SUPERSONIC CONTROLLED AIR INTAKE Russian patent published in 2013 - IPC F02C7/42 B64D33/02 

FIELD: aircraft engineering.

SUBSTANCE: supersonic controlled air intake comprises inlet representing flow deceleration system, that is, supersonic diffuser 22 consisting of two multistep sweep deceleration wedges 7 and 20 to make dihedral angle, shell ring that also makes dihedral angle. Note here that all edges of inlet are located in one plane, air intake entrance located behind deceleration system, and subsonic diffuser 23 located there behind. Air intake entrance features rectangle- or parallelogram-shape in front view. Number of steps on sweep wedges 7, 20 may disagree as well as their sweep may differ between themselves and from inlet edge. All stages, apart from first one, of one of two multistage sweep wedges 7, 20 may turn about axis located at crossing of first and second stages of said wedge to make moving front panel 11. Subsonic diffuser accommodated moving rear panel 12.

EFFECT: stable operation of engine in all operating conditions.

8 cl, 5 dwg