RU2013110971A - METHOD FOR MEASURING AN ANGLE OF AN Aircraft PITCH AND RADIO NAVIGATION SYSTEM FOR ITS IMPLEMENTATION - Google Patents

Abstract

1. A method of measuring the pitch angle of an aircraft while it is moving in a known direction, characterized in that horizontally linearly polarized electromagnetic waves are emitted from a point with known coordinates, the electric field vector of which coincides with the horizontal plane, on board the aircraft, receiving antenna, axis of symmetry which is perpendicular to the direction of movement of the aircraft, receives electromagnetic waves in its own in-phase circular polarization basis, e whose unit vectors correspond to waves with left and right circular polarizations, the electric vectors of which at time t = 0 coincide with the direction of the electric field vector, divide the received electromagnetic waves into two components of the left and right directions of rotation of the electric field vector, orthogonally polarized, measure the difference phases between them Δφ, calculate the pitch angle ξ between the longitudinal axis of the aircraft and the horizontal plane according to the formula:, where Δ φ = φ-φ is the phase difference between orthogonally circularly polarized components of the left and right directions of rotation (in degrees), + ξ is the positive pitch angle when the longitudinal axis of the aircraft is above the horizontal plane, -ξ is the negative pitch angle when the longitudinal axis of the aircraft the apparatus is below the horizontal plane. 2. A radio navigation system for measuring the pitch angle of an aircraft, characterized in that a transmitter is located at a point with known coordinates, the output of which is

Claims (2)

1. A method of measuring the pitch angle of an aircraft when it moves in a known direction, characterized in that horizontally linearly polarized electromagnetic waves, an electric field vector, are emitted from a point with known coordinates $$\dot{\overrightarrow{E}}$$

which coincides with the horizontal plane on board the aircraft, the receiving antenna, the axis of symmetry of which is perpendicular to the direction of movement of the aircraft, receives electromagnetic waves in its own in-phase circular polarization basis, the unit vectors of which correspond to waves with left and right circular polarizations, the electric vectors of which at the moment time t = 0 coincide with the direction of the electric field vector $$\overrightarrow{E}$$

, divide the received electromagnetic waves into two components of the left orthogonally polarized in a circle $${\overrightarrow{E}}_L$$

and right $${\overrightarrow{E}}_R$$

directions of rotation of the electric field vector $$\overrightarrow{E}$$

, measure the phase difference between them Δφ _LR , calculate the pitch angle ξ between the longitudinal axis of the aircraft and the horizontal plane according to the formula: $$\xi \left[gR\mathrm{but}d\right]=\pm \frac{\Delta {\varphi }_{LR}}{2}\left[gR\mathrm{but}d\right]$$

, where Δφ _LR = φ _L -φ _R is the phase difference between the components of the left orthogonally polarized in a circle $${\overrightarrow{E}}_L$$

and right $${\overrightarrow{E}}_R$$

directions of rotation (in degrees), + ξ is the positive pitch angle when the longitudinal axis of the aircraft is above the horizontal plane, -ξ is the negative pitch angle when the longitudinal axis of the aircraft is below the horizontal plane. 2. A radio navigation system for measuring the pitch angle of an aircraft, characterized in that at a point with known coordinates there is a transmitter whose output is connected to the input of the transmitting antenna and a receiving antenna located on board the aircraft, the output of which is connected to the input of the circular waveguide section with built-in a quarter-wave phase plate, the output of which is connected to the input of the linear polarizing separator, two outputs of which are connected to the corresponding two inputs of the phase angle a discriminator whose output is connected to the indicator input, the scale of which is calibrated in degrees of the pitch angle of the aircraft, and the transmitting antenna is made in the form of a weakly directed horizontal speaker with a horizontal intrinsic polarization, the electric field vector of the emitted horizontally linearly polarized electromagnetic waves coincides with the horizontal plane , the receiving antenna is made in the form of a round horn, the axis of symmetry of which is perpendicular to the direction of motion of the aircraft, a quarter-phase plate is oriented at -45 ° to a broad wall of a rectangular waveguide one of the arms of the linear polarization separator, and the linear polarization separator is oriented so that its own unit vectors coincide with the vertical and longitudinal axes of the aircraft respectively.