Model and finite element methods for studing insulating lining of space module compartments

At design of the space-rocket equipment the prediction problem of acoustic action on elements of the launch vehicle design and payload. The sources of such impact are the engines operating at the start and the incoming air flow acting on the launch vehicle at the start and on the active part of the flight in the earth's atmosphere. However, the solution of the problem, complications of the impossibility of testing in bench conditions. Check the adequacy of the selection process only when the launch vehicle. Therefore, it is important to develop a methodology for calculating the minimum sound insulation based on the physical parameters of the material and the geometric parameters of the structures. The calculation of these parameters was carried out on models of structures, in connection with which the proposed approach was called model. The simulation is carried out by the finite element method while simplifying the initial structure to a similar rigidity. The results were compared with experimental data.