RU2012152598A - METHOD FOR MEASURING AN ANGLE OF AN Aircraft PITCH AND DEVICE 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 linear orthogonal polarization base whose unit vectors make an angle of -45 ° with the longitudinal and vertical axes of the aircraft, divide the received horizontally linearly polarized electromagnetic waves into two in-phase orthogonally linearly polarized components of the electric field vector, measure their amplitudes A and A respectively, calculate the pitch angle ξ between the longitudinal axis of the aircraft apparatus and the horizontal plane according to the formula, where -ξ is the negative pitch angle of the aircraft when its longitudinal axis finds below the horizontal plane, + ξ is the positive pitch angle of the aircraft when its longitudinal axis is above the horizontal plane, A is the amplitude of the linearly polarized component of the electric field vector, A is the amplitude of the linearly polarized component of the electric field vector. 2. A device 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 connected to the input of the transmitting antenna, and

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 linear orthogonal polarization basis, the unit vectors of which make an angle of -45 ° with the longitudinal and vertical axes of the aircraft, are divided received horizontally linearly polarized electromagnetic waves into two in-phase orthogonally linearly polarized components $${\dot{\overrightarrow{E}}}_x$$

and $${\dot{\overrightarrow{E}}}_y$$

electric field vector $$\dot{\overrightarrow{E}}$$

, their amplitudes A _x and A _y are measured, respectively, the pitch angle ξ between the longitudinal axis of the aircraft and the horizontal plane is calculated by the formula $$\xi \left[gR\mathrm{but}d.\right]=\mp \left({45}^{\circ }-arctg\frac{A_y}{A_x}\right)$$

, where -ξ is the negative pitch angle of the aircraft when its longitudinal axis is below the horizontal plane, + ξ is the positive pitch angle of the aircraft when its longitudinal axis is above the horizontal plane, A _x is the amplitude of the linearly polarized component of the electric field vector $${\overrightarrow{E}}_x$$

, A _y is the amplitude of the linearly polarized component of the electric field vector $${\overrightarrow{E}}_y$$

. 2. A device 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 a linear polarizing separator, two outputs are connected to respective inputs of two angular amplitude discriminator, whose output is connected to the input of the calculator, wherein the measured relative amplitude a _y / a _x inphase ort gonal linearly polarized components $${\overrightarrow{E}}_x$$

and $${\overrightarrow{E}}_y$$

electric field vector $$\overrightarrow{E}$$

received horizontally linearly polarized electromagnetic waves, the pitch angle ξ of the aircraft is calculated, and if the ratio A _y / A _x = 1, then the longitudinal axis of the aircraft is in the horizontal plane and the pitch angle ξ = 0 ° if A _y / A _x <1 , the longitudinal axis of the aircraft is above a horizontal plane and this corresponds to a positive pitch angle of the aircraft and ξ> 0 °, if the ratio of the amplitudes of the A _y / A _x> 1, the longitudinal axis of the aircraft is below the horizontal plane and that The appropriate negative pitch angle of the aircraft and ξ <0 °, where the electric field vector $$\dot{\overrightarrow{E}}$$

radiated horizontally linearly polarized electromagnetic waves coincides with the horizontal plane, while the proper polarization of the transmitting antenna is horizontal, the axis of symmetry of the receiving antenna is perpendicular to the direction of movement of the aircraft, and the linear polarizing separator is oriented so that its own unit vectors into which it divides the received electromagnetic waves are an angle of -45 ° with the vertical and longitudinal axes of the aircraft, respectively.