METHOD FOR BOUNDARY LAYER CONTROL AT AIRCRAFT SURFACE AND DEVICE FOR ITS IMPLEMENTATION Russian patent published in 2010 - IPC B64C21/00 B82B1/00 B61B7/00 

FIELD: air transport.

SUBSTANCE: method includes impulse action on boundary layer, registration of flow conditions, regulation of frequency and amplitude impact on boundary layer in real time. Action on boundary layer and registration of flow conditions is made by elements performed as nano- or microtubes at aircraft surface. Action on boundary layer is made in pulse-periodic thermal mode. The device contains elements located at aircraft surface that act on boundary layer and register flow conditions and parametre management system acting on boundary layer in real time. Action elements and registration of flow conditions are made as mass of nano- and microtubes oriented at the base surface under angle to flux within range of 0≤β≤180°, where β is an angle between main flow and tubes. Tubes are located at the base surface by pairs in rows at current lines. One of the tube in a pair is a generator with pulse periodic thermal impact, the other is a registering sensor of boundary layer parameters.

EFFECT: increase in range of frequency acting on flow.

3 cl, 4 dwg