RU2467288C1 - Unit of orientation of navigation instrumentation - Google Patents

Abstract

FIELD: measurement equipment.

SUBSTANCE: unit of orientation of navigation instrumentation relates to aviation equipment, namely, to units of orientation of airplanes and helicopters. The device differs by the fact that it additionally contains the second inertial measurement unit, the first and second buffers, the first and second isolation units connected with their inlets to outlets of the first and second inertial measurement units, accordingly, and with outlets - to an inlet of a magnetometer, the outlet of which via the first and second buffers is connected to the inlets of the first and second inertial measurement units, accordingly. The proposed device is used in a heading and vertical sensor.

EFFECT: increased reliability and accuracy of airplanes and helicopters piloting.

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Description

The invention relates to aircraft, in particular to orientation blocks for aircraft and helicopters.

Known unit orientation of the course system [1], containing a gyrocompass, analog-to-digital Converter, a computer and an induction magnetic sensor.

The disadvantage of this device is the ambiguity of the issued parameters by various induction magnetic sensors of each of the two orientation units installed on the same plane.

Known orientation unit [2], containing an inertial measuring unit with its constituent primary information sensors, a transducer and a magnetometer.

The disadvantage of this device is the ambiguity of the issued parameters by various magnetometers of each of the two orientation units installed on the same plane.

The claimed invention is aimed at improving the reliability and accuracy of piloting aircraft and helicopters.

The task is achieved in that in the orientation block of the flight-navigation complex containing the first inertial measuring unit and magnetometer, according to the invention, a second inertial measuring unit, first and second buffers, first and second decoupling nodes connected by inputs to the outputs of the first and second inertial measuring blocks, respectively, and outputs to the input of the magnetometer, the output of which through the first and second buffers is connected to the inputs of the first and second inertial meters GOVERNMENTAL blocks respectively.

Significant differences of the proposed device include the introduction of a second inertial measuring unit, connected together with the first inertial measuring unit through decoupling nodes and buffers to the magnetometer.

When such a device is installed on board an airplane or helicopter, piloting is provided by two pilots, and information on the magnetic course comes from one magnetometer to both inertial measuring units simultaneously, making the readings of both instruments unambiguous, which increases the accuracy of piloting.

The present invention is illustrated in the drawing, which shows a structural diagram of a device containing a first inertial measuring unit 1, a magnetometer 2, a second inertial measuring unit 3, a first buffer 4, a second buffer 5, a first decoupling unit 6, a second decoupling unit 7.

The outputs of the first and second inertial measuring units 1 and 3 are connected to the inputs of the first and second isolation nodes 6 and 7, the outputs of which are connected to the input of the magnetometer 2, the output of which is connected through the first and second buffers 4, 5 to the inputs of the first and second inertial measuring units 1 , 3.

The device operates as follows.

During the flight of an airplane or a helicopter, inertial measuring units 1, 3 process the information of their own primary information sensors and an external magnetometer 2. When two orientation units are installed on board an aircraft, the magnetometers included in them must be spaced apart to avoid distortion of the Earth’s magnetic field, therefore it will have place the ambiguity of their output parameters. According to the invention, one common magnetometer 2 is used for two inertial measuring units 1 and 3, while the supply voltage from them is supplied to the magnetometer 2 through the first and second isolation nodes 6 and 7, and the useful signal of the magnetometer 2 is supplied to the inertial measuring units 1, 3 through buffers 4, 5 - this is done so that in case of failure of one of the inertial measuring units 1, 3, the power is supplied from the working unit, and the faulty unit does not affect the output signal of magnetometer 2.

Thus, the use of one magnetometer 2 in conjunction with two inertial measuring units 1, 3 ensures the unambiguity of the parameters of the orientation unit and improves the accuracy of piloting.

The proposed device is used in the sensor heading and vertical.

Information sources

1 US Patent No. 4347730, cl. 73 / 1E, 1982

2 Anniversary XV St. Petersburg International Conference on Integrated Navigation Systems. Collection of materials. St. Petersburg, 2008, p. 263. Compensation for magnetic deviation of an integrated backup instrument system. V.M. Samoylov, D.V. Svyazhin (the closest analogue).

Claims (1)

The orientation unit of the flight-navigation complex containing the first inertial measuring unit and a magnetometer, characterized in that it additionally includes a second inertial measuring unit, first and second buffers, first and second decoupling units connected by inputs to the outputs of the first and second inertial measuring units, respectively and the outputs to the input of the magnetometer, the output of which through the first and second buffers is connected to the inputs of the first and second inertial measuring units, respectively.