Comparative calculation of the low frequency component of dynamic overloads for onboard space vehicle equipment

In this article, a comparative analysis of the calculation of the dynamic overload acting in the center of mass of the device (unit) of the spacecraft in a particular case of operation is carried out. Operational overloads obtained from maximum absolute accelerations are taken into account in the design of equipment mounts. The safety factor used in the strength calculations of the brackets directly depends on the accuracy of the determination of loads. Specialists of JSC «RCC» Progress» wrote a program to determine the maximum absolute loads in the center of mass of the device (unit). The work of the program is presented on the example of calculating the load on the Earth-orientation device of the small spacecraft «Aist-2D». In addition, the authors of the article calculated the considered structure in the program for interactive creation and maintenance of FEMAP with NX Nastran. As an object of study, a ready-made verified finite element model of the spacecraft was used. As a result of the solution by two methods, quantitative indicators of the physical quantity realized in the node are determined as a result of the impact of dynamic acceleration on the object. The results showed high convergence, which confirms the correctness of the program.