Figure 10. Vibration tests, antenna mounting component vibration loads applied in X, Y and Z axis directions, mass dummy simulators attached to spacecraft component interfaces. Figure 11. Sine and random vibration tests sequences. CONCLUSIONS FEM dynamic analysis models were correlated with the results of the vibration tests, mode frequency, damping and response linearity data gathered in the vibration tests. The part survived all tests, and showed a close correlation between predicted and measured eigenmode frequencies. www. sampe.org The major focus of the work was on design of lattice type structures, this configuration was selected for it's potential to achieve low density and hence lightweight structural components, with high freedom to optimised individual parameters so that typical spacecraft requirements NOVEMBER/DECEMBER 2021 | SAMPE JOURNAL | 53http://www.sampe.org