RU2431204C2 - Head-up display - Google Patents

Abstract

FIELD: physics.

SUBSTANCE: device includes an electron-beam device, a collimating optical head, and a central processing module, graphic processor module, non-volatile memory module, input-output module, all connected on a computation-data exchange main line, and an additional multifunctional indicator and a local data exchange main line.

EFFECT: adaptation of devices to change piloting in situations.

1 dwg

Description

The invention relates to the field of aviation instrumentation, in particular to indicating instruments for displaying to the crew state parameters and aircraft control parameters.

In the closest analogue (US patent No. 5302964 C1, 345/7, IPC G09G 1/04, [1]) an aviation indicator is presented that includes a collimator optical head interacting with an electron-beam device controlled from a computing-converting device (VPU) containing a central processor module, a graphics processor module, a non-volatile memory module, an input-output module connected by inputs / outputs on a highway of computer-information exchange. The signals of information mnemonics of typical situations formed in the VPU through an electron-beam device and a collimator optical head are presented to the crew as an image in projection to infinity against the background of the space behind the windshield of the aircraft cabin. In this case, the collimator optical head is a two-component lens according to the patent of the Russian Federation No. 2358303 [2].

The disadvantage of the closest analogue is the limited ability to quickly configure and manage typical situations and operating modes of the collimator aircraft indicator and the equipment of the aircraft equipped with it.

The objective of the invention is to expand the functionality of the collimator aircraft indicator.

This result is achieved by the fact that the collimator aviation indicator, including a central processor module, a graphics processor module, a non-volatile memory module, an input-output module, connected to one input-output via the computer-information exchange highway, is connected to the on-board data exchange channel to the inputs and outputs of the electron-beam device and the collimator optical head in the form of an optical system of lenses, reflective and translucent mirrors, forming in the pilot’s field of view in projection to infinity, the image transmitted by the light beam of the electron-beam device against the background of the visible cockpit space also includes a multifunction indicator connected by the first input-output, respectively, to the computer-information exchange highway and the second input-output, respectively, to the airborne information exchange channel a local trunk of information exchange connecting another input-output of the central processor module, another input-output of the graphical module th processor, the other input-output non-volatile memory module, the third input-output input-output module, and a third input-output multi-indicator.

The drawing shows a block diagram of a collimator aviation indicator (KAI), containing: 1 - main line of computing and information exchange MVIO, 2 - module of the central processor MCP, 3 - module of a graphics processor IHP, 4 - module of non-volatile memory MEP, 5 - input module- MVV output, 6 - local highway of information exchange LMIO, 7 - multifunctional indicator MFI, 8 - electron beam device ELP, 9 - collimator optical head KOG, 10 - interacting equipment VDO, 11 - on-board channel for information exchange B KIO.

The blocks of MCP 2, MGP 3, MEP 4, MVV 5, interconnected according to MVIO 1, form a computing-converting device (VPU) - a digital computing machine that receives data from consumers (MVV 5), performing calculations using embedded algorithms and programs (MPP 2, IHL 3, IEP 4, MVIO 1), the conversion and delivery of generated data to consumers (MVV 5). The VPU blocks are executed on standard computing elements according to standard computing schemes shown, for example, in the book Presnukhin L.N., Nesterov P.V. “Digital Computers”, Moscow, Higher School, 1981, p. 21, p. 474.

When stabilized supply voltages are supplied from MVV 5 through BKIO 11, the ELP generator 8 emits a narrow electron beam (beam) to the luminescent screen on which a luminous dot appears. When applying control voltages (x, y) from MVV 5 to BKIO 11, a luminous point on the screen of ELP 8 tracks the given x, y; accordingly, the luminous trail forms an image on the EBP screen 8. The luminous flux from the EBP screen 8 enters COG 9 [2], which is an optical system of lenses, reflecting and translucent mirrors forming in the field of view of the pilot of the aircraft in projection to infinity transmitted by the light flux from the screen ELP 8 image on the background of the visible in-hull space. Thus, the KAI collimator aviation indicator is formed.

VDO 10 (not included in the inventive device) includes airborne information (navigation, flight, sighting and sighting) systems and sensors of information necessary for forming information frames on the ELP screen 8. Interaction of VDO 10 with the second input-output of MVV 5 is carried out according to the CCW 11, which includes all types of natural, standard and non-standard relationships, for example, according to GOST 26765.52-87, GOST P50832-95, GOST 18977-79, STANAG 3350, RS-423.

MVIO 1, made, for example, on the basis of a high-speed noise-protected LVDS interface (I. Furman, E. Zvonarev, “High-speed LVDS and M-LVDS Interfaces”, Electronics, Moscow, Nauka, 2003, No. 8, pp. 32-36 ), providing the transmission and reception of information streams (including video data) with a speed of up to 2 Gbit / s and the organization of computing processes for the formation and transmission of video frames in real time.

The additionally introduced IFI 7 (patent No. 2181093 for the invention “Aircraft multifunctional indicator”) is, for example, a multifunctional indicator operating in the mode of a multifunctional control panel.

Additionally introduced LMIO 6 is a double bit channel (DBK) of serial communication with a speed of up to 30 Mbit / s, made according to the RS-485 standard with a communication line on two (receive-transmit) twisted pair wires. Through synchronization for each bit and each transmitted word, circular echo control is implemented in the transmitter-communication-receiver-communication-communication-transmitter-circuit with monitoring the status of transceiver devices, wired communication and transmitted information. LMIO 6 in the form of DBK provides a reliable, controlled exchange of MFI 7 keyboard processing signals, one-time commands, light signals, manual and automatic adjustment of image quality on the ELP 8 screen.

MFI 7 contains on the front panel an information board made on the liquid crystal screen, buttons (buttons, keys, touch buttons) for operative input of alphanumeric information, KAI mode control buttons, knobs for operative adjustment of image brightness on the MFI 7 information panel, on the ELP screen 8 and, respectively image submitted by KOG 9.

When the MIF7 mode “navigation” and standard situations corresponding to this mode are set to “route”, “landing”, “re-entry”, control signals from the first input-output of MFI 7 according to MVIO 1 arrive at IHL 3. At the same time, data from sensors and parameter systems the state of the aircraft and the environment (the angles of evolution of the aircraft, components of the speed of movement, angles of attack and slip) from the VDO 10 input-output according to BKIO 11 are fed to the second input-output MVV 5, from the first input-output of which the converted parameter signals according to MVIO 1 arrive and an input-output IHP 3.

MEP4 stores long-term and operational data of graphic and alphanumeric characters, fonts, which from the input-output of MEP 4 via MVOI 1 go to the input-output of MGP 3. MCP 2 carries out a cyclogram of the computing process and the data exchange procedure according to MVIO 1 and LMIO 6 between IHL 3, MEP 4, MVV 5, MFI 7.

In IHL 3, mnemo-frames of images are formed corresponding to given modes and typical situations. Signals of a graphic image, converted to the form of the given deviations of the luminous point (x, y and its brightness z) of the beam on the screen of the ELP 8, from the input-output of the IHP 3 via MVIO 1 go to the first input-output of MVV 5, from the second input-output which, according to BKIO 11, the converted parameters x, y, z are fed to the input-output of the ELP 8, the deflecting device of which generates the beam motion in the form of a dot glowing with brightness z on the screen of the ELP 8, thereby reproducing the current mnemonic formed in MPL 3. The luminous flux from the screen of the ELP 8 enters the COG 9, in which the image of the current mnemonic frame is formed in projection to infinity against the background of the visible hull space. The formats of the presented image are determined by the dimensions of the EBF 8 screen, the geometric ratios of the optical elements in KOG 9 and the scale factors of the parameters x, y coming from the MHP 3.

Indication frames for the pilot are informative in the automatic flight mode and are indicative-controlling when switching to the semi-automatic and manual control modes. At the same time, the mnemonic images formed in MGP 3 from the MGP 3 input-output 3 through MVIO 1, the second MVV 5 input-output, through BKIO 11 go to the VDO 10 input-output for recording into the video signal registration system and displaying it on the display means - multifunction indicators , means of indication helmet-mounted target designation system. The same mnemo-frames of images from the input-output of the MGP 3 according to MVOI 1 are fed to the input-output of the MFI 7 and, by command with a click on the corresponding button, the mnemo-frames of images can be presented on the information panel of the MFI 7 for information control of the image represented by the KOG 9.

When connecting the airspace and the earth's surface aids (for example, the optical radar system or the radar radar system), the signals of the survey data from the VDO 10 input-output according to BKIO 11 are fed to the second input-output MVV 5 and from the first input-output MVV 5 according to MVIO 1 - to the inputs and outputs of MCP 2 and MHP 3, where, together with data from MEP 4, integrated mnemonic frames of typical situations are formed for displaying the results of the review and the use of various countermeasures with guidance from the OLS or radar in various targeting methods, pointing assessment and application of the discovered goals and landmarks, as well as the implementation of repeated visits and the implementation of repeated applications. The aforementioned integrated mnemonic frames with superimposed navigation and aerobatic information, reduced to control signals x, y, z of the ELP 8, from the input-output of MGP 3, through MKIO 1, first input-output MVV 5, second input-output MVV 5 according to BKIO 11 enter the VDO 10 input / output for registration on the video recording means and the ELP 8 input / output, respectively, KOG 9 forms an image of the mnemonic frames, using which the pilot navigates, reviews the location and uses countermeasures for fixed targets and landmarks.

If the clarity and brightness of the image deteriorates, the pilot (operator) acts on the adjustment knobs on the front panel of the MFI 7. The control signals from the third input-output of the MFI 7 via the additionally entered LMI 6 are sent to the other input-output of the IHP 3, where commands for changing the brightness z are generated, commands for changing the control supply voltages, which from this input-output of MGP 3 via LMIO 11 go to the third input-output of MVV 5. Converted signals from the second input-output of MVV 5 according to BKIO 11 are fed to the input-output of ELP 8, respectively, according to the presented KOG 9 images, the pilot controls the adjustment results.

The additionally introduced LMIO 6 and MFI 7 significantly expand the functionality of the collimator aviation indicator and significantly increase the efficiency of aircraft performing navigation, control and guidance tasks.

Claims (1)

A collimator aviation indicator, including a central processor module, a graphics processor module, a non-volatile memory module, an input-output module connected by the same I / O on the main line of computing and information exchange, the second input-output of which is connected to the electronic input-outputs via the on-board information exchange beam device and collimator optical head in the form of an optical system of lenses, reflective and translucent mirrors, forming in the pilot's field of view in projection onto the endless the image transmitted by the light flux of the electron-beam device against the background of the visible pit space, which also includes the first input-output, respectively, to the computer-information exchange highway and the second input-output, respectively, to the on-board information exchange channel, a multifunctional indicator, and a local information exchange highway, connecting another input-output of the CPU module, another input-output of the GPU module, another input-output non-volatile memory module, the third input-output of the input-output module and the third input-output of a multifunctional indicator.