Agile display and control method for state of airborne avionics equipment

Abstract

The invention belongs to the technical field of aircraft cockpit display control, and discloses an airborne avionics equipment state agile display control method, a power supply hub device and an AAP control the power-on of avionics equipment and send the power-on state to a core machine, the avionics equipment sends fault information detected by self fault detection software to the core machine, and the avionics equipment sends the fault information to the core machine. Performing real-time bus communication between the core machine and the avionics equipment to obtain a communication state of the avionics equipment; the core machine is connected with the display device and displays the power-on state, the communication state and the fault information of the avionics device in a display picture. The power supply state of the power supply hub device, the working state of the power supply module of the avionics equipment and the AAP starting signal state are collected through the core machine to judge whether the avionics equipment is in the power-on state or not, the principle is clear, the implementation mode is simple, and ground crew and pilots can conveniently and rapidly position problems by observing display colors in pictures.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of aircraft cockpit display control, and relates to a display method for avionics in an aircraft cockpit, in particular to an airborne avionics state agile display control method. BACKGROUND

[0002] The current state display of aircraft avionics is not comprehensive and is not displayed on one screen, which is not convenient for pilots to grasp the state information of avionics at any time through one screen. The current cockpit display screen system includes back display, flat display, state display, and lift display, which has a complex structure. Each avionics is arranged in different display screens, and cannot display enough information for pilots to judge the specific state of avionics. Only the normal state or fault state of avionics can be displayed, which is far from enough for pilots to monitor the normal state of avionics, and is not conducive to troubleshooting. SUMMARY

[0003] In order to solve the above problems, the present application provides an airborne avionics state agile display control method, which can monitor the state of airborne avionics in real time and display the state information in real time.

[0004] The technical scheme of the present application is as follows: An airborne avionics state agile display control method, a power hub device, and an AAP control the power-on of avionics and send the power-on state to the core machine. The avionics sends the fault information detected by the self-fault detection software to the core machine. The core machine communicates with the avionics in real time to obtain the communication state of the avionics. The core machine is connected to a display device, and the power-on state, communication state, and fault information of the avionics are displayed in one display screen.

[0005] Further, the avionics includes all avionics installed on the aircraft.

[0006] Further, the power-on state of the avionics is displayed in gray when it is not powered on, the communication state of the avionics is displayed in amber when it is disconnected, and the fault information of the avionics is displayed in red when it is faulty.

[0007] Further, the method specifically comprises the following steps: S1, the power hub device outputs 28V power supply to the airborne avionics through the power supply circuit breaker, and the power hub device collects the power supply circuit breaker state and the power module working state of the avionics, and reports to the core machine; S2, press the avionics button on the AAP panel, the AAP outputs a start signal to the avionics, and the AAP collects the button state and reports to the core machine; S3, after the avionics equipment collects the power supply and starting signal through the power-on control circuit of the internal power module, the power-on starting is started, the self-checking is carried out after the power-on, and the communication with the core machine is waited for after the self-checking is normal; S4, the core machine judges the power-on state of the avionics equipment according to the power supply state of the power hub device and the starting signal reported by the AAP; in the power-on state, the core machine displays the "power supply line" from the power hub device to the avionics equipment in green, the frame of the avionics equipment in green, and the "starting line" from the AAP to the avionics equipment in green; S5, the core machine and the avionics equipment carry out the "handshake" to establish the communication; after the communication is normal, the core machine reports to the display equipment that the state of the avionics equipment is "power-on and online", and the display is green; if the communication is abnormal, the core machine reports to the display equipment that the state of the avionics equipment is "power-on but not online", and the display is amber; S6, after the core machine and the avionics equipment complete the communication, the avionics equipment reports the self-checking state, and the avionics equipment carries out the periodic self-checking; when the self-checking information indicates that the avionics equipment is faulty, the fault information is reported to the core machine; the core machine reports to the display equipment that the state of the avionics equipment is "power-on and online but faulty", and the display is red.

[0008] Further, in S4, the "power supply line" is displayed in gray when the power supply state is abnormal, and the "starting line" is displayed in gray when the starting signal is abnormal.

[0009] Further, in the display picture, the name of the avionics equipment is displayed, and the outer frame is additionally displayed outside the name of the avionics equipment; the connection line is additionally displayed between the outer frames of the avionics equipment.

[0010] Further, the name display of the avionics equipment is divided into four states, i.e. not power-on, power-on but not online, power-on and online but faulty, and power-on and online; the not power-on is displayed in gray, the power-on but not online is displayed in amber, the power-on and online but faulty is displayed in red, and the power-on and online is displayed in green.

[0011] Further, the outer frame display of the avionics equipment is divided into two colors, i.e. green and gray; the green represents that the equipment is power-on, and the gray represents that the equipment is not power-on.

[0012] Further, the connection line display between the outer frames of the avionics equipment is divided into two colors, i.e. green and gray; the green represents that the communication between the avionics equipment is normal, and the gray represents that the communication between the avionics equipment is not normal.

[0013] The advantages of the present application are as follows: 1. The present application judges whether the avionics equipment is in the power-on state according to the power supply state of the power hub device, the power module working state of the avionics equipment and the AAP starting signal state through the core machine, the principle is clear, and the implementation is simple; the ground service personnel and the pilot can quickly locate the problem by observing the display color in the picture.

[0014] 2. By defining the status of avionics equipment and using different colors to distinguish them, pilots can easily and clearly view the operating status of avionics equipment in a timely manner. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. The drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 This is a cross-linking block diagram of the avionics equipment of the present invention.

[0017] Figure 2 This is a status display diagram of the avionics equipment of the present invention.

[0018] Figure 3 This is a schematic diagram of the power-on control circuit for the internal power module of the avionics equipment of the present invention.

[0019] Figure 4 This is a schematic diagram of the power supply fault acquisition circuit of the present invention. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0022] In the description of this invention, it should be noted that the directions or positional relationships indicated by terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" are based on the directions or positional relationships shown in the accompanying drawings and are only for the convenience of describing and simplifying the invention, and should not be construed as limiting the invention. Furthermore, the use of ordinal numbers (e.g., "first and second," etc.) is for distinguishing objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0023] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly, encompassing both direct connection and indirect connection via an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0024] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0025] Example 1: A method for agile display and control of the status of airborne avionics equipment includes a power hub device and an AAP that control the power-on of the avionics equipment and send the power-on status to the core computer. The avionics equipment sends fault information detected by its own fault detection software to the core computer. The core computer communicates with the avionics equipment in real time via a bus to obtain the communication status of the avionics equipment. The core computer is connected to a display device and displays the power-on status, communication status, and fault information of the avionics equipment on a single display screen.

[0026] Avionics equipment includes all avionics equipment installed on the aircraft.

[0027] The power status of avionics equipment is displayed in gray when it is not powered on, in amber when the communication status is disconnected, and in red when there is a fault.

[0028] Specifically, the following steps are included: S1, the power hub device outputs 28V power to the airborne avionics equipment through the power supply circuit breaker. At the same time, the power hub device collects the status of the power supply circuit breaker and the working status of the power modules of the avionics equipment, and reports them to the core machine. S2, press the avionics button on the AAP panel, the AAP outputs a start signal to the avionics equipment, and at the same time the AAP collects the button status and reports it to the core machine; S3: After the avionics equipment receives the power supply and start-up signals through the power-on control circuit of the internal power module, it starts to power on and start up. After power-on, it performs a self-test. After the self-test is normal, it waits to establish communication with the core machine. S4, when the core computer receives the power supply status and start-up signal of the avionics equipment reported by the power hub device and AAP respectively, it determines that the avionics equipment is in the power-on state; when in the power-on state, the core computer displays the "power supply line" from the power hub device to the avionics equipment in green, the frame of the avionics equipment in green, and the "start-up line" from the AAP to the avionics equipment in green. S5: The core engine and avionics equipment establish communication through a "handshake". Once communication is normal, the core engine reports the avionics equipment status to the display device as "Powered and connected to the network", displayed in green. If communication is abnormal, the core engine reports the avionics equipment status as "Powered but not connected to the network", displayed in amber. S6. After the core unit and avionics equipment complete communication, the avionics equipment reports its self-test status. Simultaneously, the avionics equipment performs periodic self-tests. If the self-test information indicates an avionics equipment malfunction, the malfunction information is reported to the core unit. The core unit reports the avionics status to the display device as "Powered and connected to the network, but malfunctioning," and displays it in red.

[0029] In S4, if the power supply status is abnormal, the "Power Supply Line" will be displayed in gray; if the start signal is abnormal, the "Start Line" will be displayed in gray.

[0030] The display screen shows the names of the avionics equipment, with an outer frame around each name and connecting lines between the frames.

[0031] The names of avionics equipment are displayed in four states: not powered on, powered on but not connected to the network, powered on and connected to the network but malfunctioning, and powered on and connected to the network. Not powered on is displayed in gray, powered on but not connected to the network is displayed in amber, powered on and connected to the network but malfunctioning is displayed in red, and powered on and connected to the network is displayed in green.

[0032] The outer frame of the avionics equipment is displayed in two colors: green indicates that the equipment is powered on, and gray indicates that the equipment is not powered on.

[0033] The connection between the outer frames of avionics equipment is displayed in two colors: green indicates that communication between avionics equipment is normal, and gray indicates that communication between avionics equipment is not normal.

[0034] Example 2: This invention relates to a method for controlling and displaying the status of airborne avionics equipment. It provides real-time monitoring of the status of airborne avionics equipment and displays the status information comprehensively and effectively in real time. The status information of the avionics equipment (including power-on status, communication status, fault conditions, etc.) is displayed on a single screen, allowing the pilot to clearly and promptly view the operational status of the avionics equipment. Powering on the airborne avionics equipment is controlled by a power hub and the AAP (Automatic Access Point). The power hub reports power supply information to the core computer, and the AAP reports the power-on start signal to the core computer. Fault information of the avionics equipment itself is detected in real time by its own fault detection software and reported to the core computer. The core computer communicates with the avionics equipment via a bus to monitor the status of the avionics equipment in real time. All the aforementioned avionics equipment statuses are uniformly reported by the core computer to the display device for display. To facilitate pilot observation, the status of the avionics equipment is divided into four states: not powered on, powered on but not connected to the network, powered on and connected to the network but faulty, and powered on and connected to the network, each displayed with a different color to distinguish them.

[0035] A method for status control and agile display of airborne avionics equipment, characterized by comprising the following steps: Step 1: The power hub device outputs 28V power to the airborne avionics equipment through the power circuit breaker. At the same time, the power hub device collects the status of the power circuit breaker and the working status of the power modules of the avionics equipment and reports them to the core machine. Step 2: Press the avionics button on the AAP panel. The AAP will output a start signal to the avionics equipment. At the same time, the AAP will collect the button status and report it to the core unit. Step 3: After the avionics equipment receives the power supply and start-up signals through the power-on control circuit of the internal power module, it starts to power on and start up. After power-on, it performs a self-test. After the self-test is normal, it waits to establish communication with the core machine. Step 4: When the core unit receives the power supply status and start-up signal of the avionics equipment reported by the power hub device and the APP respectively, it determines that the avionics equipment is in the power-on state; the core unit displays the "power supply line" from the power hub device to the avionics equipment in green, the frame of the avionics equipment in green, and the "start-up line" from the AAP to the avionics equipment in green.

[0036] Step 5: The core engine and avionics equipment establish communication through a "handshake". Once communication is normal, the core engine reports the avionics equipment status to the display device as "Powered and connected to the network," displayed in green. If communication is abnormal, the core engine reports the avionics equipment status as "Powered but not connected to the network," displayed in amber. Step 6: After the core unit and avionics equipment complete communication, the avionics equipment reports its self-test status (the working status of each module). Simultaneously, the avionics equipment performs periodic self-tests. If a self-test failure occurs, the fault information is reported to the core unit. The core unit reports the avionics status to the display device as "Powered on and connected to the network, but faulty," and displays it in red.

[0037] The core engine determines whether the avionics equipment is powered on by collecting the power supply status of the power hub and the AAP start signal status. If both signals are valid, the "Power Supply Line" and "Start Line" are displayed in green. If one signal is invalid, it is displayed in gray. Ground crew and pilots can quickly determine the reason why the avionics equipment is not powered on by observing the display colors. If the core engine does not receive a valid start signal from the AAP, it will display the "Start Line" from the AAP to the avionics equipment in gray. Ground crew and pilots can then determine that the AAP start signal has not been output by observing the display colors, prompting them to press the button on the AAP panel.

[0038] The aforementioned avionics equipment status display is divided into three categories: First, the display of the avionics equipment name, which uses four colors to indicate different statuses: not powered on, powered on but not connected to the network, powered on and connected to the network but malfunctioning, and powered on and connected to the network. Not powered on is displayed in gray, powered on but not connected to the network in amber, powered on and connected to the network but malfunctioning in red, and powered on and connected to the network in green. Second, the display of the avionics equipment's outer frame, which uses two colors: green indicates the equipment is powered on, and gray indicates the equipment is not powered on. Third, the display of the connection lines between the equipment, which uses two colors: green indicates normal communication between the equipment, and gray indicates no communication between the equipment. This system is easy to distinguish and displays information on the same screen for convenient observation.

[0039] The power module inside the avionics equipment has a power-on control function. The internal power-on control circuit controls the surge and spike voltage suppression converter (ON / OFF) to realize the power output switching control function. When the power hub device inputs +28V, if the AAP power-on start signal is in the off state, the optocoupler V3 is not conducting, the ON / OFF (enable) pin of the surge and spike voltage suppression converter is pulled low, the output is turned off, and there is no power output. When the AAP power-on start signal is in the closed state, the optocoupler V3 is turned on, the ON / OFF pin of the surge and spike voltage suppression converter is in the floating state, and the power is turned on and output to each module inside the avionics equipment.

[0040] Example 3: like Figure 1 As shown, the power hub device outputs 28V power to the airborne avionics equipment 4 through the power circuit breaker 3. At the same time, the power hub device collects the status of the power circuit breaker 3 and the working status of the power module inside the avionics equipment 4, and reports them to the core computer. When the power circuit breaker 3 is turned on, the core computer turns on the power circuit breaker in the figure and displays the power supply line 2 from the power hub to the avionics equipment in green, indicating that the power hub device is outputting power to the avionics equipment 4. The core computer displays the frame of the avionics equipment 4 in green, indicating that the power module inside the avionics equipment 4 is working normally.

[0041] Press the avionics button on the AAP panel. The AAP will output a start signal to the avionics equipment. At the same time, the AAP will collect the button status and report it to the core computer. The core computer will display the start line 1 output by the AAP to the avionics equipment as green, indicating that the AAP will output a start signal to the avionics equipment terminal 4. After receiving power supply and start-up signals through the power-on control circuit of its internal power module, avionics equipment 4 begins power-on startup. After power-on, it performs a self-test. If the self-test is normal, it waits to establish communication with the core unit. The core unit and avionics equipment establish communication through a "handshake." Once communication is normal, the avionics equipment reports its self-test status (the working status of each module). The core unit determines that avionics equipment 4 is in "power-on and connected to the network," and the connection line 5 between the core unit and avionics equipment is displayed in green, along with avionics equipment 4 itself. If communication is abnormal, the avionics equipment is determined to be in "power-on but not connected to the network," and avionics equipment 4 is displayed in amber, while the connection line between avionics equipment 4 and the core unit is displayed in gray.

[0042] After the core unit and avionics equipment complete communication, the avionics equipment performs periodic self-tests. If a fault is detected during the self-test, the fault information is reported to the core unit. If the core unit determines that the status of avionics equipment 4 is "powered on and connected to the network but faulty", it will display avionics equipment 4 in red.

[0043] The status of avionics equipment is divided into four states: not powered on, powered on but not connected to the network, powered on and connected to the network but malfunctioning, and powered on and connected to the network. Not powered on is displayed in gray, powered on but not connected to the network is displayed in amber, powered on and connected to the network but malfunctioning is displayed in red, and powered on and connected to the network is displayed in green. The four states are displayed by different colors.

[0044] The power supply of avionics equipment has a power-on control function, such as... Figure 3 As shown: The power hub device inputs 28V and 28VG power supply signals. When the button on the AAP panel is pressed, the input AAP- and AAP+ signals are shorted, and the power supply is turned on. When the input AAP signal is disconnected, the power supply is turned off.

[0045] The power-on control circuit of the avionics equipment realizes the power output switching control function by controlling the surge and spike voltage suppression converter (ON / OFF). When the power hub device inputs +28V, if the power-on start signal of the AAP is in the off state, the optocoupler V3 is not turned on, the ON / OFF (enable) pin of the surge and spike voltage suppression converter is pulled low, the output is turned off, and there is no power output. When the AAP power-on control is in the closed state, the optocoupler V3 is turned on, the ON / OFF pin of the surge and spike voltage suppression converter is in the floating state, and the power output is turned on.

[0046] L1, C1, and C2 are backup AAP filter circuits to prevent power supply interference from being transmitted through the AAP signal.

[0047] V3 is an optocoupler. Its normal operating current requires a conduction current greater than 3mA. After conduction, the voltage drop of its input arm is 1.1V. V1 and V2 are TVS diodes, used to absorb any external voltage spikes that may be introduced into the output AAP input signal; R1 is a current-limiting resistor. Optocoupler V3 requires at least 3mA of current to conduct normally. Therefore, with an input voltage of 28VDC, the input arm voltage drop is 1.1V after V3 conducts. To ensure V3 functions properly, the resistance value of R1 is calculated as follows: R1=(28-1.1)÷0.03=8.967kΩcv The resistance value of R1 should not exceed 8.967kΩ; in this circuit, the selected resistance value of R1 is 5kΩ, which meets the requirements.

[0048] like Figure 4 The power hub device uses a power supply fault detection circuit to check whether the power modules inside the avionics equipment are working properly. It uses the output voltage to control the on / off state of the optocoupler, providing a high-level 28V and a low-level 0V signal from the optocoupler's output.

[0049] When the output voltage is normal, optocoupler V5 is turned on, and the fault detection signal outputs a high-level signal of 28V; when the output voltage is faulty, optocoupler V5 is not turned on, and the fault detection signal outputs a low-level signal of 0V.

[0050] R4 is a current-limiting resistor, and its resistance is selected as 1.21kΩ based on calculations.

[0051] V6 is a TVS diode, used to absorb any external voltage spikes that may be introduced into the output fault detection signal.

[0052] R5 is the grounding resistor.

[0053] The above detailed embodiments are a description of the present invention. It should not be considered that the specific embodiments of the present invention are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present invention, and all of these should be considered to fall within the protection scope of the present invention.

Claims

1. A method for agile display and control of the status of airborne avionics equipment, characterized in that, The power hub device and AAP control the power-on of avionics and send the power-on status to the core computer. The avionics send the fault information detected by its own fault detection software to the core computer. The core computer communicates with the avionics in real time via bus to obtain the communication status of the avionics. The core unit is connected to a display device, which displays the power-on status, communication status, and fault information of the avionics equipment on a single screen.

2. The method for agile display and control of the status of airborne avionics equipment according to claim 1, characterized in that, Avionics equipment includes all avionics equipment installed on the aircraft.

3. The method for agile display and control of the status of airborne avionics equipment according to claim 1, characterized in that, The power status of avionics equipment is displayed in gray when it is not powered on, in amber when the communication status is disconnected, and in red when there is a fault.

4. The method for agile display and control of the status of airborne avionics equipment according to claim 3, characterized in that, Specifically, the following steps are included: S1, the power hub device outputs 28V power to the airborne avionics equipment through the power supply circuit breaker. At the same time, the power hub device collects the status of the power supply circuit breaker and the working status of the power modules of the avionics equipment, and reports them to the core machine. S2, press the avionics button on the AAP panel, the AAP outputs a start signal to the avionics equipment, and at the same time the AAP collects the button status and reports it to the core machine; S3: After the avionics equipment receives the power supply and start-up signals through the power-on control circuit of the internal power module, it starts to power on and start up. After power-on, it performs a self-test. After the self-test is normal, it waits to establish communication with the core machine. S4, when the core computer receives the power supply status and start-up signal of the avionics equipment reported by the power hub device and AAP respectively, it determines that the avionics equipment is in the power-on state; when in the power-on state, the core computer displays the "power supply line" from the power hub device to the avionics equipment in green, the frame of the avionics equipment in green, and the "start-up line" from the AAP to the avionics equipment in green. S5: The core engine and avionics equipment establish communication through a "handshake". Once communication is normal, the core engine reports the avionics equipment status to the display device as "Powered and connected to the network", displayed in green; if communication is abnormal, the core engine reports the avionics equipment status as "Powered but not connected to the network", displayed in amber. S6. After the core unit and avionics equipment complete communication, the avionics equipment reports its self-test status. At the same time, the avionics equipment performs periodic self-tests. When the self-test information indicates a fault in the avionics equipment, the fault information is reported to the core unit. The core unit reports the avionics status to the display device as "Powered and connected to the network but faulty," and displays it in red.

5. The method for agile display and control of the status of airborne avionics equipment according to claim 4, characterized in that, In S4, if the power supply status is abnormal, the "Power Supply Line" will be displayed in gray; if the start signal is abnormal, the "Start Line" will be displayed in gray.

6. The method for agile display and control of the status of airborne avionics equipment according to claim 3, characterized in that, The display screen shows the names of the avionics equipment, with an outer frame around each name and connecting lines between the frames.

7. The method for agile display and control of the status of airborne avionics equipment according to claim 6, characterized in that, The names of avionics equipment are displayed in four states: not powered on, powered on but not connected to the network, powered on and connected to the network but malfunctioning, and powered on and connected to the network. Not powered on is displayed in gray, powered on but not connected to the network is displayed in amber, powered on and connected to the network but malfunctioning is displayed in red, and powered on and connected to the network is displayed in green.

8. The method for agile display and control of the status of airborne avionics equipment according to claim 6, characterized in that, The outer frame of the avionics equipment is displayed in two colors: green indicates that the equipment is powered on, and gray indicates that the equipment is not powered on.

9. A method for agile display and control of the status of airborne avionics equipment according to claim 6, characterized in that, The connection between the outer frames of avionics equipment is displayed in two colors: green indicates that communication between avionics equipment is normal, and gray indicates that communication between avionics equipment is not normal.

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