Blanking display method for display elements of sketch page based on flight scene

Abstract

The invention discloses a blanking display method for sketch page display elements based on a flight scene. The method comprises the following steps: receiving electromechanical and other external system data related to the flight scene; determining one or more sketch pages which are being displayed; determining required electromechanical and other external system data according to display elements on the sketch page; and determining a flight scene according to electromechanical and other external system data, setting blanking display of related sketch page display elements when the flight scene meets corresponding display element blanking logic, and otherwise, keeping display of the sketch page display elements. According to the method, the extra system information can be blanked according to the flight scene, and the problem of low aero-crew cognition performance caused by a large amount of extra information concerned by a non-current flight scene when the aero-crew inquires related aircraft system information through a sketch page is solved.

Description

Technical Field

[0001] The invention relates to the field of avionics, and in particular to a display method for a multi-function display window (MFW) in an aircraft cockpit, and in particular to a display method for hiding display elements of a schematic page according to a specific flight scenario. Background Art

[0002] The complexity of system status indication is often proportional to the complexity of avionics system or aircraft system. With the continuous advancement of technology, modern aircraft are developing towards intelligence, the number of onboard sensors is increasing, and the recorded aircraft status information is becoming more and more abundant. On the one hand, this enhances the crew's grasp of the aircraft system status, and on the other hand, it puts higher requirements on the crew to handle more complex information.

[0003] A large amount of information related to the aircraft's electromechanical systems, such as the operating parameters and working status of fuel, power supply, flight control, hydraulics, environmental control, cabin doors, etc., is displayed to the crew in the form of graphics, colors, numerical values ​​or text on the aircraft schematic page, playing an important auxiliary role in the crew's system inspection, monitoring, management and troubleshooting.

[0004] Taking a fixed-wing firefighting aircraft as an example, the relevant information of four engines needs to be displayed simultaneously on the sub-pages of the relevant system diagram pages. In order to reduce the possibility of confusion among the crew, the design of the diagram page often needs to follow the concepts of intuitive form, corresponding position, and covering the entire system status. This makes the diagram page contain many graphics and text display elements with relative position requirements. For example, the fuel system page needs to include the total fuel volume of the whole aircraft, the total consumption, the difference between the left and right fuel volumes, the fuel consumption of each of the four engines, the fuel pipeline and the fuel pump and fuel valve on the pipeline, the drain pipeline and the drain pump and drain valve on the pipeline, etc.; the power system page needs to display the status, voltage, and current information of the eight DC generators corresponding to the four engines, the four AC generators, the DC system ground power supply, the AC system ground power supply, the APU status, the emergency battery status, the flight control battery status, and the status of each bus bar. If a large amount of information of the same system is displayed at the same time, it will often cause the dispersion of attention resources, which is not conducive to the crew to quickly and efficiently identify relevant information. Especially in different flight scenarios, the crew often pays different attention to the information on the schematic page, and the crew will only pay attention to some content in some scenarios during the flight. For example, the crew rarely pays attention to the status of the oil dumping pipeline, oil dumping pump and oil dumping valve related to emergency oil dumping during normal flight, and they are only used in emergency oil dumping missions; the ground power supply and APU status are only observed when the aircraft is on the ground and the engine is not started and external power supply is required, or when the engine is stopped after landing and auxiliary power supply is performed. The relevant power supply status will not be used during the flight.

[0005] Therefore, when the crew confirms the status of each system of the aircraft through the diagram page, it is likely that due to the simultaneous display of a large amount of information that is not of concern in the current flight scenario and the information that is of concern in the current flight scenario, the crew spends more time searching for the information they need to know, resulting in lower cognitive performance. Based on the above situation, the present invention proposes a method for determining the flight scenario based on electromechanical and other external system data, and by hiding the non-concern information in the current flight scenario, the display elements of the diagram page are simplified, the difficulty of the crew to query information is reduced, and cognitive performance is improved. Summary of the invention

[0006] The object of the present invention is to provide a method for hiding display elements of a schematic page based on a flight scenario, which can hide additional system information according to the flight scenario, and overcome the problem that when the crew queries relevant aircraft system information through the schematic page, there is a large amount of additional information that is not concerned with the current flight scenario, resulting in low crew cognitive performance.

[0007] The object of the present invention is achieved through the following technical solutions:

[0008] A method for hiding and displaying display elements of a schematic page based on a flight scene comprises the following steps:

[0009] Step 1: receiving electromechanical and other external system data related to the flight scenario;

[0010] Step 2, determining one or more simplified diagram pages being displayed, and if there is no simplified diagram page, no subsequent blanking judgment is performed;

[0011] Step 3, determining the required electromechanical and other external system data according to the display elements on the determined schematic page;

[0012] Step 4: Determine the flight scenario based on the determined electromechanical and other external system data. When the flight scenario meets the corresponding display element blanking logic, set the display elements of the relevant schematic page to be blanked, otherwise the display elements of the schematic page remain displayed.

[0013] Furthermore, in step four, after the electromechanical and other external system data associated with the flight scene changes, if the conditions for the current display element to be hidden are still met, the corresponding display element continues to remain hidden; if the conditions for the current display element to be hidden are no longer met, the display of the corresponding display element is restored; if the electromechanical and other external system data are invalid, the display element is displayed in an invalid style.

[0014] In some embodiments, electromechanical and other external system data are used as inputs to determine whether display elements on the schematic page are blanked, including the pre-position status of the oil drain valve, the pre-position status of the oil drain pump, the on-off status of the oil drain valve, the on-off status of the oil drain pump, the ground power status, the calibrated airspeed, and the wheel load.

[0015] In some embodiments, when the display elements in the schematic page determined in step three include an oil drain pump, an oil drain valve, and an oil drain pipeline connecting the oil drain pump and the oil drain valve, then in step four, when the relevant electromechanical and other external system data are valid and it is judged that the oil drain pump and the oil drain valve are both in the pre-position state, and the oil drain passage composed of any oil drain pump and the oil drain valve is in the connected state, or the oil drain passages composed of all the oil drain pumps and the oil drain valves are in the disconnected state, it is judged to be an aircraft emergency oil drain flight scene, and the oil drain pump, the oil drain valve, and the oil drain pipeline connecting the oil drain pump and the oil drain valve disappear.

[0016] In some embodiments, when the display elements on the schematic page confirmed in step three include a DC ground power indication, then in step four, when the relevant electromechanical and other external system data are valid and it is judged that the aircraft is on the ground, and the DC power supply voltage is lower than the operating voltage, it is judged as a flight scene before and after the ground power is connected, and the corresponding DC power supply indication display element is blanked.

[0017] In some embodiments, when the display elements on the schematic page confirmed in step three include an AC ground power indication, then in step four, when the relevant electromechanical and other external system data are valid and the aircraft is on the ground, and the AC power voltage is lower than the operating voltage, it is judged as a flight scene before and after the ground power is connected, and the corresponding AC power indication display element is blanked.

[0018] In some embodiments, when the display elements on the schematic page confirmed in step three include an APU indication, then in step four, when the relevant electromechanical and other external system data are valid and the aircraft is on the ground, and the APU power supply voltage is lower than the operating voltage, it is judged to be a flight scenario before and after the auxiliary power system is connected, and the display elements corresponding to the APU indication are blanked.

[0019] In some embodiments, when the display elements on the schematic page confirmed in step three include a rudder limit indication, then in step four, when the airspeed voting value and the main flight control status are valid, and the main flight control is not in degraded mode, and the main flight control is not in direct mode, and the main flight control is not in backup mode, it is judged that the main flight control is operating normally and the rudder indication is blanked.

[0020] In some embodiments, the hidden display of flight scene related schematic page display elements includes the hidden display of directly related display elements and also includes the hidden display of indirectly related display elements.

[0021] The beneficial effects of the present invention are:

[0022] Compared with fixedly displaying the aircraft system information on the schematic page, the technical solution proposed in the present invention hides the system information that is not of concern to the current flight scene, effectively reducing the amount of information displayed on the schematic page at the same time, allowing the crew to find relevant information more quickly and easily, reducing the crew's workload and improving the crew's cognitive performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 The present invention is a flowchart of a method for hiding display elements of a diagram page based on a flight scenario;

[0024] Figure 2 It is a schematic diagram of the fuel discharge pump, fuel discharge valve and fuel discharge pipeline connecting the fuel discharge pump and the fuel discharge valve in the aircraft emergency fuel discharge flight scenario shown in the embodiment, wherein the left side is a schematic diagram of the fuel page before the blanking, and the right side is a schematic diagram of the fuel page after the blanking;

[0025] Figure 3 It is a schematic diagram of the blanking of the ground DC ground power supply, AC ground power supply, and APU indication in the ground stage shown in the embodiment, wherein the left side is a schematic diagram of the power page of the simplified diagram page before blanking, and the right side is a schematic diagram of the power page of the simplified diagram page after blanking;

[0026] Figure 4 It is a schematic diagram of the blanking of the rudder limit deviation indication in the normal working flight scenario of the main flight control shown in the embodiment, wherein the left side is the rudder indication before the effect, and the right side is the rudder indication after the effect;

[0027] Figure 5 An example diagram of an oil drain pump, an oil drain valve, and an oil drain pipeline connecting the oil drain pump and the oil drain valve shown in an embodiment;

[0028] Figure 6 This is an example diagram of the ground DC power indication shown in the embodiment;

[0029] Figure 7 This is an example diagram of ground AC power indication shown in the embodiment;

[0030] Figure 8 This is an example diagram of the APU indication shown in the embodiment;

[0031] Fig. 9 The diagram is a diagram showing the display states and state transition relationships of display elements on a simplified diagram page shown in the embodiment. DETAILED DESCRIPTION

[0032] The present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0033] See also Figure 1 As shown, a method for hiding display elements of a schematic page based on a flight scene shown in this embodiment includes the following steps:

[0034] Step 1: Receive electromechanical and other external system data related to the flight scene. The electromechanical and other external system data are used as inputs for determining whether the display elements on the schematic page are blanked, including the pre-position state of the oil drain valve, the pre-position state of the oil drain pump, the on-off state of the oil drain valve, the on-off state of the oil drain pump, the ground power supply state, the corrected airspeed, the wheel load and other data related to the flight scene determination. Of course, other signals not mentioned here fall within the protection scope of the present invention as long as they are related to the flight scene determination.

[0035] Step 2, determining one or more diagram pages associated with the flight scene being displayed in the multi-function window, if there is no diagram page, no subsequent blanking judgment is performed.

[0036] Step 3, determining the required electromechanical and other external system data according to the display elements on the determined schematic page;

[0037] Step 4: Determine the flight scene based on the determined electromechanical and other external system data. When the flight scene satisfies the corresponding display element blanking logic, set the display elements of the relevant schematic page to be blanked, otherwise the display elements of the schematic page remain displayed. After the electromechanical and other external system data associated with the flight scene changes, if the current display element blanking conditions are still met, the corresponding display element continues to remain blank. If the current display element blanking conditions are no longer met, the display of the corresponding display element is restored. Fig. 9 As shown, there are three display states for the display elements on the relevant schematic page and there is a conversion relationship between them. When it is judged according to the schematic page that the required electromechanical and other external system data are invalid, the display element is in a failed state, and the display element is displayed and displayed in a failed style, such as some crosses, to prompt the pilot that the data is invalid so that the pilot can respond; when it is judged according to the schematic page that the required electromechanical and other external system data are valid, and the determined flight scenario meets the blanking judgment conditions, the display element is in a blanking state; when it is judged according to the schematic page that the required electromechanical and other external system data are valid, and the flight scenario does not meet the blanking judgment conditions, the display element is in a display state.

[0038] The following are some examples of flight scenarios.

[0039] like Figure 2 In the simplified page diagram shown, the display elements include an oil drain pump 4, an oil drain valve 6, and an oil drain pipeline 5 connecting the oil drain pump and the oil drain valve. When the relevant electromechanical and other external system data are valid and it is determined that the oil drain pump and the oil drain valve are both in the pre-position state, and the oil drain passage composed of any oil drain pump and the oil drain valve is in the connected state, or the oil drain passages composed of all the oil drain pumps and the oil drain valves are in the disconnected state, it is determined to be an aircraft emergency oil drain flight scene, the relevant display elements are blanked, and the fuel screen is converted from 11 to 12.

[0040] like Figure 3 The schematic page shown, the display elements include a DC ground power indication 7. When the relevant electromechanical and other external system data are valid and it is determined that the aircraft is on the ground, and the DC power voltage is lower than the operating voltage, preferably lower than 0 to 50 volts, and particularly preferably lower than 10 volts, it is determined to be a flight scene before and after the ground power is connected. The corresponding DC power indication display element is blanked, and the power screen is converted from state 13 to state 14.

[0041] like Figure 3 The schematic page shown, the display elements include an AC ground power indication 9. When the relevant electromechanical and other external system data are valid and the aircraft is on the ground, and the AC power voltage is lower than the operating voltage, preferably lower than 0 to 180 volts, and particularly preferably lower than 20 volts, it is judged as a flight scene before and after the ground power is connected, the corresponding AC power indication display element is blanked, and the power screen is converted from state 13 to state 14.

[0042] like Figure 3 The schematic page shown has display elements including an APU indication 8. When the relevant electromechanical and other external system data are valid and the aircraft is on the ground, and the APU power supply voltage is lower than the operating voltage, preferably lower than 0 to 50 volts, and particularly preferably lower than 10 volts, it is judged to be a flight scenario before and after the auxiliary power system is connected. The display element corresponding to the APU indication is blanked, and the power screen is converted from state 13 to state 14.

[0043] like Figure 4 The schematic page shown has display elements including a rudder limit indication of 10. When the airspeed voting value and the main flight control status are valid, and the main flight control is not in the degraded mode, and the main flight control is not in the direct mode, and the main flight control is not in the backup mode, it is judged that the main flight control is operating normally. The rudder indication is blanked and converted from 15 to 16.

[0044] The hidden display of display elements on the flight scene related schematic page includes the hidden display of directly related display elements and also includes the hidden display of indirectly related display elements, such as the hidden display of labels identifying corresponding elements and units of display values.

[0045] like Figure 5 The display elements shown, the oil drain pump, the oil drain valve and the oil drain pipeline connecting the oil drain pump and the oil drain valve, all indicate the interconnection relationship and working status with each other in the form of icons. When the judgment conditions are met, the graphics of the oil drain pump, the oil drain valve and the oil drain pipeline connecting the oil drain pump and the oil drain valve and the number labels distinguishing multiple pumps and valves are hidden at the same time.

[0046] like Figure 6The display elements shown, the DC ground power indication indicates the ground DC power connection, working status, voltage and current in the form of graphics combined with numerical values. When the judgment conditions are met, the power contactor graphics, power graphics, voltage value, current value, and the label identifying the DC ground power and the numerical unit label are blanked at the same time.

[0047] like Figure 7 The display elements shown, the AC ground power indication indicates the ground AC power connection, working status, voltage, current, and frequency in the form of graphics combined with numerical values. When the judgment conditions are met, the power contactor graphics, power graphics, voltage value, current value, frequency value, and the label identifying the AC ground power and the numerical unit label are blanked at the same time.

[0048] like Figure 8 The display elements shown, APU indication indicates APU power on, working status, voltage, and current in the form of graphics combined with numerical values. When the judgment conditions are met, the power contactor graphics, power graphics, voltage value, current value, and the label identifying the APU power supply and the numerical unit label are blanked at the same time.

[0049] like Figure 4 As shown in the figure, the rudder limit deviation indication indicates the rudder limit deviation range in a graphical form. When the judgment conditions are met, the limit deviation graphic disappears.

[0050] This embodiment cites the oil dumping pump, oil dumping valve and oil dumping pipeline connecting the oil dumping pump and the oil dumping valve in the emergency oil dumping flight scenario; the ground stage, the AC and DC ground power indications before and after the ground power is connected; the ground stage, the APU indication before and after the auxiliary power system is connected; the rudder limit deviation indication in the flight scenario of normal operation of the main flight control. For different flight scenarios, the display elements related to the flight scenario will be different, and they are not listed one by one. They can be set according to the specific situation, but the relevant elements (excluding display elements unrelated to the flight scenario) fall within the protection scope of the present invention.

[0051] It is understandable that those skilled in the art can make equivalent substitutions or changes based on the technical solution and inventive concept of the present invention, and all these changes or substitutions should fall within the protection scope of the claims attached to the present invention.

Claims

1. A method for hiding display elements of a schematic page based on a flight scene, characterized in that The following steps are involved: Step 1: receiving electromechanical and other external system data related to the flight scenario; Step 2, determining one or more simplified diagram pages being displayed, and if there is no simplified diagram page, no subsequent blanking judgment is performed; Step 3, determining the required electromechanical and other external system data according to the display elements on the determined schematic page; Step 4: Determine the flight scenario based on the determined electromechanical and other external system data. When the flight scenario meets the corresponding display element blanking logic, set the display elements of the relevant schematic page to be blanked, otherwise the display elements of the schematic page remain displayed.

2. The method for displaying the hidden elements of a schematic page based on a flight scene according to claim 1, characterized in that In step four, after the electromechanical and other external system data associated with the flight scene changes, if the conditions for the current display element to be hidden are still met, the corresponding display element continues to remain hidden; if the conditions for the current display element to be hidden are no longer met, the display of the corresponding display element is restored; if the electromechanical and other external system data are invalid, the display element is displayed in an invalid style.

3. The method for displaying the hidden elements of a schematic page based on a flight scene according to claim 1, characterized in that The electromechanical and other external system data are used as input to determine whether the display elements on the schematic page are blanked, including the pre-position status of the oil drain valve, the pre-position status of the oil drain pump, the on-off status of the oil drain valve, the on-off status of the oil drain pump, the ground power status, the calibrated airspeed, and the wheel load.

4. The method for hiding display elements of a schematic page based on a flight scene according to claim 1, characterized in that When the display elements in the schematic page determined in step three include an oil drain pump, an oil drain valve and an oil drain pipeline connecting the oil drain pump and the oil drain valve, then in step four, when the relevant electromechanical and other external system data are valid and it is judged that the oil drain pump and the oil drain valve are in the pre-position state, and the oil drain passage composed of any oil drain pump and the oil drain valve is in the connected state, or the oil drain passage composed of all the oil drain pumps and the oil drain valves are in the disconnected state, it is judged to be an aircraft emergency oil drain flight scene, and the oil drain pump, the oil drain valve and the oil drain pipeline connecting the oil drain pump and the oil drain valve disappear.

5. The method for hiding display elements of a schematic page based on a flight scene according to claim 1, characterized in that When the display elements on the schematic page confirmed in step 3 include a DC ground power indication, then in step 4, when the relevant electromechanical and other external system data are valid and it is judged that the aircraft is on the ground, and the DC power voltage is lower than the working voltage, it is judged to be a flight scene before and after the ground power is connected, and the corresponding DC power indication display element is blanked.

6. The method for hiding display elements of a schematic page based on a flight scene according to claim 1, characterized in that When the display elements on the schematic page confirmed in step 3 include an AC ground power indication, then in step 4, when the relevant electromechanical and other external system data are valid and the aircraft is on the ground, and the AC power voltage is lower than the operating voltage, it is judged as a flight scenario before and after the ground power is connected, and the corresponding AC power indication display element is blanked.

7. The method for hiding display elements of a schematic page based on a flight scene according to claim 1, characterized in that When the display elements on the schematic page confirmed in step 3 include APU indications, then in step 4, when the relevant electromechanical and other external system data are valid and the aircraft is on the ground, and the APU power supply voltage is lower than the operating voltage, it is judged as a flight scenario before and after the auxiliary power system is connected, and the display elements corresponding to the APU indication are blanked.

8. The method for hiding display elements of a schematic page based on a flight scene according to claim 1, characterized in that When the display elements on the schematic page confirmed in step 3 include the rudder limit indication, then in step 4, when the airspeed voting value and the main flight control status are valid, and the main flight control is not in degraded mode, and the main flight control is not in direct mode, and the main flight control is not in backup mode, it is judged that the main flight control is working normally and the rudder indication is blanked.

9. The method for hiding display elements of a schematic page based on a flight scene according to claim 1, characterized in that The hidden display of flight scene related schematic page display elements includes the hidden display of directly related display elements and the hidden display of indirectly related display elements.

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