ACOUSTICS TEST OF A SMALL SPACECRAFT

摘要

A protoqual acoustic test of a small spacecraft was performed in a reverberant chamber. It was performed in two steps: low level (-6 dB) run and full level run. The results of low level run indicated response exceedances at two areas with possible component failures at full level run. A Finite Element Model Analysis pointed to the responsible modes. Stiffeners and SMRD Damper Assemblies were designed, fabricated and installed. They were verified by in-situ tap tests. The same low level acoustic test was repeated and showed significant improvement. The full level test was then proceeded with confidence of no structural or component failures. Post functional test of all components verified the spacecraft is functioning well. The combination of testing, analysis, design, and fabrication in an integrated fashion demonstrated the key of success for a cheaper, faster, and better spacecraft test program.