Single Event Effects Test Verification for the Virgin Orbit LauncherOne Vehicle

W. Elkman, C. Scoby, Umer Qureshi, Andrew Shirali
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Abstract

This paper describes the SEE (single event effects) design verification approach and proton beam verification test results for the Virgin Orbit LauncherOne (L1) two stage LOX/RP-1 launch system, capable of deploying payloads up to 300kg to 500km Sun Synchronous Orbit (SSO), and deploying payloads up to 500kg to 200km Low Earth Orbit (LEO). [9] Describes the EMI/EMC Control Program tailored from RTCA-DO-160F and MIL-STD-461F. [10] Reports the Electromagnetic Compatibility (EMC) verification procedures and results for LauncherOne,.
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维珍轨道发射一号飞行器单事件效应试验验证
本文描述了维珍轨道发射一号(L1)两级LOX/RP-1发射系统的SEE(单事件效应)设计验证方法和质子束验证测试结果,该发射系统能够部署300公斤至500公里太阳同步轨道(SSO)的有效载荷,以及部署500公斤至200公里低地球轨道(LEO)的有效载荷。[9]描述了根据RTCA-DO-160F和MIL-STD-461F定制的EMI/EMC控制程序。[10]报告LauncherOne的电磁兼容性验证过程和结果。
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