RU2178375C1 - Aircraft multi-function display - Google Patents

Abstract

FIELD: aviation instrumentation engineering. SUBSTANCE: display is designed for representation of parameters of flying vehicle and its on- board equipment by crew members. Display includes liquid crystal screen, unit of sensors showing screen state parameters, actuating device unit, unit of mode-of-operation controls and information exchange adapter, reprogrammed storage of programs and symbols, on-line storage unit, graphical processor, video graphical adapter, reprogrammed synthesized multiple image storage and information exchange adapter with ground technological and operational verifying equipment which are interconnected by inputs and outputs via information computer exchange line. Said display possesses extended functional capabilities and may be used as tactical situation display, low altitude flight display, windscreen display, observation facilities display, as well as multi- functional control console of flying vehicle and on-board equipment. EFFECT: enhanced efficiency and reliability. 3 cl, 1 dwg

Description

 The invention relates to the field of aeronautical instrumentation, in particular to in-cab display devices for displaying the state parameters of an aircraft and onboard equipment.

 The closest analogue is a multifunctional indicator described in [1] - US patent N 5896098; CL. 340-974; IPC G 01 C 21/00.

 This indicator is made on the liquid crystal screen, has connections with on-board transceiver equipment via analog, digital and discrete inputs / outputs, and operates in the “planned navigation indicator” or “command flight horizon” modes.

 The disadvantage of the closest analogue is the limited ability to display information from measuring systems and sensors of aircraft (airplanes and helicopters), performing, for example, low-altitude flight relative to the relief of the earth’s surface, equipped with a survey system of the earth’s surface and air space, equipped with resettable countermeasures against television, thermal and radar guidance and homing devices.

 The objective of the invention is to expand the functionality of the aviation multifunctional indicator.

 This result is achieved by the fact that the aviation multifunctional indicator comprising a liquid crystal screen, a block of sensors for screen state parameters, a block for actuators for screen state parameters, a block for operating mode controls, and an information exchange adapter with on-board equipment interconnected inputs and outputs along the information and computing exchange line, reprogrammable memory of programs and symbols, block of random access memory, graphic percent a quarrel, a video graphics adapter, the second input-output of which is combined with the input-output of the liquid crystal screen and the second input-output of an information exchange adapter with on-board equipment, to the third or sixth inputs-outputs of which, respectively, the input-output of the actuator unit of the screen state parameters is connected, the input - the output of the block of controls of operating modes, the input-output of the sensor block of the parameters of the screen condition, the first input-output of the aviation multifunction indicator in relation to the onboard reception transmitting equipment, an additional programmable memory device for synthesized multidimensional images and an exchange adapter with ground technological and operational calibration equipment, the second input-output of which is connected to the second input-output of the aviation multifunction indicator in relation to the ground technological and operational calibration equipment.

 In conjunction with the first input-output of an aircraft multi-function indicator with airborne transceiver equipment, the possibility of its operation as a “tactical situation indicator”, “low-altitude flight indicator”, “indicator on the windshield”, “visibility indicators”, and “multi-function aircraft control panel is implemented” apparatus and avionics. "

 In relation to the second input-output of the aviation multifunctional indicator with ground-based technological and operational calibration equipment, the possibility of its operational modernization without changing the composition is realized.

The drawing shows a block diagram of an aviation multi-functional indicator (AMFI), containing:
1 - liquid crystal display LCD,
2 - block sensors parameters of the state of the BDPS screen,
3 - block actuators parameters of the state of the screen BIUS,
4 - block controls the operating modes of the BOUR,
5 - video graphic adapter VGA,
6 - adapter information exchange with on-board equipment AOBA,
7 - exchange adapter with ground technological and operational calibration equipment AONA,
8 - reprogrammable memory device programs and characters PPZUPS,
9 is a block of random access memory devices BOSU,
10 - reprogrammable memory device of synthesized multidimensional images PPZUSO
11 is a graphical processing unit,
12 - highway information and computer exchange MIVO,
13 - ground technological and operational calibration equipment NTEPA,
14 - airborne transceiver equipment BPL.

 NTEPA 13 and BPPA 14 are interacting equipment and are not part of AMFI.

 LCD 1 [1] is a standard color or monochrome panel type indicator. LCD 1 at its input-output receives the video signals of television mnemonic frames for display and gives response signals of echo monitoring and serviceability.

BJPS 2 [1] is a service device for LCD 1, it provides the measurement of screen state parameters (temperature, illumination), which from the BJPS 2 input-output, together with health signals and echo control response signals, are fed to the fifth AOBA 6 input-output 6. BIUS 3 [ 1] is a device that ensures the completion of the specified parameters of the screen state:
- temperature using elements of heating and cooling the screen,
- Illumination using screen backlight.

 From the third input-output of AOBA 6, the signals of the specified parameters of the state of the screen and the echo control signals are sent to the input-output of the BIUS 3, from where the response signals of the echo control and serviceability are sent to the third input of the AOBA 6.

 BOUR 4 is the master of AMPI operating modes and contains a set of button keys (or touch buttons), by pressing which the AMPI operating modes are set or the specified parameters of the screen state (temperature, illumination) and displayed image parameters (brightness, color, contrast) are adjusted. From the fourth input-output of AOBA 6, the echo control signals and response signals confirming the fact that the button-keys were pressed by turning on their backlight lamps are fed to the input-output of the BOUR 4, from which the button-key press signals and the echo control response signals come from.

 MIVO12 ([1], [2] Nesterov L. N, Petrukhin P.V. "Digital Computers", Moscow, Higher School, 1981, p. 21, p. 474), controlled from AOBA 6 at its first entrance - output, interconnects all computing and conversion units (CAA 5, AOBA 6, AONA 7, PPZUPS 8, BOZU 9, PPZUSO 10, GRPR 11) at their inputs and outputs with an exchange frequency (not less than 2 MHz) that ensures reception, the computational process, data transfer and display on LCD 1 in almost the same time in accordance with the requirements of AMFI as an aviation indicator.

AMPI in its first input-output is interconnected with input-output of BPPA 14:
- from AMPI to BPPA 14, echo control response signals, serviceability signals of AMPI and its units, signals of video frames presented on LCD 1 are received; all the above signals are received in the on-board monitoring and registration system;
- from BPPA 14 AMFI receives signals from measuring systems (navigation and flight control system, survey systems, monitoring and registration systems, control systems of countermeasures, etc.) with analog, digital, discrete, television and location analog and digital outputs. The first input-output of AMFI is interconnected with the sixth input-output of AOBA 6.

 BOZU 9 ([1]; [2], p. 17) is a block of random access memory that interacts through MIWO 12 with other AMFI units during the computational process and data exchange.

 PZPUPS 8 ([1]; [2], p. 17) is a reprogrammable memory device, with a memory capacity of up to 2 megabytes, storing standard programs (a single-time operating system program and a program for interacting with MIVO 12), application and logic solving programs AMFI works, data set of standard graphic primitives, fonts, characters.

 The newly introduced MESP 10 is a reprogrammable memory device with a large memory capacity (up to 150 megabytes) that stores data of multidimensional synthesized images - two-dimensional and three-dimensional maps and terrain images transforming in time, images of synthesized building objects, countermeasures necessary for presentation to the crew on LCD1 during the flight, especially of low altitude.

 TRPR 11 ([1]; [2], p. 433) generates signals of graphic images (in interaction with the inputs-outputs of AOBA 6, PPZUPS 8, BOZU 9, PPZUSO 10), which through MIVO 12 go to the first input-output of the CAA 5.

 NTEPA 13, which provides verification of AMPI in operation, loading and verifying the correct loading of programs and data in PPZUPS 8 and PPZUSO 10, interacts with AMPI on its second input-output connected to the second input-output of the newly introduced block AONA 7, the first input is the output of which is connected to MIVO 12. For the accelerated loading of large amounts of information in MESP 10 (via MIVO 12 from NTEPA 13), AONA 7 provides fast information exchange (exchange frequency of more than 2 MHz) of the ISA type of personal computer IBM PC / AT.

 Data replacement in PPZUPS 8 is carried out during the modernization of AMFI (various aircraft, improvements based on the results of tests and operation).

 Replacing the data in MES 10 is carried out when changing theaters of action, regions and countries where the aircraft are based, as well as during the modernization and refinement of AMFI.

 The work of AMFI in flight is carried out with undocked NTEPA 13 in conjunction with BPPA 14.

 CAA 5 generates video frame signals, which from the second input-output of CAA 5 go to the input-output of LCD 1 for visualization on the screen and to the second input-output of AOBA 6 for conversion and transmission through its sixth input-output, the first input-output of AMFI , BPPA 14 input-output in the on-board control and registration system.

 AOBA 6 [1] is an input-output controller that accepts signals of various types from the second to sixth inputs-outputs, synchronizes these signals and outputs the first input-output through MIWO 12 to the first input-output of the CAA 5. Response signals of echo control and serviceability 12 blocks interacting via MIVO through the first input-output of AOBA 6, its sixth input-output, and the first input-output of AMPI enter BPPA 14 in the control and registration equipment. In the interaction of CAA 5, AOBA 6, PPZUPS 8, BOZU 9, PPZUSO 10, GRPR 11, a mixed color video signal is formed, including information from BPPA 14, symbolic and font information, information of multidimensional synthesized images, converted into CAA 5 into a signal of video frames presented on LCD 1.

By pressing the softkeys on BOUR 4, AMPI operating modes are set as in the closest analogue and new operating modes with the mixed color video signal displayed on LCD 1:
- "indicator of tactical situation",
- "low altitude flight indicator",
- "indicator on the windshield",
- “review tools indicators”,
- "multifunctional control panel for aircraft and avionics",
which, together with the possibility of operational modernization, AMFI significantly expands its functionality as part of on-board equipment complexes of aircraft, aircraft and helicopters for various purposes.

Claims (3)

 1. Aircraft multifunctional indicator comprising a liquid crystal screen, a block of sensors for screen state parameters, a block for actuators for screen state parameters, a block for operating mode controls, and an information exchange with on-board equipment interconnected by inputs and outputs on an information and computer communications exchange, a programmable program memory and characters, a block of random access memory devices, a graphics processor, a graphics adapter, the second the input-output of which is combined with the input-output of the liquid crystal screen and the second input-output of an information exchange adapter with on-board equipment, to the third, fourth, fifth, sixth inputs and outputs of which are connected respectively the input-output of the actuator unit of the screen state parameters, input-output the block of controls for operating modes, the input-output of the block of sensors for the state of the screen, the first input-output of the aircraft multifunction indicator in relation to the onboard transceiver equipment d, characterized in that it additionally introduces a reprogrammable memory device for synthesized multidimensional images connected by inputs and outputs to the computer-data exchange highway and an information exchange adapter with ground technological and operational calibration equipment, the second input-output of which is connected to the second input-output of the aircraft multifunctional indicator in relation to ground technological and operational equipment.  2. Aircraft multifunctional indicator according to claim 1, characterized in that, in relation to the first input-output with on-board transceiver equipment, it is possible to operate as an indicator of tactical conditions, an indicator of low-altitude flight, an indicator on the windshield, indicators of viewing tools, and a multifunctional console control of the aircraft and on-board equipment.  3. Aircraft multifunctional indicator according to claim 1, characterized in that, in relation to the second input-output with ground technological and operational calibration equipment, it is possible to quickly upgrade it without changing the composition.