METHOD FOR CONTROL OVER SOUND SHOCK LEVEL FROM AIRCRAFT COMPONENTS

摘要

FIELD: aircraft engineering.SUBSTANCE: claimed process subjecting the flow ahead and nearby aircraft elements to power supply source effects, for example, laser radiation. Intermittently or continuously formed is one local heat feed area in gas medium ahead of aircraft elements for control over its sizes, distance to aircraft elements and temperature of said heat feed area. Note here that aircraft elements are located in cold airflow with structure composed by shock waves from power feed source. Note also that said heat feed area is spaced from aircraft elements so that the latter do not cross the heat trace from said heating area. Front part of aircraft elements gets in either high static pressure area or low pressure area developed in mirror axis which allows the decrease or increase in sound shock in far field.EFFECT: control over sound shock level at ground surface under supersonic flight conditions.5 dwg