RU2012133593A - METHOD FOR MEASURING AN ANGLE OF AN Aircraft ROLL AND DEVICE FOR ITS IMPLEMENTATION - Google Patents

Abstract

1. A method of measuring the roll angle of an aircraft during its movement to a source of electromagnetic wave radiation, 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, receive electromagnetic waves on board the aircraft in its own in-phase circular polarization basis whose unit vectors correspond to waves with left and right circular polarization, 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 right and left directions of rotation of the electric field vector that are orthogonally polarized, measure the phase difference Δφ between them, calculate the angle of heel γ between the transverse axis the aircraft and the horizontal plane according to the formula, where Δφ = φ-φ is the phase difference between the components orthogonally polarized in a circle, the right evogonapravleniya rotation [degrees], + γ - positive roll angle (right side or transverse axis of the aircraft is below the horizontal plane), - γ - negative roll angle (right wing aircraft or the transverse axis, located above the horizontal plane) .2. A device for measuring the roll angle of an aircraft, characterized in that a transmitter is located at a point with known coordinates, the output of which is connected to the input of a transmitting antenna with horizontal intrinsic polarization and a receiver located on board the aircraft

Claims (2)

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

which coincides with the horizontal plane, receive electromagnetic waves on board the aircraft in their own in-phase circular polarization basis, whose unit vectors correspond to waves with left and right circular polarization, the electric vectors of which at time t = 0 coincide with the direction of the electric field vector $$\overrightarrow{E}$$

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

and left $${\overrightarrow{E}}_L$$

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

, measure the phase difference between them Δφ _RL , calculate the angle of heel γ between the transverse axis of the aircraft and the horizontal plane according to the formula $$\gamma [gR\mathrm{but}d]=\pm \frac{\Delta {\varphi }_{RL}}{2}[gR\mathrm{but}d]$$

, where Δφ _RL = φ _R -φ _L is the phase difference between the orthogonally circularly polarized components, right $${\overrightarrow{E}}_R$$

and left $${\overrightarrow{E}}_L$$

direction of rotation [hail], + γ is the positive angle of heel (the right wing, or the transverse axis of the aircraft, is below the horizontal plane), -γ is the negative angle of heel (the right wing, or the transverse axis of the aircraft, are above the horizontal plane). 2. A device for measuring the roll angle of the aircraft, characterized in that a transmitter is located at a point with known coordinates, the output of which is connected to the input of the transmitting antenna with its own horizontal polarization and a receiving antenna located on board the aircraft, the output of which is connected to the input of the circular waveguide section with a quarter-wave phase plate built into the inside, the output of which is connected to the input of the linear polarizing separator, the two outputs of which are connected to the corresponding the two inputs of the phase angular discriminator, the output of which is connected to the indicator input, the scale of which is calibrated in degrees of the roll angle of the aircraft, the electric field vector of the emitted horizontally linearly polarized electromagnetic waves coincides with the horizontal plane, the quarter-wave phase plate is oriented at an angle of -45 ° to the wide wall of the rectangular waveguide of one of the arms of the linear polarizing separator, and the linear polarizing separator is orient so that its own unit vectors coincide with the vertical and transverse axes of the aircraft, respectively.