RU2441813C2 - Aviation integrated multi-indicator - Google Patents

Abstract

FIELD: aeronautics.

SUBSTANCE: invention relates to electronic devices cockpit information display parameters of the aircraft, airborne equipment, radar situation. Integrated Aviation multifunctional indicator includes liquid crystal display (LCD), sensor unit ZHKE parameters and controls, power actuators, power mode control, power adapter input data and input-output and control information exchange. The control unit is connected to the operation modes of the adapter input-output-control information exchange related command-and-highway information exchange with the adapter information about landforms, the adapter television information, adapter radar meteorological information and the GPU. A graphics processor is connected to the device image smoothing, baseline data block, the block parameters ZHKE sensors and controls, ZHKE, power actuators, trunk and video adapters with a background image information on landforms, television information, radar meteorological information. The indicator device further comprises a measuring aerodynamic parameters, the spatial orientation of the device (gyrovertical) and the device current location, connected to the adapter input-output-control information exchange.

EFFECT: expanded functionality of the cockpit indicator.

1 dwg, 2 dwg

Description

The invention relates to the field of on-board multi-functional indicators, in particular to in-cabin instruments for electronic indication of parameters of an aircraft, on-board equipment, and radar conditions.

Known multi-functional indicator described in the patent of the Russian Federation No. 2181093. This indicator is made on the liquid crystal screen and includes a control unit for operating modes, an information exchange highway, computing modules of the source data base, control of screen devices, forming indicator frames, input-output for managing information exchange, forming inverted indicator frames, synthesizing on-board devices, synthesizing a multifunctional console control, image formation, combined with the aeronautical map of the area, the formation of combined op ponents images.

The disadvantage of the analogue is the limited functionality in the presentation of information on the indicator screen.

The closest analogue is the aviation multifunctional indicator described in the patent of the Russian Federation No. 2287459.

The indicator contains a liquid crystal screen, an operating mode control unit, computing modules of the source data base, input-output-information exchange control, input-output-information exchange control modules, an operating mode control unit connected to an information exchange input-output-control device, an image smoothing device connected by inputs and outputs to the highway of information exchange, adapter of information about the relief of the earth's surface, adapter of television information, adapter for radar meteorological information, a device for combining and superimposing images, which is additionally connected to the LCD with its inputs and outputs, a block of sensors and controls, a block of actuators, and a video line with a graphics processor and a video line for video information with adapters for earth relief, television information, radar weather information, moreover, the image smoothing device is connected to the grap device eskogo processor.

This indicator has advanced functionality compared to the previous counterpart. However, it does not provide for the possibility of autonomous measurement, calculation of the aerometric parameters of the aircraft and its spatial orientation.

The objective of the invention is the creation of an integrated aviation multifunctional indicator, which, in addition to traditional functions, has additional functions of SHS and SINS systems.

The technical result is to expand the functionality of the indicator.

The functionality of the claimed indicator is expanded by introducing additional devices for autonomous measurement and calculating (directly in the indicator) the aerometric parameters of the aircraft, its spatial orientation, current location, deviation of the aircraft from the line of the given path and displaying these parameters on the LCD screen.

This result is achieved in that the aviation multi-function indicator comprising a liquid crystal screen, a block of sensors for parameters of the liquid crystal screen, a block of executive devices, a graphics processor device, an image smoothing device, a source data block, an input / output adapter and information exchange control device, a radar weather information adapter, adapter for radar information of the earth’s surface, adapter for television information, command and information highway Discount exchange, the exchange of video information of the background image line, further comprises a wind measuring device UIAP parameters, spatial orientation device (gyrovertical) UPR and apparatus determine the current location UOTM.

The invention is illustrated by drawings.

Figure 1 presents the structural diagram of the inventive indicator, which indicates:

1 - liquid crystal display LCD,

2 - a block of sensors of parameters of the LCD and DB controls,

3 - block actuators BIU,

4 - device GPU GPU,

5 - control unit operating modes BUR,

6 - adapter input-output-control information exchange AVVU,

7 - block initial data BID,

8 - device smoothing images USI,

9 - highway command and information exchange ICIE,

10 - adapter radar weather information AWP,

11 - adapter information about the relief of the earth's surface ARZ,

12 - ATI television information adapter,

13 - line video of the background image of the IMFI,

14 is a device for measuring aerodynamic parameters UIAP,

15 - device spatial orientation (gyro) UPR,

16 is a device for determining the current location of UOTM.

Figure 2 presents a structural diagram of a device for measuring the aerodynamic parameters of UIAP 14 and its connection with the adapter I / O-control information exchange AVVU 6 (Fig 1.), where it is indicated:

P _p is the total flow pressure;

R _d - static pressure;

T _p - the temperature of the complete deceleration of the flow;

6 - adapter input-output-control information exchange AVVU;

14 is a device for measuring aerodynamic parameters UIAP,

17 - full pressure sensor DD p _p ;

18 - static pressure sensor DD r _article ;

19 is a device for processing and converting UOPS signals.

LCD 1 is implemented on a full-color active-matrix liquid crystal panel.

The sensor block of the parameters of the liquid crystal screen and the DB 2 control elements consists of ambient light photo sensors, LCD 1 temperature sensors, backlight temperature sensors, internal indicator volume temperature sensors, backlight brightness controls and background image brightness controls.

The block of actuators BIU 3 consists of a LED backlight device, an LCD heater 1, forced cooling electric fans.

The GPU 4 GPU device is a computing unit built on the basis of a video graphics processor and an image combining and overlapping device, and is connected by inputs-outputs 1 with the MKIO 9 trunk, inputs 2 with the MVFI 13 trunk, inputs 3 with the BID 7 source data block, inputs outputs 4 with an image smoothing device USI 8, designed to form an array of graphic video data in the LCD 1 format and allowing the formation of superimposed images, for example, a weather image with a course and whether the television information is graphic, as well as combining images from various sources of information and positioning image fragments on the screen to implement the multi-screen mode, superimposing one image on another in a translucent mode, as well as plotting a line of a given path based on data from an air navigation database.

The control unit for operating modes of the BUR 5 is a multifunctional control panel of buttons located on the perimeter of the LCD-1, encoders for entering parameters and a four-position switch (joystick). The BUR 5 includes a device for interrogating control elements, a device for processing the position of control elements, and a controller for a data transmission channel.

The adapter of input-output-control of information exchange АВВУ 6 is a computing unit, built on the basis of the processor, and includes controllers of input and output channels of communication with on-board equipment and interfaced ground equipment. The processor carries out primary processing of information received via serial communication channels with interfaced airborne and ground equipment, the selection of parametric information for transmission to the graphics processor. Connected by inputs-outputs 1 with MKIO 9, the processor configures the devices that make up the multifunctional indicator, performs testing and initial installation of hardware, determines the mode of operation of the indicator, sets the scale and coordinates of the image on the screen in the computing devices AWP, ARZ, ATI. In addition, the adapter connected to inputs-outputs 4 with UIAP 14, inputs-outputs 5 with UPR 15, and inputs-outputs 2 with UOTM 16 accumulates, filters, and processes the primary parametric information, as well as calculates the derived values and transfers the generated data using MKIO 9 .

The BID 7 source data block is a reprogrammable memory device, including a channel controller, consisting of two functional units: the first functional unit for storing images of primitives (arcs, scales, symbols, images of devices, etc.), and the second functional unit , which is an aeronautical database containing the necessary information for the implementation of all the main sections of the flight route provided by ARINC-424.

The device for smoothing images USI 8 is a set of software and hardware designed to improve dynamic properties when displaying moving objects.

The ICIE 9 command and information exchange highway is a PCI type highway.

Adapter for radar meteorological information AWP 10, adapter for terrain relief ARZ 11, adapter for television information ATI 12 are computing units connected by inputs-outputs 1 to the main information exchange MKIO 9 and inputs-outputs 2 to the main line of video information of the background image MVFI 13 These adapters form arrays of video data of the background image in the LCD 1 format. Adapters are able to reconfigure by commands from the input-output-control adapter for information exchange of the AVUU 6 I (when changing the signal source), scale the image, change the brightness of the background image in relation to the graphic image.

The backbone of video information of the background image IMFI 13 is a digital backbone of the exchange of video information.

The device for measuring aerodynamic parameters UIAP 14 is a device containing sensors for full and static pressure, connected by pipelines, respectively, to airborne probes for full and static pressure, with an electronic device for processing and converting signals (measured pressures), based on a microcontroller.

The spatial orientation device (gyro vertical) of the UPR 15 is based on micromechanical, gyrometric, and accelerometer inertial sensors and includes a processor for processing and calculating the spatial position (roll and pitch angles), based on the processor.

The UOTM 16 current location determination device is based on the GLONASS / GPS satellite information receiving module, which determines the current coordinates (latitude, longitude, altitude), velocity vector, and current time.

The functional devices incorporated in the indicator allow it to perform, in addition to the traditional functions of the multifunctional indicator, additional functions of the SHS and SINS measuring systems, i.e. Integrated Flight Navigation System (IPS) functions.

The work of the integrated multi-functional indicator starts with initialization of the hardware; at the end of initialization, the indicator goes into test mode with the built-in monitoring tools. The results of control according to MKIO 9 are issued to the HLA 6. If the control results are negative, the indicator generates information about the failure in the communication channels with the on-board equipment. If the control results are positive, the blocks that make up the indicator are transferred to the operating mode specified by MKIO 9. Depending on the set of one-time commands and information in the communication lines, the HLAU 6 selects the indicator operation program and sets the operation modes of nodes and blocks.

During the flight, the signals from the sensors for full and static pressure 17 and 18, which are built into the device for measuring the aerodynamic parameters of the UIAP 14, and from the temperature sensor for the complete deceleration of the flow (not included in the indicator) enter the signal processing and conversion device of the OPS 19 (FIG. 2). UOPS device processes these signals, calculates the total _Pn and the static pressure P _st and flow stagnation temperature (T _n) and corrects the signals from the pressure sensors as a function of the stagnation temperature. The corrected pressure signals (R _p , P _st ) and the signal T _p from the UOPS via a code line (RS-232 channel) are supplied to the input-output-control adapter of the information exchange of the AVUU 6, based on the received signals from the UOPS 19 unit, the adapter calculator calculates according to known dependencies, the main aerobatic parameters: instrumental speed V _CR , true speed V _East , absolute height H _abs , relative height H _rel , vertical speed V _c , outdoor temperature T _article and number M.

The AVUU 6 calculator also carries out filtering, processing, and accumulation of information received via serial communication channels from UIAP 14 and UPR 15, converts the calculated data on the speed, barometric altitude, vertical speed, outdoor temperature, and the number M, the calculated spatial position of the aircraft ( roll and pitch angles) along the X, Y, Z axes and gyroscopic course in a form convenient for indication, and issues them along the ICIE 9 information exchange highway to the graphic processor 4 device.

The SNA data from UOTM 16, the on-board (or built-in indicator) magnetic probe and radio means are transferred to the AVVU 6, the calculator of which converts the received signals to the desired shape and transmits them to the UPR 15 device. The UPR 15 contains computational tools by which the spatial position of aircraft taking into account the data received from the SNA. The signals corrected parameters of the spatial position of the UPR 15 enter the device IO Abba 6, a calculator which converts the received signals and the calculated flight parameter (V _ave, V _ist, N _abs, H _rel, V _in, T _v, the number M) a form convenient for indication, and issues them along the ICIE 9 information exchange highway to the graphics processor 4.

When the indicator is executed with a magnetic probe integrated into it, the work in terms of course correction is carried out according to information from the built-in magnetic probe, the data from which are fed to the AVVU 6 input-output device and then to the UPR module 15, where the course correction process (gyromagnetic course) is carried out. The signals of the corrected gyromagnetic course according to magnetic data from the magnetic probe integrated into the system (as well as during course correction from the on-board magnetic probe) are fed back to the AVVU 6 input-output device, the calculator of which converts the corrected signals to the desired shape and transmits them along the information exchange line MKIO 9 and then to the graphics processor 4. Signals from the SNA and the magnetic probe are used in the inventive indicator for the correction, respectively, of the main flight and navigation parameters of the aircraft, measured and calculated by sensors located in autonomous devices for measuring the aerodynamic parameters of UIAP 14 and spatial orientation of the UPR 15. In this case, the advantage is given to signals from a working satellite navigation system SNA. When the signal from the SNA disappears, the output from the aerodynamic parameters measuring device UIAP 14 is used, and the calculated gyroscopic course is corrected using information from the magnetic probe (gyromagnetic course), and the magnetic probe can be either external to the indicator (on-board magnetic probe) or built into it. In the ATI block 12, the number of received lines and the standard of received information are set, the preliminary image format and the base point on the indicator screen are also set. In blocks ARZ 11 and AWP 10, the information display mode (sector, semicircle, etc.) is set, the base point for displaying information on the indicator screen and the format of the background image. After the installation is completed, the AVVU 6 switches to the mode of receiving information from on-board equipment, carries out the primary processing of the received information, and transmits parametric information via MKIO 9 to UGP 4. UGP 4 on the basis of the received information from the HLA 6 generates in the video RAM information equivalent to the image on the indicator screen. In order to exclude the dynamic drift of moving fragments of the image and to facilitate the perception of inclined lines, a device for smoothing the image of ASI 8 has been introduced into the indicator.

Adapters ATI 12, ARZ 11, AWP 10, receiving information on their own communication lines, process the received information and provide information on the MFI 13 to the background information storage device, which is part of the GPU 4. GPU 4, selects the algorithm for controlling the actuator unit of the BIU 3 on the basis of the information received from DB 2, in addition, according to the instructions from the HLA 6 received by MKIO 9, it forms from the information received by MVFI 13 and MKIO 9, the image on the indicator screen in the required form implements the multi-window mode nnogo image when the screen display simultaneously displays information from various sources, i.e. implements overlay images, the formation of a translucent display mode when overlaying images.

The indicator modes can be controlled both via communication lines with the on-board equipment, and from the parameter input device and control of the BUR 5 modes. Using the BUR 5, parameters can also be entered, for example, a given speed, ground pressure, etc. Information on the state of the BUR 5 through AVVU 6 it is issued via communication lines to the on-board equipment mating with it.

In addition, when connecting to the ground equipment of the AVVU 6 through the air navigation database input adapter, which is part of the AVVU 6, it updates the air navigation database stored in the second BID 7 functional node, which is updated in accordance with the AIRAC cycle every 28 days.

The indicator has the ability to interact with the near and far navigation radio system and carry out radio navigation, while the following is displayed on the LCD indicator screen:

- direction to the lighthouses,

- range to lighthouses.

The indicator also has the ability to interact with driven radio beacons and make an approach approach along a glide path.

In addition, the system allows the piloting of an aircraft along a given route using the planned intermediate points of the PPM route.

The presence in the claimed integrated multifunctional indicator of the aerodynamic parameters measuring device UIAP 14 and spatial orientation (gyro vertical) of the UPR 15 allows you to autonomously measure, calculate the known speed, true speed, barometric height, vertical speed, number M, roll angles, pitch, magnetic heading and their indication, which expands the functionality of the indicator, and also allows you to significantly reduce the weight of avionics on the apparatus. In addition, if there is onboard L.A. SHS and SINS systems as standard equipment, the claimed indicator is able to receive and display information from these systems, while the flight-navigation devices built into the indicator act as backups, which ultimately increases the reliability of piloting the aircraft.

Information sources

1. RF patent No. 2181093 "Aviation multifunctional indicator", B64D 45/00, G01C 21/00, 2002.

2. RF patent No. 2287459 “Aviation multifunctional indicator”, B64D 45/00, G01C 21/00, 2006.

Claims (1)

An integrated aviation multifunctional indicator comprising a liquid crystal screen (LCD), a block of sensors for LCD parameters and controls, an actuator unit, an operating mode control unit, as well as a source data unit and an input-output adapter and information exchange control, the operating mode control unit being connected with an input-output-control adapter for information exchange connected by a command and information exchange trunk with an adapter for information about the relief of the earth’s surface, an adapter for evizion information, a radar meteorological information adapter and a graphics processor connected to an image smoothing device and a source data unit, characterized in that the graphics processor is connected to a block of sensors of LCD parameters and LCD controls, a block of actuating devices, and a background image video line to information adapters on the relief of the earth’s surface, television information, radar weather information, and the indicator further comprises a device and measurements of aerodynamic parameters, a spatial orientation device (gyro vertical) and a device for determining the current location, connected to an input-output-control adapter for information exchange.

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