RU2593424C1 - Integrated system of backup devices and method for calibrating magnetic field sensor of integrated system of backup devices - Google Patents

Abstract

FIELD: measuring systems.

SUBSTANCE: invention relates to systems for measurement and indication, and can be applied to systems, which provide pilotage of aircraft (AC) in case of failure of main pilotage and navigation systems. For this purpose, device for entering and selection of deviation coefficients is additionally introduced into integrated system of backup devices. At that, magnetic field sensor calibration is executed, wherefrom deviation coefficients are determined for perturbed of magnetic field independent useful load objects.

EFFECT: technical result is increase of accuracy.

2 cl, 1 dwg

Description

The invention relates to measurement and display systems for piloting aircraft in the event of a failure of the main navigation and navigation systems.

A well-known integrated system of backup devices containing a block of primary information sensors, a signal processing and conversion device, a calculator, a spatial orientation module, an LCD indicator, a magnetic probe based on an algorithmic method of writing off the deviation error [1].

The disadvantage of this system is the low accuracy of measuring the magnetic course, due to an imperfect method of writing off the deviation error of the magnetic course, not taking into account the change in the recorded payload, which has its own perturbing magnetic field.

Closest to the claimed invention is an integrated system of backup devices containing a block of inertial information sensors, a liquid crystal screen, a magnetic field sensor (DMF) with compensation windings, and a method of eliminating magnetic deviation, which consists in calculating the coefficients characterizing the magnitude of the disturbing magnetic field [2].

The disadvantage of this system, as well as the method it implements, is the low accuracy of measuring the magnetic course when the considered payload has its own perturbing magnetic field, since the stationary magnetic field is total and consists of the perturbing magnetic field of the aircraft itself, the perturbing magnetic fields of several independent objects useful loads, as well as disturbing fields of electric communication lines and conductors with current.

The claimed invention is aimed at improving the accuracy of an integrated system of backup devices by taking into account deviation coefficients characterizing changes in the recorded payload, which has its own perturbing magnetic field.

The problem is solved due to the fact that in the integrated system of backup devices of the aircraft, made in the form of a separate block, containing a block of inertial sensors, sensors of full and static pressure, a magnetic field sensor connected through signal processing and conversion devices with a computer, a device for writing off the deviation error with a memory, the input of which is connected to a magnetic field sensor, and the output to a computer, a liquid crystal indicator, an operating mode control device containing an element s preset input rate barokorrektsii specified height, made in the form of functional knobs, the invention further introduced a device for entering and selecting compass deviation coefficients, whose input is connected to the operation mode control unit, and an output connected to the calculator.

In a method for calibrating a magnetic field sensor of an integrated system of backup devices, which consists in determining calibration coefficients to exclude the influence of a disturbing magnetic field when calculating the magnetic course of an aircraft, according to the invention, during the calibration, deviation coefficients characterizing the magnitude of the disturbing magnetic field of the aircraft itself are determined, then the deviation coefficients of the disturbing magnetic fields arising in the presence or absence of several independent objects on an aircraft loads having their own perturbing magnetic fields, after which they determine the coefficients of the total perturbing magnetic field of the aircraft with the installed payload, which during the flight is block or whole separated from the aircraft, select the appropriate deviation coefficients and compensate for the changed disturbing magnetic field.

A distinctive feature of the proposed integrated system of backup aircraft devices is the introduction of a device for input and selection of deviation coefficients designed to compensate for the external disturbing magnetic field that changes during the flight of the aircraft during separation of the installed payload, which has its own perturbing magnetic fields, which improves the accuracy of measuring the aircraft’s magnetic course.

Distinctive features of the proposed method for calibrating a magnetic field sensor are the determination of deviation coefficients characterizing the magnitude of the disturbing magnetic field of the aircraft itself, the determination of the deviation coefficients of the disturbing magnetic fields arising in the presence or absence of several independent payload objects on the aircraft having their own disturbing magnetic fields, the determination of the coefficients of the total disturbing magnetic field of the aircraft with a set payload during flight the whole or partially detachable from the aircraft, as well as the selection of the appropriate deviation coefficients and compensation of the changed perturbing magnetic field, which also provides an increase in the accuracy of measuring the magnetic course of the aircraft.

In FIG. 1 is a diagram of a system comprising a sensor (1) full pressure, a sensor (2) static pressure, a device (3) for processing and converting signals, a computer (4), a module (5) for spatial orientation, an LCD indicator (6), DMP ( 7), a device (8) for controlling operating modes, a krenoscope (9), a photosensor (10), a device (11) for compensating the systematic component of the zero offset of the inertial sensors of the spatial orientation module (5), a device (12) with memory, designed to write off the deviation errors, integrated control system (13), a device (14) for input and selection of deviation coefficients, a device (15) for controlling operation modes [3].

A device (14) for input and selection of deviation coefficients is connected by its input to the device (15) for controlling operating modes, and by an output to a computer (4). The input of the device (14) for input and selection of deviation coefficients also receives signals from the central computer of the aircraft in automatic mode.

The claimed integrated system of backup devices operates in the "hot" backup mode and provides autonomous measurement of roll angles, pitch and gyromagnetic course, as well as aerobatic parameters: instrument speed V _CR , true speed V _IST , absolute height N _abs , relative height N _rel , vertical speed V _in , outdoor temperature T _article , number M (Mach).

The gyromagnetic course is formed according to the DMF information, the data from which are supplied to the calculator (4), where the gyro rate correction process is carried out, calculated from information from the angular velocity sensors of the spatial orientation module (5). The DMF provides information on the magnitude of the Earth's magnetic field along three orthogonal axes, however, due to the presence of soft and magnetically hard materials or conductors with current, magnetic deviation occurs in the area of the DMF installation.

The integrated system of backup devices and the calibration method of the magnetic field sensor of the integrated system of backup devices operate as follows.

First, a disturbing magnetic field caused by the influence of aircraft materials and electric communication lines is calculated, for which the aircraft on which the DMF is installed, in working condition rotate 360 ° around the vertical axis, during rotation, deviation coefficients are calculated, which are stored in the device memory (12) write-off of deviation error.

Then, the perturbing magnetic field is calculated, caused by the influence of the aircraft materials and electric communication lines, as well as by the presence of some object having its own perturbing magnetic field, for which the aircraft are also rotated 360 ° around the vertical axis in the working state, and the deviation coefficients are calculated during rotation, which enter into the memory of the device (12) the write-off of the deviation error.

Then perturbing magnetic fields are calculated, caused by the influence of aircraft materials and electric communication lines, as well as the influence of objects having their own perturbing magnetic fields, sequentially implementing combinations of the presence or absence of these objects on the aircraft, and in the working state they rotate the aircraft 360 ° around the vertical axis, in the process of rotation, deviation coefficients are calculated, which are recorded in the memory of the device (12) to write off the deviation error.

After that, a perturbing magnetic field is calculated, caused by the influence of aircraft materials and electric communication lines, as well as all independent objects that have their own perturbing magnetic fields, for which the aircraft in working condition are also rotated 360 ° around the vertical axis, in the process of rotation, deviation coefficients are calculated, which are recorded in the memory of the device (12) to write off the deviation error.

Subsequently, during the flight of the aircraft, when separating some objects, the perturbing magnetic field changes. Using signals from the central computer of the aircraft, arriving in automatic mode, or manually using the input device of the LCD indicator, the selection and input of deviation coefficients corresponding to a certain mode of presence or absence of independent payload objects on the aircraft and designed to compensate for the disturbing magnetic field are made.

Application of the proposed method for calibrating a magnetic field sensor improves the accuracy of measuring the course of an aircraft in flight.

Information sources:

1. RF patent No. 2386927, IPC G01C 21/00, publ. 2009 (prototype).

2. RF patent No. 2469275, IPC G01C 23/00, publ. 12/10/2012

3. RF patent №2337315, IPC G1C 21/00, publ. 10/27/2008

Claims (2)

1. The integrated system of reserve devices of the aircraft (LA), made in the form of a separate block, containing a block of inertial sensors, sensors of full and static pressure, a magnetic field sensor (DMF), connected through signal processing and conversion devices with a computer, a device for writing off the deviation error with a memory, the input of which is connected to the DMF, and the output to the computer, a liquid crystal indicator, an operating mode control device containing input elements for a given course, barocorrection Specified height, made in the form of functional knobs, characterized in that it additionally introduced a device for entering and selecting compass deviation coefficients whose input is connected to the operation mode control unit, and an output connected to the calculator. 2. A method of calibrating a magnetic field sensor of an integrated system of backup aircraft instruments, which consists in determining calibration coefficients to exclude the influence of a disturbing magnetic field in calculating the magnetic course of an aircraft, characterized in that during the calibration, deviation coefficients characterizing the magnitude of the disturbing magnetic field of the aircraft itself are determined, then determine the deviation coefficients of disturbing magnetic fields arising in the presence or absence of several independent objects on the aircraft Loading the having own perturbing magnetic fields, after which the coefficients of the sum of the perturbing magnetic field installed aircraft payload, which subsequently during flight blockwise or completely separated from the aircraft, the respective selected coefficients Deviation altered and compensates the disturbing magnetic field.

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