Abstract
The increasing size and complexity of Space Launch Vehicles (SLVs) have led to higher random vibration requirements for spacecraft instruments and electronic components. This paper examines the protection of vibration-sensitive electrical, electronic, and electromechanical (EEE) parts on the Interstellar Mapping Acceleration Probe (IMAP) mission from acceleration loads experienced by SpaceX’s Falcon 9 LV. A finite element model of the Power Distribution Unit (PDU) is presented, revealing acceleration responses of critical EEE parts exceeding vendor test levels. Through modeling, simulation, and hardware correlation, a notched test profile is derived to attenuate component responses while meeting specific requirements. The resulting Protoflight test profile for the flight PDU demonstrated no mechanical or electrical anomalies during testing. This research provides insights into detecting and mitigating high acceleration responses in EEE parts for future space missions utilizing larger SLVs or operating in high random vibration environments.
