AERODYNAMIC CONTROL METHOD OF AIRCRAFT Russian patent published in 2019 - IPC B64C13/00 

FIELD: aircraft control.

SUBSTANCE: invention relates to aerodynamic control of technical objects, mainly small-size aircrafts, flying with maneuvering at small angles of attack and sliding (for example, on straight or ballistic trajectories). For aerodynamic control of aircraft (1), air flow of cantilevers (2) is periodically extended into air stream flowing over the aircraft with their subsequent heating to initial position. At that, cantilevers (2) are arranged in aircraft (1) fuselage symmetrically to its pitch plane. Extending each console (2) is performed by 10…100 % of its span with frequency of input into air flow of up to 200 Hz. Console (2) cross-section is provided with configuration of flat plate or aerodynamic profile. On aircraft (1) there are at least two pairs of consoles (2). Console (2) of each pair is unfolded until their average aerodynamic chords (ACC) angle ±(0.5…45) degrees relative to the plane of symmetry of the pair parallel to aircraft longitudinal axis. At least two cantilevers (2) are simultaneously introduced into the air flow that flows around the aircraft.

EFFECT: efficient aerodynamic control of aircraft in "relay" mode without speed losses at intensive standard operation and with possibility of arrangement of aerodynamic steering wheels not on planes, and in fuselage, more dense in comparison with traditional schemes of folding aerodynamic rudders configuration, smaller structural complexity and power consumption of drives, absence of specialized systems of opening (including synchronous) and fixation of rudder cantilevers, convenience of sealing (for example, film ring), increased overall reliability during storage and operation.

9 cl, 7 dwg