Determination of the Stopping Power and Failure-time of Spacecraft Components due to Proton Interaction Using GOES 11 Acquisition Data

Abstract: 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.