Structural reliability prediction of an All-sky Electrostatic Analyzer for lunar mission under launch and transport-induced vibrations

Abstract This study evaluates the structural reliability and dynamic stability of an All-sky Electrostatic Analyzer (A-ESA) subjected to launch and transport-induced vibrations. A high-fidelity finite element model was developed to perform modal, harmonic response, Shock Response Spectrum (SRS), and random vibration analyses, with results validated through tri-axial sine sweep vibration tests. Modal analysis shows first-mode natural frequencies along the X , Y , and Z axes exceeding the 150 Hz design threshold, indicating adequate high-frequency stiffness. Harmonic analysis reveals resonances near 190 Hz on the X and Y axes, and a torsional mode at 1125 Hz on the Z -axis with stress concentration on the mid-section PCB. SRS analysis indicates Z-axis excitation produces a peak von Mises stress of 343.33 MPa, exceeding the yield strengths of aluminum alloy and PCB materials, suggesting failure risk. Random vibration results show Z -axis excitation yields 0.4424 mm deformation and 278.13 MPa peak stress, indicating potential fatigue damage. The validated finite element model provides reliable predictive capability and supports structural reinforcement strategies for future designs.