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Balanis, C. 1982. Antenna Theory Analysis and Design. Harper & Row, New York. Brain, D. J., and A. W. Rudge. 1984. Electronics and Power. J. of the IEEE, Vol. 30, No. 1, January, pp. 51 56. Brown, R. E. 1998. RF-MEMS Switches for Reconfigurable Integrated Circuits. IEEE Trans. on Microwave Theory and Techniques, Vol. 46, No. 11, November, pp. 1868 1880. Chang, K. (ed.). 1989. Handbook of Microwave and Optical Components, Vol. 1. Wiley, New York. De Flaviis, F., N. G. Alexopoulos, and, O. M. Stafsudd. 1997. Planar Microwave Integrated Phase Shifter Design with High Purity Ferroelectric Material. IEEE Trans. on Microw. Theory and Tech., Vol. 45, No. 6, June, pp. 963 969 (see also www.ece.uci.edu/ rfmems/publications/papers-pdf/J005.PDF). Glazier, E. V. D., and H. R. L. Lamont. 1958. The Services Textbook of Radio, Vol. 5: Transmission and Propagation. Her Majesty s Stationery Office, London. Hwang, Y. 1992. Satellite Antennas. Proc. IEEE, Vol. 80, No. 1, January, pp. 183 193. James, J. R., P. S. Hall, and C. Wood. 1981. Microstrip Antenna Theory and Design. Peter Peregrinus, UK. Kummer, W. H. 1992. Basic Array Theory. Proc. IEEE, Vol. 80, No. 1, January, pp. 127 140. Miya, K. (ed.). 1981. Satellite Communications Technology. KDD Engineering and Consulting, Japan. Olver, A. D. 1992. Corrugated Horns. Electron. Commun. Eng. J., Vol. 4, No. 10, February, pp. 4 10. Pozar, D. M.2004. Microstrip Reflectarrays Myths and Realities. JINA Conference (see www.ecs.umass.edu/ece/pozar/jina.ppt). Reid, J. R. 2005. Microelectromechanical Phase Shifters for Lightweight Antennas, at www.afrlhorizons.com. Rudge, A. W., K. Milne, A. D. Olver, and P. Knight (eds.). 1982. The Handbook of Antenna Design, Vol. 1. Peter Peregrinus, UK.

Rusch, W. V. T. 1992. The Current State of the Reflector Antenna Art: Entering the 1990s. Proc. IEEE, Vol. 80, No. 1, January, pp. 113 126. Nishio, T., X. Hao, W. Yuanxun, and T. Itoh, 2004. A Frequency Controlled Active Phased Array. IEEE Microw. and Components Lett., Vol. 14, No. 3 March. pp. 115 117. Vectors. 1993. Hughes in-house magazine, Vol. XXXV, No. 3.

7.1 Introduction A satellite communications system can be broadly divided into two segments a ground segment and a space segment. The space segment will obviously include the satellites, but it also includes the ground facilities needed to keep the satellites operational, these being referred to as the tracking, telemetry, and command (TT&C) facilities. In many networks it is common practice to employ a ground station solely for the purpose of TT&C. The equipment carried aboard the satellite also can be classified according to function. The payload refers to the equipment used to provide the service for which the satellite has been launched. The bus refers not only to the vehicle which carries the payload but also to the various subsystems which provide the power, attitude control, orbital control, thermal control, and command and telemetry functions required to service the payload. In a communications satellite, the equipment which provides the connecting link between the satellite s transmit and receive antennas is referred to as the transponder. The transponder forms one of the main sections of the payload, the other being the antenna subsystems. In this chapter the main characteristics of certain bus systems and payloads are described. 7.2 The Power Supply The primary electrical power for operating the electronic equipment is obtained from solar cells. Individual cells can generate only small amounts of power, and therefore, arrays of cells in series-parallel connection are required. Figure 7.1 shows the solar cell panels for the HS 376 satellite

The HS 376 satellite. (Courtesy of Hughes Aircraft Company Space and Communications Group.)

manufactured by Hughes Space and Communications Company. The spacecraft is 216 cm in diameter and 660 cm long when fully deployed in orbit. During the launch sequence, the outer cylinder is telescoped over the inner one, to reduce the overall length. Only the outer panel generates electrical power during this phase. In geostationary orbit the telescoped panel is fully extended so that both are exposed to sunlight. At the beginning of life, the panels produce 940 W dc power, which may drop to 760 W at the end of 10 years. During eclipse, power is provided by two nickel-cadmium (Ni-Cd) long-life batteries, which will deliver 830 W. At the end of life, battery recharge time is less than 16 h. The HS 376 spacecraft is a spin-stabilized spacecraft (the gyroscopic effect of the spin is used for mechanical orientational stability, as

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