LABEL SENSOR FOR AERODYNAMIC ANGLE AND TRUE AIR SPEED Russian patent published in 2016 - IPC G01P5/00 G01C1/12 

FIELD: measuring equipment.

SUBSTANCE: device comprises a generator of ion labels, channel recording ion labels in the form of a system of receiving electrodes arranged in circle with center at the point of generation of ion labels, and unit of preamplifiers, measuring circuit in the form of a channel for determining work sector, which is rough reading channel, channel for accurate measurement of angle in the working sector and true air speed channel connected to the input of computing device, whose outputs are digital outputs intended for aerodynamic angle and true air speed. On the metal plate-mask of system of receiving electrodes there is a hole, i.e. receiver of static pressure of incoming air flow, which is connected by pneumatic channel to the input of absolute pressure sensor which output is connected to the input of computing device. Computing device is made in the form of a computer realising both algorithms for determination of aerodynamic angle and true air speed and algorithms for determination of other altitude-speed parameters of motion relative to ambient air medium according to the equations:

where i - is the number of work sector of rough channel containing an ion label; α_o - angle covering work sector of the rough reading channel intended for aerodynamic angle (when α_o = 90°); Asinα_i and Acosα_i - values of sinusoidal and co-sinusoidal signals recorded by channel of the precise angle reading in the i-th sector; R - is distance from the point of generation of ion labels to the circle with receiving electrodes; τ_ν -period of time the ion label travels the distance from the point of generation of ion labels to the circle with receiving electrodes; α and (V)_B, h, ρ_H, V_pr, m is determined by altitude-speed parameters; P₀ = 101,325 Pa = 760 mmHg and T₀ = 288.15 K is the average absolute pressure and the average absolute temperature of standard atmosphere at H = 0; τ = 0.0065 K/m is a temperature gradient, determining change in absolute temperature T_H at change of height H; R = 29.27125 m/K is a gas constant; k = 1.4 is an adiabat index air; ρ₀ = 0.125 kgf²/m⁴ - mass density of air at the height h = 0.

EFFECT: invention relates to devices for measuring value (module) and direction angle (aerodynamic angle) of true air speed vector, as well as other aircraft altitude and speed parameters, determining movement relative to ambient air.

1 cl, 4 dwg