  One of the several ways to describe the net effect of charged-particles'
interaction is the rate of energy loss along the particles' path. In this
study, the mass stopping power (Sp) of selected spacecraft composite materials,
through which the particle traverses, its range (R) and the distance (d)
travelled (by the particles) through the materials have been calculated and
analyzed. The dose (in Gy) as a function of particle flux and deposited energy
was also determined. Predictions of their possible effects on space system
operations and life-span were made, especially as values exceeded certain
threshold (limit). Using GOES 11 acquired data for 3 months, estimations and/or
calculations were made to determine the risk and safe period of a satellite in
the geosynchronous orbit. Under certain space radiation environmental
conditions (without mitigation of any sort), a spacecraft whose body is 20 mm
thick and with Al alloy casing, was theoretically estimated to have a safe
period of about 3 years and risk period of about 29 years (due to total
ionizing dose) within which it would experience a catastrophic failure.
