METHOD OF SUPERSONIC AIRCRAFT SOUND SHOCK ATTENUATION AND DEVICE FOR ITS IMPLEMENTATION Russian patent published in 2024 - IPC B64C30/00 B64C21/02 G10K11/16 

FIELD: aviation.

SUBSTANCE: invention relates to methods and devices for reducing the level of acoustic shock of an aircraft. Proposed method comprises forming perforated sections on aircraft skin. Attenuation of sound shock caused by volume effect is achieved by active action on equivalent body of revolution by diverting a certain portion of the incident flow under the skin through perforations in the front part of the fuselage, by discharging the flow through perforations in the rear part of the aircraft. Distribution of perforation zones and parameters of the pressure conversion system is carried out with coordination with the general layout of the aircraft. Flow discharge and discharge are controlled through perforations by changing pressure in accordance with the specified program in receivers located under aircraft skin. At the same time coordination of perforation zones distribution and pressure conversion system parameters is carried out using aircraft model with installed system of perforations and air removal for active action on equivalent body of revolution, by blowing the model in a high-speed wind tunnel and evaluating the efficiency of the perforation and air removal system. In the process of blowing, the pressure field around the installed model of the aircraft is measured.

EFFECT: reduced intensity of sound impact generated by aircraft fuselage, id est due to volume.

2 cl, 3 dwg