Virtual automatic flight control interface human-computer interaction system and method

Abstract

The present application belongs to the field of automatic flight control, and particularly relates to a virtual automatic flight control interface human-computer interaction system and method. The system comprises: a cockpit integrated display control subsystem, a plurality of instruction solving units, an automatic flight control board, a cockpit integrated display control subsystem, a power control device, the cockpit integrated display control subsystem comprises a digital keyboard and a multifunctional display, the automatic flight control board is crosslinked with the instruction solving units and the power control device through an HB6096 bus, a virtual interface is resident on the multifunctional display of the cockpit integrated display control subsystem, the multifunctional display is crosslinked with the instruction solving units through an AFDX network bus, the multifunctional display is crosslinked with the power control device through the HB6096 bus, the instruction solving units are crosslinked with a central warning system through the AFDX network bus, and the digital keyboard of the cockpit integrated display control system is connected with the multifunctional display through a system internal bus and used for sending a target value and the like signal to the multifunctional display.

Description

Technical Field

[0001] This invention belongs to the field of automatic flight control, specifically relating to a virtual automatic flight control interface human-computer interaction system and method. Background Technology

[0002] The automatic flight control board is a component of the automatic flight control subsystem. It is used for connecting and disconnecting the automatic flight control subsystem and for mode / mode selection. It also displays and sets altitude, speed, heading / track, and vertical speed / track tilt angle, serving as the primary means of human-machine interaction within the automatic flight control subsystem. Traditional automatic flight control boards are typically single-redundant, and their LCD display components have a high failure rate, resulting in low mission reliability and making it difficult to meet the long-endurance, multi-scenario mission requirements of modern aircraft. Summary of the Invention

[0003] Purpose of the invention: To provide a virtual automatic flight control interface human-computer interaction system and method to solve the problem that when the automatic flight control board fails, the pilot cannot continue to perform long-duration flight missions and special scenarios that require autopilot assistance, thereby improving the mission reliability of the automatic flight control subsystem.

[0004] Technical solution:

[0005] A virtual automatic flight control interface human-machine interaction system includes: a cockpit integrated display and control subsystem, multiple command processing units, an automatic flight control board, and a power control device. The cockpit integrated display and control subsystem includes a numeric keypad and a multi-function display. The automatic flight control board is interconnected with the command processing units and the power control device via an HB6096 bus. The virtual interface resides on the multi-function display of the cockpit integrated display and control subsystem. The multi-function display is interconnected with the command processing units via an AFDX network bus, and with the power control device via an HB6096 bus. The command processing units are interconnected with the central alarm system via an AFDX network bus. The numeric keypad of the cockpit integrated display and control system is connected to the multi-function display via an internal system bus and is used to send signals such as target values ​​to the multi-function display.

[0006] A method for human-computer interaction using a virtual automatic flight control interface, the method being executed by means of the aforementioned human-computer interaction system, the method comprising:

[0007] Step 1: After the automatic flight control board fails, activate the backup virtual interface and enter the backup working mode;

[0008] Step 2: After the automatic flight control board is restored from failure, disconnect the backup virtual interface control, exit the backup working mode, and enter the normal working mode.

[0009] Further, step 1 specifically includes:

[0010] Step 11: When the automatic flight control board malfunctions, it sends a fault signal to the command processing unit.

[0011] Step 12: The instruction processing unit disconnects the automatic driving function after receiving the fault signal;

[0012] Step 13: The command processing unit sends the automatic flight control board fault signal to the central alarm system and the cockpit integrated display and control system;

[0013] Step 14: The central alarm system alerts the pilot that the current automatic flight control panel is malfunctioning. The pilot can switch to the virtual interface to continue the automatic flight mission.

[0014] Step 15: After receiving a fault signal from the automatic flight control panel, the cockpit integrated display and control system activates the virtual interface;

[0015] Step 16: The pilot runs the backup working mode through the virtual interface.

[0016] Further, step 14 specifically includes:

[0017] The central alarm system displays an "Autoflight Control Panel Failure" alarm message on the PFD screen, indicating to the pilot that the current Autoflight Control Panel is malfunctioning and that the pilot can switch to the virtual interface to continue the autoflight mission.

[0018] Further, step 15 specifically includes:

[0019] After receiving a fault signal from the automatic flight control board, the cockpit integrated display and control system sends the fault signal to the multi-function display, activates the virtual interface, and controls the "backup" button status light on the virtual interface to turn yellow in preparation.

[0020] Further, step 16 specifically includes:

[0021] When the pilot inputs the command to activate the backup virtual interface by clicking or touching the "Backup" button on the virtual interface, the multifunction display receives a valid status signal for the "Backup" button on the virtual interface, the control button status light turns green, and the automatic flight control system begins to operate in backup mode.

[0022] Further, step 2 specifically includes:

[0023] Step 21: After the automatic flight control board recovers from the fault, it sends an automatic flight control board valid signal to the command processing unit. After receiving the valid signal for 25 consecutive cycles, the command processing unit forwards the automatic flight control board valid signal to the multi-function display.

[0024] Step 22: The multi-function display control virtual interface prompts the pilot that the current automatic flight control board malfunction has been resolved and the pilot can switch back to normal automatic flight control functions;

[0025] Step 23: If you want to continue the current working mode, click the "Backup" button on the virtual interface to input an invalid signal;

[0026] The multi-function display exits the virtual interface after receiving an invalid signal and sends an interface exit signal to the instruction processing unit.

[0027] After receiving the exit signal, the command processing unit sends the current automatic flight mode, target value and other information to the automatic flight control board, lights up the corresponding button lights and display screen of the automatic flight control board, so that the automatic flight control subsystem can continue to control the aircraft to fly according to the previous state;

[0028] Step 24: If you wish to re-engage the normal autopilot function, press the activation button on the autopilot control board. The autopilot control board will send the activation signal to the command processing unit, which will then forward the activation signal to the multifunction display. After receiving the activation signal, the multifunction display will control the virtual interface to exit, and the autopilot control subsystem will operate normally and enter the default working mode.

[0029] Further, step 22 specifically includes: the status light of the "backup" button on the multi-function display control virtual interface changes from green to yellow, indicating to the pilot that the current automatic flight control board has recovered from the fault and can switch back to normal automatic flight control functions.

[0030] Beneficial effects:

[0031] By designing a virtual interface, the problem of autopilot unusable when the automatic flight control panel malfunctions is solved, improving the mission reliability of the automatic flight control subsystem and providing pilots with a convenient and easy-to-use method for selecting autopilot functions. This method allows pilots to continue performing flight missions requiring the automatic flight control subsystem's involvement by activating a virtual automatic flight control panel after the automatic flight control panel malfunctions, thus improving the mission reliability of the automatic flight control subsystem and better meeting the current requirements for long-endurance, multi-scenario missions. Attached Figure Description

[0032] Figure 1 This is a schematic diagram of a virtual automatic flight control interface human-computer interaction system;

[0033] Figure 2 This is a schematic diagram of the virtual interface entry logic;

[0034] Figure 3 This is a schematic diagram of the exit logic for the virtual interface. Detailed Implementation

[0035] To address the aforementioned issues, a virtual interface can be installed on the main flight display (the multi-function display of the cockpit integrated display and control subsystem) to serve as a backup for the automatic flight control panel, thereby improving the reliability of the automatic flight control subsystem and reducing the pilot's workload. As a backup control interface, the virtual interface also possesses the functions of mode / mode selection and the loading and display of altitude, speed, heading, track, and vertical speed / track inclination. However, for safety and ergonomics reasons, the functions of the automatic flight control panel and the virtual interface should mutually inhibit each other. Furthermore, since the virtual interface resides on the main flight display and lacks physical buttons, knobs, dials, or other control components, its operating characteristics and human-machine interaction differ significantly from the automatic flight control panel.

[0036] To solve the above-mentioned technical problems and achieve human-computer interaction in a virtual automatic flight control interface, this invention is implemented through the following method:

[0037] a) Design Requirements Analysis

[0038] 1) Interconnection requirements: In order to realize the function of replacing the automatic flight control board to perform automatic flight tasks, the virtual interface is mainly interconnected with the automatic flight control computing unit and power control device, and data transmission and reception are realized through the bus network;

[0039] 2) Functional requirements: Based on the automatic flight control board function, the virtual interface is set on the integrated display of the onboard avionics system with touch screen or mouse selection functions. It can realize the selection of working mode and mode of automatic flight control subsystem, data loading and display functions. When the virtual interface is switched, the automatic flight control calculation unit sends an alarm signal to the central alarm subsystem to remind the pilot of the current autopilot status.

[0040] b) Virtual Interface Entry and Exit Logic Design

[0041] The virtual interface is activated upon receiving a fault signal from the automatic flight control board forwarded by the command settlement unit. Upon receiving a pilot's activation command, the virtual interface controls the operation in backup mode. Once the automatic flight control board fault is resolved, the main flight control computer forwards a fault recovery signal to the multifunction display and displays a fault recovery message on the virtual interface. When the pilot presses a button on the virtual interface, the virtual interface exits. The command settlement unit then sends the current automatic flight mode, target values, and other information to the automatic flight control board, illuminating the corresponding status lights and displays to continue the automatic flight mission. Alternatively, the pilot can directly press the activation button on the automatic flight control board. Upon receiving the activation signal from the automatic flight control board, the multifunction display controls the virtual interface to exit, and the automatic flight control subsystem operates normally and enters the default working mode.

[0042] c) Virtual Interface Control Logic Design

[0043] The virtual interface can realize all the functions of the automatic flight control board, and has an automatic flight control subsystem working mode selection area, function mode selection area, numerical binding and display area, as well as a virtual interface "backup" button. The function switching logic is consistent with that of the automatic flight control board.

[0044] Taking a quadruple-redundant automatic flight control subsystem of a medium-sized propeller aircraft as an example, this paper designs its virtual interface human-computer interaction system and method.

[0045] 1. This automatic flight control subsystem consists of four command processing units and a dual-channel automatic flight control board. The automatic flight control board is interconnected with the command processing units and the power control device via an HB6096 bus. The virtual interface resides on the multi-function display of the cockpit integrated display and control subsystem, and is interconnected with the command processing units via an AFDX network bus, and with the power control device via an HB6096 bus. The command processing units are interconnected with the central alarm subsystem via an AFDX network bus. The numeric keypad of the cockpit integrated display and control subsystem sends target values ​​and other signals to the multi-function display via the subsystem's internal bus. The interconnection relationships of the virtual interface are as follows: Figure 1 As shown.

[0046] 2. The virtual interface has functions such as activation, working mode, mode selection, data binding, and display. To achieve the above functions, the requirements for the relevant subsystems are as follows:

[0047] 1) The cockpit integrated display and control subsystem must provide a backup interface, and the functions on the interface can be selected via touch or mouse click;

[0048] 2) The cockpit integrated display and control subsystem needs to provide a numerical input interface for numerical input on the virtual interface;

[0049] 3) The cockpit integrated display and control subsystem must have the function of sending data such as operating mode, mode and set values ​​to the automatic flight control subsystem;

[0050] 4) The central alarm subsystem must provide an automatic flight control board fault display alarm function.

[0051] 3. Virtual interface entry logic as follows: Figure 2As shown, when the automatic flight control panel malfunctions, a fault signal is sent to the command processing unit. Upon receiving the fault signal, the command processing unit disconnects the autopilot function. Simultaneously, the automatic flight control panel fault signal is sent to the central alarm subsystem and the cockpit integrated display and control subsystem. The alarm subsystem displays an "Automatic Flight Control Panel Fault" alarm message on the PFD screen, informing the pilot that the current automatic flight control panel is faulty and that they can switch to the virtual interface to continue the automatic flight mission. After receiving the automatic flight control panel fault signal, the cockpit integrated display and control subsystem sends the signal to the multifunction display, activates the virtual interface, and turns the "Backup" button status light on the control interface to yellow in preparation. When the pilot clicks or touches the "Backup" button on the virtual interface, the multifunction display receives a valid "Backup" button status signal, the control button status light turns green, and the automatic flight control subsystem's backup function begins operation.

[0052] 4. Virtual interface exit logic as follows: Figure 3 As shown, after the automatic flight control board recovers from the malfunction, it sends a valid signal to the command processing unit. Upon receiving a valid signal for 25 consecutive cycles, the command processing unit forwards the signal to the multifunction display. The status light of the "Backup" button on the virtual interface of the multifunction display changes from green to yellow, indicating to the pilot that the automatic flight control board has recovered and the pilot can switch back to normal automatic flight control. At this point, the pilot can choose whether to continue the current automatic flight mode. If they choose to continue, they click the "Backup" button on the virtual interface. Upon receiving an invalid "Backup" button signal from the virtual interface, the multifunction display exits the control interface and displays the interface itself. The signal is sent to the command processing unit. Upon receiving an invalid signal, the command processing unit sends the current automatic flight mode, target value, and other information to the automatic flight control board, illuminating the corresponding button lights and display screen on the automatic flight control board, allowing the automatic flight control subsystem to continue controlling the aircraft's flight according to the previous state. If the pilot wishes to re-engage the normal autopilot function, they can press the activation button on the automatic flight control board. The automatic flight control board sends an activation signal to the command processing unit, which then forwards the signal to the multifunction display. Upon receiving this signal, the multifunction display controls the virtual interface to exit, and the automatic flight control subsystem resumes normal operation and enters the default working mode.

[0053] 5. During virtual interface operation, the command processing unit sends the initial target value to the multi-function display, which then displays the initial value on the virtual interface. Simultaneously, the multi-function display sends the automatic flight mode / mode switch signal generated by the pilot's clicks or touches to the command processing unit. The command processing unit, based on the current flight status and the switch signal, activates or pre-positions the automatic flight control subsystem functions. The multi-function display also sends the target setpoint signal input from the numeric keypad to the command processing unit, which performs control law calculations to achieve the tracking and holding function of the automatic flight control subsystem's target value. The switching logic between different modes of the virtual interface is consistent with that of the automatic flight control board.

Claims

1. A virtual automatic flight control interface human interaction method, characterized in that, Comprising: Step 1: after the failure of the automatic flight control panel, activate the backup virtual interface and enter the backup working mode; Step 2: after the failure of the automatic flight control panel is restored, disconnect the backup virtual interface control, exit the backup working mode, and enter the normal working mode, specifically including: Step 21: after the failure of the automatic flight control panel is restored, send the automatic flight control panel valid signal to the command calculation unit, and the command calculation unit forwards the automatic flight control panel valid signal to the multifunction display after receiving the valid signal for 25 cycles; Step 22: the multifunction display controls the virtual interface to prompt the pilot that the current automatic flight control panel failure is restored, and the automatic flight control function can be switched back to normal; Step 23: if the current working mode is continued, click the "backup" button on the virtual interface to input an invalid signal; The multifunction display exits the virtual interface after receiving the invalid signal; and sends an interface exit signal to the command calculation unit; The command calculation unit sends the current automatic flight working mode, target value, and other information to the automatic flight control panel after receiving the exit signal, lights up the corresponding button light and display screen of the automatic flight control panel, and makes the automatic flight control subsystem continue to control the aircraft flight according to the previous state; Step 24: if it is desired to re-access the normal function of the automatic pilot, press the on button on the automatic flight control panel, the automatic flight control panel sends an on signal to the command calculation unit, and the command calculation unit forwards the on signal to the multifunction display, the multifunction display controls the virtual interface to exit after receiving the on signal, the automatic flight control subsystem operates normally and enters the default working mode.

2. The human-machine interaction method of claim 1, wherein, Step 1, specifically including: Step 11: after the failure of the automatic flight control panel, the automatic flight control panel sends a failure signal to the command calculation unit; Step 12: the command calculation unit disconnects the automatic pilot function after receiving the failure signal; Step 13: the command calculation unit sends the automatic flight control panel failure signal to the central warning system and the cockpit integrated display control system; Step 14: the central warning system prompts the pilot that the current automatic flight control panel is faulty and can switch to the virtual interface to continue the automatic flight task; Step 15: the cockpit integrated display control system activates the virtual interface after receiving the automatic flight control panel failure signal; Step 16: the pilot runs the backup working mode through the virtual interface.

3. The human-machine interaction method of claim 2, wherein, Step 14, specifically including: The central warning system displays "automatic flight control panel failure" warning information on the PFD screen, prompting the pilot that the current automatic flight control panel is faulty and can switch to the virtual interface to continue the automatic flight task.

4. The human-machine interaction method of claim 3, wherein, Step 15, specifically including: After receiving the automatic flight control panel failure signal, the cockpit integrated display control system sends the failure signal to the multifunction display, activates the virtual interface, and controls the "backup" button state light on the virtual interface to turn yellow in preparation.

5. The human-machine interaction method of claim 3, wherein, Step 16, specifically including: When the pilot inputs the start-up backup virtual interface instruction by clicking or touching the "backup" button on the virtual interface, the multifunctional display receives the valid state signal of the virtual interface "backup" button, the button state light changes to green, and the automatic flight control system starts to run in the backup mode.

6. The human-machine interaction method of claim 5, wherein, Step 22 specifically comprises: the multifunctional display controls the "backup" button state light of the virtual interface to change from green working state to yellow, prompting the pilot that the current automatic flight control board fault is recovered and the normal automatic flight control function can be switched back.

7. A virtual autopilot control interface human-machine interaction system, characterized in that, The system is used for executing the method in any one of claims 1-6, and the system comprises: a cockpit integrated display control subsystem, a plurality of instruction calculation units, an automatic flight control board, a cockpit integrated display control subsystem, a power control device, wherein the cockpit integrated display control subsystem comprises a digital keyboard and a multifunctional display, the automatic flight control board is cross-linked with the instruction calculation units and the power control device through an HB6096 bus, a virtual interface is resident on the multifunctional display of the cockpit integrated display control subsystem, the multifunctional display is cross-linked with the instruction calculation units through an AFDX network bus, the multifunctional display is cross-linked with the power control device through the HB6096 bus, the instruction calculation units are cross-linked with a central warning system through the AFDX network bus, and the digital keyboard of the cockpit integrated display control system is connected with the multifunctional display through a system internal bus and used for sending a target value signal and the like to the multifunctional display.

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