The development and experimental verification of solar array in folded configuration dynamic finite element model with taking into account an air environment

During launcher’s take-off, spacecraft and its equipment units are subjected to intensive vibration and acoustic loads. The structure analysis of equipment that is characterized by small mass and big surface square of some structure elements (in particular, solar arrays in folded configuration) to such type loads is very actual and carried out by many aerospace companies. The aim of this study is development and experimental verification of spacecraft solar array in folded configuration dynamic finite element model with taking into account an air environment action. Realization of the mentioned aim has been made based on the one of spacecraft’s solar array that has been developed by RSC Energia. Short description of solar array mathematic (dynamic) model is presented. The modelling is realized with taking into account environmental air action. Dynamic model verification was implemented based on frequency response functions determined under solar array (in folded configuration) vibration strength tests which was a part of general qualification testing program. The model developed is dedicated for making loads calculations for low frequency range up to 100 Hz. Using the calculation results and experimental data comparison, the analysis has been implemented and corresponding conclusions about air environment influence on solar array structure’s dynamic parameters has been made.