The acoustic loads arising during the operation of the launch vehicle are sources of in-tense vibration of its components. Basically these loads are caused by such factors as the propulsion system operation during the launch vehicle start and by oscillatory processes in a turbulent boundary layer during the launch vehicle flight. In this regard, industry normative documentation prescribes evaluating dynamic tests of the launch vehicles and autonomous tests of rocket and space equipment.These tests confirm the dynamic strength and performance of launch vehicle components. This paper presents the results of the vibroacoustic loads analysis for the dry compartments of the mid-range launch vehicle currently being designed, depending on their construction, the attachments weight and the external load, which was set both in the form of acoustic load when solving a coherent elastic and acoustic task, and in the form of harmonic pressure, equivalent to acoustic.
Effect of Surface Pressure Integration Methodology on Launch Vehicle Buffet Forcing Functions