Single Event Effects Test Verification for the Virgin Orbit LauncherOne Vehicle

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,.