English (United Kingdom)

https://curated-unify.zendy.io/wp-json/zendy-region/v1/featured_content/oa?rat=en

https://curated-unify.zendy.io/wp-json/zendy-region/v1/highlighted_journal/

Global: Zendy Plus annual

Presents the access of premium content as premium feature

Premium Content

Presents the keyphrase highlighting as premium feature

Keyphrase Highlighting

Presents the summarisation as premium feature

Summarisation

Insights

Presents the pdf analysis as premium feature

PDF Analysis

Presents the zaia usage as premium feature

ZAIA

Global: Zendy Plus monthly

Global: Zendy Tools annual

Global: Zendy Tools monthly

Global: Zendy Free Plan

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 thisstudy, 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 andanalyzed. The dose (in Gy) as a function of particle flux and deposited energywas also determined. Predictions of their possible effects on space systemoperations and life-span were made, especially as values exceeded certainthreshold (limit). Using GOES 11 acquired data for 3 months, estimations and/orcalculations were made to determine the risk and safe period of a satellite inthe geosynchronous orbit. Under certain space radiation environmentalconditions (without mitigation of any sort), a spacecraft whose body is 20 mmthick and with Al alloy casing, was theoretically estimated to have a safeperiod of about 3 years and risk period of about 29 years (due to totalionizing dose) within which it would experience a catastrophic failure.

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