RU2013131637A - POLARIZATION-MODULATION METHOD OF RADAR RADAR MEASUREMENT ANGLE OF Aircraft Aircraft and device for its implementation - Google Patents

Abstract

1. The polarization-modulation method of radar measurement of the roll angle of the aircraft during its movement on a passive radar reflector of electromagnetic waves, characterized in that at a point with known coordinates have a passive polarization-anisotropic radar reflector of electromagnetic waves with a horizontal linear intrinsic polarization coinciding with the horizontal plane, passive polarization-anisotropic radar reflection is irradiated from the aircraft A linearly polarized electromagnetic wave, the plane of polarization of which rotates with frequency Ω, receives an electromagnetic wave reflected by a polarization-anisotropic radar reflector, the polarization of which coincides with the polarization of the radiated electromagnetic wave, from the received signal, in a linear orthogonal polarizing basis, single unit vectors which coincide with the transverse and vertical axes of the aircraft, horizontally linearly polarized the component, determine the amplitude of the output signal of the receiver having a logarithmic amplitude characteristic and a linear detector, where C is a constant taking into account the potential of the transmitter, the distance from the transmitter to the polarization-anisotropic radar reflector and vice versa, its effective scattering area (EPR) and receiver sensitivity, the spectral component is extracted from the output signal of the logarithmic receiver at a frequency of 2Ω, its phase φ is measured relative to the doubled angular position of the plane along

Claims (2)

1. The polarization-modulation method of radar measurement of the roll angle of the aircraft during its movement on a passive radar reflector of electromagnetic waves, characterized in that at a point with known coordinates have a passive polarization-anisotropic radar reflector of electromagnetic waves with a horizontal linear intrinsic polarization coinciding with the horizontal plane, passive polarization-anisotropic radar reflection is irradiated from the aircraft A linearly polarized electromagnetic wave, the plane of polarization of which rotates with frequency Ω, receives an electromagnetic wave reflected by a polarization-anisotropic radar reflector, the polarization of which coincides with the polarization of the radiated electromagnetic wave, from the received signal, in a linear orthogonal polarizing basis, single unit vectors which coincide with the transverse and vertical axes of the aircraft, horizontally linearly polarized Ponent, determine the amplitude of the output signal of the receiver having a logarithmic amplitude characteristic and a linear detector, $$E_{\mathrm{at}sx}(\Omega t)=\lg C+\lg \frac{\mathrm{one}}{2}[\mathrm{one}+\cos (2\Omega t\pm 2\gamma )]$$

, where C is a constant taking into account the potential of the transmitter, the distance from the transmitter to the polarization-anisotropic radar reflector and vice versa, its effective scattering area (EPR) and the sensitivity of the receiver, the spectral component at a frequency of 2Ω is extracted from the output signal of the logarithmic receiver, its phase φ _{2Ω is measured} relative to the doubled angular position of the plane of polarization of the emitted electromagnetic wave and determine the angle of heel γ of the aircraft between the transverse axis of the aircraft parata and the horizontal plane according to the formula: $$\gamma [R\mathrm{but}d.]=\pm \frac{{\varphi }_{2\Omega }}{2}[R\mathrm{but}d]$$

, where φ _2Ω is the phase of the spectral component at a frequency of 2Ω (in radians), + γ is the positive angle of heel when the right wing of the aircraft, or its transverse axis is below the horizontal plane, -γ is the negative angle of heel when the right wing of the aircraft, or its transverse axis is above the horizontal plane. 2. A device for measuring the roll angle of an aircraft, characterized in that at a point with known coordinates there is a polarization-anisotropic passive radar reflector of electromagnetic waves with horizontal linear intrinsic polarization, made in the form of a trihedral angular reflector, consisting of three planar mutually perpendicular metal or metallized triangular faces of equal sizes significantly exceeding the wavelength λ = 3.2 cm, in the opening of which the vertical A newly oriented polarization array made of round parallel metal rods (or wires) with a pitch of A = 5 mm and a diameter of B = 0.64 mm and sequentially connected synchronizer, transmitter, antenna switch, linear polarizer arranged on board an aircraft, made in the form of a transition from a rectangular waveguide on a circular waveguide, a polarization plane rotator with a frequency of Ω, made in the form of a section of a circular waveguide with a half-wave plate λ / 2 mounted therein, rotating with a frequency of Ω ₁ = Ω / 2 and the antenna, while the circular waveguide section is mechanically connected using a gear 1: 1 gear with the rotor shaft of a synchronous stepless micromotor and the angular position sensor of a half-wave phase plate made in the form of a selsyn, the axis of which is mechanically connected using a gear with the rotor shaft of the synchronous stepper micromotor, while the control input of the synchronous stepper micromotor is connected to the output of the master oscillator, and the signal output of the angular position sensor is half-wave phase the plate is connected to the input of the balanced detector, and its output is connected to the input of the reference signal generating unit, the second output of the antenna switch is connected to a logarithmic receiver and a temporary selector made in the form of a controlled key, the synchronizer output is also connected to the first input of the tracking range meter, the output the time selector is simultaneously connected to the second input of the tracking range meter, to the input of the automatic gain control unit and to the follower but connected to a peak detector and a bandpass filter, while the output of the tracking range meter is connected to the control input of the time selector, the output of the automatic gain control unit is connected to the control input of the logarithmic receiver, and the output of the bandpass filter is connected to the first input of the phase detector, and its second input is connected to the output of the reference signal generating unit, and the output of the phase detector is connected to the indicator input, the scale of which is calibrated in degrees of the roll angle of the aircraft ata, wherein the center frequency of bandpass filter and a reference signal frequency equal to twice the frequency of rotation of the polarization plane, and the intrinsic polarization of the linear polarizer linear horizontal and coincides with the transverse axis of the aircraft.