Abstract The aim of this paper is to present the basic mathematical and theoretical knowledge of the orbit geometry system of the satellite. Information about the orbit of the satellite system is considered as the critical and main parts of the satellite design. The presented design model of the orbit geometry is valid for mini satellites (100-500 kg), which are used for imaging missions. The objective of the design model is to minimize the size, the mass, and the complexity of the satellite so that it fits the envelope of the launching vehicle. The propulsion system and others equipments of the satellite as the payload or the imaging system, on board computer system, data link and the solar cells determine the size and mass of the satellite. An example of orbit geometry for a satellite was described included the results of the design model.
Somaie, A., Badawy, W., & Pira, R. (2006). DESIGN OF AN ORBIT OF A MINI SATELLITE. The International Conference on Electrical Engineering, 5(5th International Conference on Electrical Engineering ICEENG 2006), 1-10. doi: 10.21608/iceeng.2006.33644
MLA
A A Somaie; Wael Badawy; Rahim Pira. "DESIGN OF AN ORBIT OF A MINI SATELLITE", The International Conference on Electrical Engineering, 5, 5th International Conference on Electrical Engineering ICEENG 2006, 2006, 1-10. doi: 10.21608/iceeng.2006.33644
HARVARD
Somaie, A., Badawy, W., Pira, R. (2006). 'DESIGN OF AN ORBIT OF A MINI SATELLITE', The International Conference on Electrical Engineering, 5(5th International Conference on Electrical Engineering ICEENG 2006), pp. 1-10. doi: 10.21608/iceeng.2006.33644
VANCOUVER
Somaie, A., Badawy, W., Pira, R. DESIGN OF AN ORBIT OF A MINI SATELLITE. The International Conference on Electrical Engineering, 2006; 5(5th International Conference on Electrical Engineering ICEENG 2006): 1-10. doi: 10.21608/iceeng.2006.33644
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