The comparative analysis of experimental methods of spacecraft structure dynamic finite element models verification

RSC «Energia»’s experience of spacecraft development shows that the main critical loading events occur on ascent flight together with launch vehicle. The validity of internal loads for spacecraft structural elements during ascent flight (which are determined by coupled loads analysis) to a large extent depends on the accuracy of spacecraft dynamic finite element models. Updating of dynamic model parameters is implemented after getting the modal survey test results. It is presented the analysis of two the most frequently used experimental methods of spacecraft structure modal testing: under oscillations been creating by local force of shaker rod and under base driven kinematic excitation by stationary vibro-shaker. It has been stated the advantages and deficiencies of both methods mentioned above and given the recommendations of their applicability for spacecraft development stages.