SYSTEM TO MEASURE HELICOPTER FLIGHT LOW SPEEDS Russian patent published in 2011 - IPC G01P5/00 

FIELD: physics.

SUBSTANCE: proposed system comprises fixed spherical body mounted on fuselage in rotor vortex column zone with rotors axis directed upward in plane parallel with helicopter axis of symmetry. Intake orifices of full pressure on vortex column incoming airflow with built-in flow braking temperature receiver is arranged on top surface of said spherical body. Intake orifices of pressure defining angular position of vortex column in said orthogonal planes are made in symmetry with spherical body axis in planes parallel to helicopter axis of symmetry. Intake orifices of static pressure of resultant vortex column incoming airflow are made in yaw plane orthogonal with two said planes on spherical body surface along circumference. Said pressure and temperature receivers are connected to inputs of pneumoelectric transducers with their outputs connected via multiplexer or ADC to microprocessor to compute three components of true air speed vector, its modulus, angles of attack and gliding at low or almost-zero speeds.

EFFECT: simplified design, lower weight and smaller sizes, higher accuracy.

4 cl, 6 dwg