Using Linear Programming,” Proceedings of 29th Chinese Control Conference, Beijing, 29-31 July 2010, pp. 3390-3393.
[13] A. Mohammadi, et al., “On Application of Q-Guidance Method for Satellite Launch Systems,” 3rd International Symposium on Systems and Control in Aeronautics and Astronautics, Harbin, 8-10 June 2010, pp. 1314-1319. doi:10.1109/ISSCAA.2010.5632295
[14] J. Pearson, “Low Cost Launch Systems and Orbital Fuel Depot,” Acta Astronautica, Vol. 18, No. 4, 1999, pp. 315-320.

  
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