Aviation integrated display system for improving redundancy of electronic flight instrument system

Abstract

The invention provides an aviation comprehensive display system for improving the redundancy of an electronic flight instrument system, which is characterized in that a display unit is additionally arranged at a pilot instrument panel, and information such as attitude, flight height, flight speed, working state, working mode and the like is displayed to a pilot. A centralized control panel (CCP) is additionally arranged at an instrument panel of a pilot, the two CCPs are mutually independent in operation and respectively control picture display of a display unit, and the turning mode, the navigation mode and the combination mode of the navigation equipment must be controlled uniquely, so that instructions of the CCPs need to be transmitted mutually, only one CCP instruction is effective at the same time, and only one CCP instruction is effective at the same time. And the display on the other CCP is kept consistent with the display on the other CCP. The invention provides a redundancy design technology of an electronic flight instrument system, a display unit and a centralized control board are added, and the use reliability of equipment is improved.

Description

Technical Field

[0001] The invention belongs to the field of aviation technology and relates to an aviation integrated display system for improving the redundancy of an electronic flight instrument system. Background Art

[0002] The electronic flight instrument system is mainly used to display flight parameters such as attitude, heading, altitude and speed, as well as equipment status. It is usually composed of a display unit, a display processor, a control panel, etc. According to the instructions of the control panel, the display processor processes the information and the display unit generates the corresponding screen.

[0003] At present, a centralized control panel is installed at the navigator's position on all the aircraft that have been delivered. According to the navigator's usage requirements, he observes the navigation page information during the flight, and also needs to observe flight parameters such as attitude, heading, altitude and speed. However, when the centralized control panel fails, the navigator cannot perform route editing and navigation control functions, which affects the completion of the flight mission. Summary of the invention

[0004] The present invention provides an aviation integrated display system for improving the redundancy of an electronic flight instrument system, which can solve the problem that a navigator cannot plan a route when a centralized control panel fails, and adds a centralized control panel and a liquid crystal display and synchronously processes information of two centralized control panels.

[0005] The present invention provides an aviation integrated display system for improving the redundancy of an electronic flight instrument system, comprising: two centralized control panels CCP, two display control processors DPU, and two display units DU; wherein:

[0006] Two display and control processors DPU are connected to two centralized control panels CCP at the same time, and two display and control processors DPU are connected to one display unit DU respectively;

[0007] The two display and control processors are used to collect signals from the external cross-linking system, receive navigation instructions input by the navigator through any CCP, and send them to the navigation equipment to guide the aircraft in real time. They also generate navigation pictures based on the guidance results and send them to the corresponding display unit DU for display.

[0008] Optionally, the display control processor is used to receive screen operation instructions input by the navigator through the corresponding centralized control panel, and control the corresponding display unit DU to display the screen according to the screen operation instructions.

[0009] Optionally, two centralized control panels CCP operate independently of each other.

[0010] Optionally, the centralized control panel is used to send new navigation instructions input by the navigator to the two display and control processors DPU when receiving them;

[0011] The display and control processor DPU is used to send the latest navigation instructions to the navigation equipment to guide the aircraft in real time.

[0012] Optionally, the display and control processor DPU is used to receive feedback information from the navigation device and send it to two centralized control boards CCP. The centralized control board CCP is also used to display the feedback information from the navigation device.

[0013] Optionally, the display content of the display unit DU includes at least: aircraft attitude, flight altitude, flight speed, working status, and working mode.

[0014] Optionally, the navigation instructions include: waypoints, route binding instructions, and control methods for navigation equipment.

[0015] Optionally, the control modes of the navigation device include: turning mode, navigation mode and combination mode.

[0016] The present invention provides an aviation integrated display system for improving the redundancy of an electronic flight instrument system. A display unit is added to the navigator's instrument panel to provide the navigator with information such as the aircraft attitude, flight altitude, flight speed, working status, and working mode. A centralized control panel (CCP) is added to the navigator's instrument panel. The two CCPs operate independently of each other and control the screen display of a display unit respectively. Since the turning mode, navigation mode, and combination mode of the navigation equipment must be unique, these CCP instructions need to be transmitted to each other. Only one CCP instruction is valid at the same time, and the display on the other CCP is kept consistent with it. The present invention provides a redundancy design technology for an electronic flight instrument system, adds a display unit and a centralized control panel, and improves the reliability of equipment use. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A schematic diagram of the principle of a method for displaying a flight track vector provided by the present invention. DETAILED DESCRIPTION

[0018] The present invention is further described in detail below in conjunction with the accompanying drawings:

[0019] like Figure 1 As shown, the present invention provides an aviation integrated display system for improving the redundancy of an electronic flight instrument system, comprising: two centralized control panels CCP, two display control processors DPU, and two display units DU; wherein,

[0020] Two display and control processors DPU are connected to two centralized control panels CCP at the same time, and two display and control processors DPU are connected to one display unit DU respectively;

[0021] The two display and control processors are used to collect signals from the external cross-linking system, receive navigation instructions input by the navigator through any CCP, and send them to the navigation equipment to guide the aircraft in real time. They also generate navigation pictures based on the guidance results and send them to the corresponding display unit DU for display.

[0022] Optionally, the display control processor is used to receive screen operation instructions input by the navigator through the corresponding centralized control panel, and control the corresponding display unit DU to display the screen according to the screen operation instructions.

[0023] Optionally, two centralized control panels CCP operate independently of each other.

[0024] Optionally, the centralized control panel is used to send new navigation instructions input by the navigator to the two display and control processors DPU when receiving them;

[0025] The display and control processor DPU is used to send the latest navigation instructions to the navigation equipment to guide the aircraft in real time.

[0026] Optionally, the display and control processor DPU is used to receive feedback information from the navigation device and send it to two centralized control boards CCP. The centralized control board CCP is also used to display the feedback information from the navigation device.

[0027] Optionally, the display content of the display unit DU includes at least: aircraft attitude, flight altitude, flight speed, working status, and working mode.

[0028] Optionally, the navigation instructions include: waypoints, route binding instructions, and control methods for navigation equipment.

[0029] Optionally, the control modes of the navigation device include: turning mode, navigation mode and combination mode.

[0030] Among them, the turning methods include: pressure point turning and passing point turning.

[0031] Navigation modes include: route navigation and automatic navigation.

[0032] The combination modes include: combination with GPS and combination with GNSS.

[0033] The present invention provides an aviation integrated display system for improving the redundancy of an electronic flight instrument system, wherein a display unit is added to the navigator's instrument panel to provide the navigator with information such as aircraft attitude, flight altitude, flight speed, working status, working mode, etc. A centralized control panel (CCP) is added to the navigator's instrument panel, and two CCPs are operated independently of each other, and each controls the screen display of a display unit. Since the turning mode, navigation mode, and combination mode of the navigation device must be controlled uniquely, these CCP instructions need to be mutually transmitted, and only one CCP instruction is valid at the same time, and the display on the other CCP is kept consistent with it.

[0034] The electronic flight instrument system consists of two display and control processors. The display and control processors collect signals from the external cross-linking system and receive the waypoints and route binding instructions from the CCP and send them to the navigation equipment to guide the aircraft in real time. The navigator is equipped with two display units and two centralized control panels. The status of CCP1 and CCP2 is synchronously processed by two DPUs to ensure that the navigation status instructions sent by the two devices are unified. The system cross-linking block diagram is shown below: Figure 1 shown.

Claims

1. An aviation integrated display system for improving the redundancy of an electronic flight instrument system, characterized in that: include: Two centralized control panels CCP, two display control processors DPU, two display units DU; among them, Two display and control processors DPU are connected to two centralized control panels CCP at the same time, and two display and control processors DPU are connected to one display unit DU respectively; The two display and control processors are used to collect signals from the external cross-linking system, receive navigation instructions input by the navigator through any CCP, and send them to the navigation equipment to guide the aircraft in real time. They also generate navigation pictures based on the guidance results and send them to the corresponding display unit DU for display.

2. The aviation integrated display system for improving the redundancy of the electronic flight instrument system according to claim 1, characterized in that: The display control processor is used to receive the screen operation instructions input by the navigator through the corresponding centralized control panel, and control the corresponding display unit DU to display the screen according to the screen operation instructions.

3. The aviation integrated display system for improving the redundancy of the electronic flight instrument system according to claim 1, characterized in that: The two centralized control panels CCP operate independently of each other.

4. The aviation integrated display system for improving the redundancy of the electronic flight instrument system according to claim 1, characterized in that: The centralized control panel is used to send new navigation instructions input by the navigator to the two display and control processors DPU when receiving them; The display and control processing unit DPU is used to send the latest navigation instructions to the navigation equipment to guide the aircraft in real time.

5. The aviation integrated display system for improving the redundancy of the electronic flight instrument system according to claim 4, characterized in that: The display and control processor DPU is used to receive feedback information from the navigation device and send it to two centralized control boards CCP. The centralized control board CCP is also used to display the feedback information from the navigation device.

6. The aviation integrated display system for improving the redundancy of the electronic flight instrument system according to claim 1, characterized in that: The display content of the display unit DU includes at least: aircraft attitude, flight altitude, flight speed, working status, and working mode.

7. The aviation integrated display system for improving the redundancy of the electronic flight instrument system according to claim 1, characterized in that: Navigation instructions include: waypoints, route binding instructions, and control methods for navigation equipment.

8. The aviation integrated display system for improving the redundancy of the electronic flight instrument system according to claim 7, characterized in that: The control modes of the navigation equipment include: turning mode, navigation mode and combination mode.

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