Abstract
An analytical relationship is derived between the reliability of the on-board power section of communication satellite systems and the effective isotropic radiated power requirement. The latter plays a key role in system design, yielding a direct impact on transmitter configuration and technological features, as well as on the critical compromise between transmitter and antenna specifications. Through the proposed approach, the impact of antenna complexity on the payload reliability is also evaluated. The analysis has been oriented to a design methodology of satellite payloads able to account for reliability constraints in a very early stage of system assessment. The methodology has been applied to a feasible satellite system. The achieved results confirm the usefulness and the potential of the approach. Nomenclature F^ (t) = distribution function of X(/) GA = antenna gain G^p = power gain of the ith amplifier devices 7 = dc voltage of the ith amplifier X(l) = time to failure (or life length) of the ith amplifier
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