CN111232232A - Device and method for comprehensive display control of avionics equipment - Google Patents

Device and method for comprehensive display control of avionics equipment Download PDF

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Publication number
CN111232232A
CN111232232A CN201911401976.9A CN201911401976A CN111232232A CN 111232232 A CN111232232 A CN 111232232A CN 201911401976 A CN201911401976 A CN 201911401976A CN 111232232 A CN111232232 A CN 111232232A
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key
display
control
knob
event
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CN111232232B (en
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罗涛
张松
伍振华
肖永红
唐太虎
汪坤
缪国凯
陈昌明
杨阳
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Chengdu Hermes Technology Co ltd
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Chengdu Hermes Technology Co ltd
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D43/00—Arrangements or adaptations of instruments
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P90/00—Enabling technologies with a potential contribution to greenhouse gas [GHG] emissions mitigation
    • Y02P90/02—Total factory control, e.g. smart factories, flexible manufacturing systems [FMS] or integrated manufacturing systems [IMS]

Abstract

The invention discloses a device and a method for comprehensive display control of avionics equipment, which can improve the human-computer interaction efficiency and the reliability and accuracy of comprehensive display operation, simultaneously reduce the complexity of the hardware connection of a cockpit instrument and a control panel, flexibly configure the button function and are easy to expand and upgrade. The device includes: the system comprises a power supply module, a data processing control module, a graphic processing unit, a display, a control panel and a plurality of communication interfaces; the system comprises a graphic processing unit, a display, a control panel and a display, wherein the graphic processing unit is configured to generate a GUI (graphical user interface) to display flight parameters and receive touch operation on the GUI from a screen of the display and/or control instructions from the control panel; the GUI interface comprises a menu display area and a content display area; the control panel is provided with a plurality of keys and knobs which are connected with the graphic processing unit and used for receiving control instructions of users; the data processing control module is used for processing data from a plurality of on-board devices.

Description

Device and method for comprehensive display control of avionics equipment
Technical Field
The invention relates to the technical field of display and control of avionic equipment, in particular to a device and a method for comprehensively controlling display of avionic equipment.
Background
Modern aircraft usually use a unified processor to process information of various avionics devices on the aircraft uniformly, combine the devices with the same or similar functions in one assembly, display related parameters comprehensively on a display, and transmit related information among the avionics devices through an onboard data bus, so that the performance of all the avionics devices on the whole aircraft reaches a higher level, and such a system is called a comprehensive avionics system.
The integrated avionics system comprises a wide variety of devices with a large number of functions, such as a data interface unit DIU, an atmospheric data system ADC, a combined navigation system INS/GNSS, an integrated radio system CNS, a head-up display unit HUD, and a cabin monitoring system, etc., which differ in the display data required and the corresponding control operations.
The integrated display control unit in the integrated avionics system is used as a main human-computer interaction device in the avionics system, and integrates an atmospheric attitude display subsystem, an engine fuel oil display subsystem, a radio navigation subsystem, a radio communication management subsystem, a flight plan and navigation subsystem, a warning and fault display subsystem, an electronic flight inspection subsystem, a synthetic vision subsystem and the like. In different flight procedures, tasks and navigation phases, different subsystems need to be operated and displayed in a combined manner.
The conventional avionic device needs to be respectively provided with a corresponding display instrument and a corresponding hardware control panel according to various functions of each device, and in the flight process, various flight related data need to be checked on different display instruments and controlled and operated on different control panels positioned at different positions of an engine room. Therefore, the cabin instruments and panels required for displaying and controlling various airborne avionics devices are numerous, the structure is complex, the operation is complex, the learning and adaptation period is long, the interaction efficiency is low, and the functions of all the buttons are fixed and are not easy to flexibly expand.
Disclosure of Invention
At least one of the objectives of the present invention is to overcome the above problems in the prior art, and to provide an apparatus and a method for integrated display control of avionics devices, which can perform centralized display and control on multiple avionics devices, improve the human-computer interaction efficiency and the reliability and accuracy of integrated display operation, reduce the complexity of hardware connection between a cockpit instrument and a control panel, and flexibly configure button functions for easy expansion and upgrade.
In order to achieve the above object, the present invention adopts the following aspects.
An apparatus for integrated display control of avionics, the apparatus comprising: the system comprises a power supply module, a data processing control module, a graphic processing unit, a display, a control panel and a plurality of communication interfaces;
the system comprises a graphic processing unit, a display, a control panel and a display, wherein the graphic processing unit is configured to generate a GUI (graphical user interface) to display flight parameters and receive touch operation on the GUI from a screen of the display and/or control instructions from the control panel; the GUI interface comprises a menu display area and a content display area;
the control panel is arranged around the screen of the display, is provided with a plurality of keys and knobs which are connected with the graphic processing unit and is used for receiving control instructions of a user; the data processing control module is connected with the plurality of on-board devices through a plurality of communication interfaces and used for processing data from the plurality of on-board devices.
Preferably, the control panel is arranged on the outer side of the periphery of the screen and is provided with a first key group and a first knob which are positioned outside the left side of the screen, a second key group and a second knob which are positioned outside the right side of the screen, and a third key group which is positioned outside the lower side of the screen.
As a preferred scheme, the first key group and the second key group are set as fixed function key groups; a part of keys in the first key group and the second key group are set as single fixed function keys to directly input control instructions of fixed functions; the other part of the keys are arranged to combine the fixed function keys to input the control instruction of the fixed function by combining the knobs on the same side as the keys.
Preferably, the content display area is divided horizontally into 4 parts, and each part is the smallest cell display unit; the keys in the third key group are uniformly distributed below the content display area, and each cell display unit is bound with 4 keys below.
Preferably, the graphic processing unit is configured to generate virtual keys with similar positions and same functions as corresponding keys in the third group of key groups in the display interface of each cell display unit.
Based on the same conception, the method for the comprehensive display control of the avionics equipment is provided, and comprises the following steps:
setting a display area of a screen into a menu display area and a content display area, and sending a control signal according to the state change of a key and/or a knob on a control panel; receiving and analyzing the control signal to generate a key event and a knob event; storing and distributing key events and knob events; registering a response function of a corresponding event according to the unique identifier of the key or the knob; and updating the content displayed by each display unit of the content display area according to the operation result data output by the response function.
Preferably, the method comprises the following steps: when the key on the control panel is pressed and released or the knob is rotated, the corresponding hardware equipment generates telecommunication and sends the telecommunication to the graphic processing unit through a control signal data packet; the contents of the data packet include: protocol header, message type, cycle counter, state of each key, state of rotating key, amount of knob rotation, and checksum.
As a preferred scheme, receiving and analyzing the control signal, and generating the key event and the knob event comprises: checking the check bit of the data packet, analyzing according to the format of the control event signal data packet when the check bit is valid, acquiring the current state of each key and the knob, simultaneously comparing the current state of each key with the previous state, and generating a key event and/or a knob event when the difference exists.
Preferably, the method comprises the following steps: and combining two adjacent cell display units into a large-area display unit, or combining three adjacent cell display units into a cross-area display unit.
Preferably, the method comprises the following steps: the event manager is adopted to periodically distribute and process various events, and when the event manager enters the next distribution period according to the generated key or rotation event, the key or rotation event is distributed to the corresponding small-area display unit, large-area display unit or cross-area display unit according to the matching relationship set dynamically.
In summary, due to the adoption of the technical scheme, the invention at least has the following beneficial effects:
according to different application scenes and different flight stages, by freely selecting and switching the combined display mode of each subsystem, the centralized display and control can be performed on various avionics equipment by combining an entity key knob and an interaction interface, so that the human-computer interaction efficiency and the reliability and accuracy of the comprehensive display operation are improved; by flexibly configuring the corresponding relation between the entity key knob and the interactive interface, the complexity of the hardware connection between the cockpit instrument and the control panel is reduced, the redundancy of control input can be improved, and the reliability of the input function is ensured.
Drawings
Fig. 1 is a schematic structural diagram of an apparatus for integrated display control of avionics devices according to an embodiment of the present invention.
FIG. 2 is a schematic diagram of a control panel according to an embodiment of the present invention.
Fig. 3 is a schematic diagram of a display interface of a cell display unit according to an embodiment of the present invention.
Fig. 4 is a schematic view of a large-area display unit display interface according to an embodiment of the present invention.
FIG. 5 is a schematic diagram of a display interface of a display unit according to an embodiment of the invention.
Fig. 6 is a flowchart of a method for integrated display control of an avionics device, in accordance with an embodiment of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and embodiments, so that the objects, technical solutions and advantages of the present invention will be more clearly understood. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Fig. 1 is a schematic structural diagram of an apparatus 100 for integrated display control of avionics devices, according to an embodiment of the present invention, which includes a power supply module 110, a data processing control module 120, a graphics processing unit 130, a display 140, a control panel 150, and a plurality of communication interfaces. Each integrated display control device 100 is powered by an onboard 28V dc power supply, and a power module 110 in the device 100 has multiple independent outputs to provide power to each unit. The graphics processing unit 130 is configured to generate a GUI interface to display various flight parameters and receive on-screen touch operations to the GUI interface from the display 140 and/or control instructions from the control panel 150. The control panel 150 is disposed around the screen of the display 140, and has a plurality of keys and knobs connected to the graphic processing unit 130 for receiving control instructions of a user. The data processing control module 120 is connected to the plurality of on-board devices through a plurality of communication interfaces, and is configured to process data from the plurality of on-board devices.
The data processing control module 120 includes a left processing unit 121 and a right processing unit 122, where an internal synchronization interface (for example, a synchronization bus may be used, or one ethernet interface may also be used for synchronization) is provided between the left processing unit 121 and the right processing unit 122 to perform data synchronization communication, so as to implement dual-redundancy data processing, where a single display displays a data processing result of the left processing unit, and only when a switching trigger condition is met, the data processing result of the right processing unit is switched and displayed. The left processing unit 121 is directly connected with INS/GNSS-1, ADC-1, CNS and other equipment through a serial interface, and the right processing unit 122 is directly connected with INS/GNSS-2 and ADC-2 through a serial interface; when a tuning instruction is sent to the CNS using the right processing unit 122, the data and instructions are synchronized by an internal synchronization interface between the processing units 121 and 122. Each of the left and right processing units 121 and 122 is connected to the data interface units DIU-1 and DIU-2, respectively, through ethernet interfaces; the head-up display HUD is connected to both DIU-1 and DIU-2 and transmits information to DIU-1 and DIU-2, respectively, DIU-1 transmits data to the left processing unit 121 through an Ethernet interface, and DIU-2 transmits data to the right processing unit 122 through an Ethernet interface. Each of the left and right processing units 121 and 122 has a navigation data processing module, an atmospheric data processing module, a radio data processing module, and a head-up data processing module to process respective data.
Fig. 2 shows a schematic view of a control panel according to an embodiment of the invention. The control panel 200 is disposed around the screen 210, and has a first key group (including keys L1 through L8) and a first knob LX located outside the left side of the screen, a second key group (including keys R1 through R8) and a second knob RX located outside the right side of the screen, and a third key group (including keys D1 through D16) located outside the lower side of the screen.
The first key group and the second key group are set as fixed function key groups, and corresponding identification symbols can be printed on the surfaces of the fixed function key groups. A part of keys in the first key group and the second key group are set as single fixed function keys to directly input control instructions of fixed functions; the other part of the keys are arranged to combine the fixed function keys to input the control instruction of the fixed function by combining the knobs on the same side as the keys. For example, the keys L1 to L4 in the first key group are set as single fixed function keys for sequentially and directly inputting control instructions for increasing or decreasing brightness, calling a system software menu, and switching between main and standby hardware; the keys R1 to R4 in the second key group are set as a single fixed function key for directly inputting control commands for increasing or decreasing contrast, calling a system mode menu, and calling a system emergency checklist in sequence. Keys L5 to L8 in the first key group are provided as combination fixed function keys, for example, a control command of course preselection is inputted by a knob on the same side after a key L5 is pressed, a control command of channel selection is inputted by a knob on the same side after a key L6 is pressed, a control command of frequency tuning of radio station 1 is inputted by a knob on the same side after a key L7 is pressed, and a control command of frequency tuning of radio station 2 is inputted by a knob on the same side after a key L8 is pressed; the keys R5 to R8 in the second key group are provided as a combination of fixed function keys, for example, a control command for flying height selection is inputted by the same-side knob after the key R5 is pressed, a control command for atmospheric pressure selection is inputted by the same-side knob after the key R6 is pressed, a control command for automatic directional frequency tuning is inputted by the same-side knob after the key R7 is pressed, and a control command for navigation frequency tuning is inputted by the same-side knob after the key R8 is pressed.
The GUI interface in the display area of the screen 210 is set to a menu display area 211 located above the dotted line and a content display area 212 located below. The menu display area 211 is configured to display entry icons of sub-pages of a system software menu, a system mode menu, a system emergency checklist, frequency tuning, an engine status, a fuel remaining amount, an alarm prompt, a system message, a current navigation station, a simple content display, an audio control, a map display, and the like to enter the corresponding sub-page for control input or display. The content display area 212 may be further divided into a plurality of sub display regions to accommodate different display modes according to the selected sub menu icon or the control command input by the key. Specifically, as shown in fig. 3, the content display area 212 is set to be divided horizontally into 4 portions by default, each portion being the smallest cell display unit. As shown in fig. 4, when a certain sub-page needs a larger display area, for example, to display more map areas, two adjacent cell display units can be combined into a large area display unit, and the content display area is divided into three parts. As shown in fig. 5, three adjacent cell display units may be further combined into a cross-region display unit, so that the content display region is divided into two parts.
Keys D1-D16 in the third key group are uniformly distributed below the content display area, each cell display unit corresponds to 4 keys below the content display area, and cell key events are designated as 0-3; each large-area display unit corresponds to 8 keys below the large-area display unit, and large-area key events are designated to be 0 to 7; each cross-region display unit corresponds to 12 keys at the lower part, and cross-region key events are designated as 0 to 11. The keys in the third key group are set to be bound with the fixed cell display unit, the event manager receives and distributes key events, the graphic processing unit calls a receiving function, analyzes control instructions of the key events, and sends the control instructions to the corresponding airborne equipment through the communication interface and updates the content display area.
In various embodiments, the graphic processing unit may be configured to generate a virtual key with a similar position and a same function as corresponding keys in the third group of key groups in the display interface of each cell display unit, so as to backup the virtual key with the third group of key groups, thereby improving the reliability of control.
Fig. 6 shows a flowchart of a method for integrated display control of an avionics device, in accordance with an embodiment of the present invention.
Which comprises the following steps:
step 601: setting the display area of the screen as menu display area and content display area, and sending control signal based on the state change of the keys and/or knobs on the control panel
Specifically, when a key on the control panel is pressed, released or the knob is rotated, the corresponding hardware device generates an electrical signal and sends the electrical signal to the graphic processing unit through a control signal data packet. The contents of the data packet include: the method comprises the steps of a protocol header, a message type, a cycle counter, each key state (including pressing or bouncing), a rotary key state (including pressing or bouncing), knob rotation amount (0-255) and a checksum. Table 1 below shows an exemplary format of a control signal packet:
TABLE 1
Figure BDA0002347713470000081
Step 602: receiving and analyzing the control signal to generate a key event and a knob event
Specifically, the check bits of the data packet may be checked, and when the check bits are valid, the check bits are analyzed according to the format of the control event signal data packet to obtain the current latest state of each key and the knob, and simultaneously, the current state of each key is compared with the previous state, and when there is a difference, a key event and/or a knob event is generated, and the event object is stored in the event manager. Wherein each key event comprises a key unique identification ID and a key state. Each knob event includes a knob unique identifier ID and an amount of rotation, wherein each of the first and second knobs may include an inner knob and an outer knob.
Step 603: storing and distributing key events and knob events
For example, an event manager may be used, which is configured as a class in a software program for managing various events generated in the system, and this class periodically performs distribution and processing of various events, and when the event manager enters the next distribution cycle according to the generated key or rotation event, the event manager distributes the key or rotation event to the corresponding cell display unit, large area display unit, or cross-area display unit according to the matching relationship dynamically configured to interact with the displayed interface. The event manager is used for dynamically matching and distributing various events and corresponding keys or knobs, so that the corresponding relation between the entity key knobs and the interactive interface is flexibly configured, the complexity of the connection between a cockpit instrument and control panel hardware is reduced, the redundancy of control input can be improved, and the reliability of the input function is ensured.
Step 604: registering response functions of corresponding events according to unique identifiers of keys or knobs
Specifically, each display unit in the current content display area registers a response function according to the unique identifier of the corresponding key or knob, inputs a state value corresponding to the key or the rotation event into the response function, outputs operation result data (for example, a brightness value calculated according to the key state value, a tuning frequency, and the like) by the response function, and may generate a corresponding control instruction according to the operation result data to send to the corresponding onboard device.
Step 605: updating the contents displayed by each display unit of the content display area according to the operation result data output by the response function
In each display unit of the content display area, data and state changes due to key events and/or knob events may be updated and displayed in real time. And, the feedback message of each onboard device to the control command can be further based on the displayed content.
The foregoing is merely a detailed description of specific embodiments of the invention and is not intended to limit the invention. Various alterations, modifications and improvements will occur to those skilled in the art without departing from the spirit and scope of the invention.

Claims (10)

1. An apparatus for integrated display control of avionics, the apparatus comprising: the system comprises a power supply module, a data processing control module, a graphic processing unit, a display, a control panel and a plurality of communication interfaces;
the system comprises a graphic processing unit, a display, a control panel and a display, wherein the graphic processing unit is configured to generate a GUI (graphical user interface) to display flight parameters and receive touch operation on the GUI from a screen of the display and/or control instructions from the control panel; the GUI interface comprises a menu display area and a content display area;
the control panel is arranged around the screen of the display, is provided with a plurality of keys and knobs which are connected with the graphic processing unit and is used for receiving control instructions of a user; the data processing control module is connected with the plurality of on-board devices through a plurality of communication interfaces and used for processing data from the plurality of on-board devices.
2. The device of claim 1, wherein the control panel is disposed around the outside of the screen with a first key set and a first knob located outside the left side of the screen, a second key set and a second knob located outside the right side of the screen, and a third key set located outside the lower side of the screen.
3. The apparatus of claim 2, wherein the first key set and the second key set are configured as a fixed function key set; a part of keys in the first key group and the second key group are set as single fixed function keys to directly input control instructions of fixed functions; the other part of the keys are arranged to combine the fixed function keys to input the control instruction of the fixed function by combining the knobs on the same side as the keys.
4. The apparatus according to claim 1, wherein said content display area is arranged to be divided horizontally into 4 parts each of which is a smallest cell display unit; the keys in the third key group are uniformly distributed below the content display area, and each cell display unit is bound with 4 keys below.
5. The device of claim 4, wherein the graphical processing unit is configured to generate a virtual key with a similar position and a same function as a corresponding key in the third group of keys in the display interface of each cell display unit.
6. A method for integrated display control of avionics equipment, the method comprising:
setting a display area of a screen into a menu display area and a content display area, and sending a control signal according to the state change of a key and/or a knob on a control panel; receiving and analyzing the control signal to generate a key event and a knob event; storing and distributing key events and knob events; registering a response function of a corresponding event according to the unique identifier of the key or the knob; and updating the content displayed by each display unit of the content display area according to the operation result data output by the response function.
7. The method of claim 6, wherein the method comprises: when the key on the control panel is pressed and released or the knob is rotated, the corresponding hardware equipment generates telecommunication and sends the telecommunication to the graphic processing unit through a control signal data packet; the contents of the data packet include: protocol header, message type, cycle counter, state of each key, state of rotating key, amount of knob rotation, and checksum.
8. The method of claim 7, wherein receiving and interpreting the control signal and generating the key event and the knob event comprises: checking the check bit of the data packet, analyzing according to the format of the control event signal data packet when the check bit is valid, acquiring the current state of each key and the knob, simultaneously comparing the current state of each key with the previous state, and generating a key event and/or a knob event when the difference exists.
9. The method of claim 6, wherein the method comprises: and combining two adjacent cell display units into a large-area display unit, or combining three adjacent cell display units into a cross-area display unit.
10. The method of claim 9, wherein the method comprises: the event manager is adopted to periodically distribute and process various events, and when the event manager enters the next distribution period according to the generated key or rotation event, the key or rotation event is distributed to the corresponding small-area display unit, large-area display unit or cross-area display unit according to the matching relationship set dynamically.
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