利用GOES 11采集数据确定质子相互作用引起的航天器部件的停止功率和失效时间
Determination of the Stopping Power and Failure-time of Spacecraft Components due to Proton Interaction Using GOES 11 Acquisition Data
摘要：
描述带电粒子相互作用净效应的几种方法之一是沿粒子路径的能量损失率，本文计算和分析了粒子穿过航天器复合材料的质量阻止本领（Sp）、射程（R）和穿过材料的距离（d）。还确定了作为粒子通量和沉积能量的函数的剂量（以Gy计）。预测了它们对航天系统运行和寿命可能产生的影响，特别是当数值超过某一阈值（极限）时。使用GOES 11获得的3个月数据，进行了估计和/或计算，以确定地球同步轨道卫星的风险和安全期。在某些空间辐射环境条件下（不采取任何形式的减缓措施），据理论估计，机身厚度为20毫米、外壳为铝合金的航天器的安全期约为3年，风险期约为29年（由于电离总剂量），在此期间，航天器将发生灾难性故障。
英文摘要：
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.
机构、总结、中文摘要均由AI分析而来，可能存在错误，请以论文正文为准。
