Method and device for displaying state of aircraft battery, electronic equipment and storage medium

Abstract

The application provides a method and device for displaying the state of an aircraft battery, electronic equipment and a storage medium. The method comprises: calculating the average temperature of the aircraft battery; calculating the temperature difference between the temperature of each single battery and the average temperature; if the absolute value of the temperature difference corresponding to any single battery exceeds a first temperature threshold, determining whether the starting duration of the auxiliary power unit of the aircraft exceeds a starting time threshold; if the starting duration exceeds the starting time threshold and the aircraft is in a ground state, issuing a battery pack maintenance instruction; determining whether the average temperature reaches a second temperature threshold; if the average temperature reaches the second temperature threshold, determining whether the average temperature reaches a third temperature threshold; if the average temperature reaches the third temperature threshold, issuing a first-level alarm instruction of the battery pack; and if the average temperature does not reach the second temperature threshold, heating the aircraft battery; and if the average temperature of the heated aircraft battery reaches a fourth temperature threshold, issuing a usable instruction of the battery pack.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and in particular to a method, device, electronic device and storage medium for displaying the status of an aircraft battery. Background Technology

[0002] Lithium-ion batteries, characterized by their high energy density and volumetric efficiency, have become a subject of intense research worldwide, with the aim of replacing nickel-cadmium batteries as the onboard emergency power source for new aircraft. Compared to lead-acid, nickel-argon, and nickel-cadmium batteries, lithium batteries offer significant advantages: high operating voltage (three times that of nickel-cadmium and nickel-argon batteries); high energy density (currently, the thermal conductivity is around 300Wh / kg, and the power density is <2.5kW / kg, six times that of nickel-argon batteries); small size (30% smaller than nickel-argon batteries); low self-discharge rate (only 5%–10% self-discharge per month); no memory effect (deep charge / discharge does not affect battery capacity or lifespan); short charging time (able to handle 1C or higher currents, with high charging efficiency, reaching 80%–90% charge in a short time); and no harmful substances (the batteries are environmentally friendly, not only delivering energy but also avoiding environmental pollution). Unlike other electronic devices, lithium batteries, due to their inherent electrochemical characteristics, are severely affected by overcharging and over-discharging, significantly impacting their lifespan. They are typically designed with charge / discharge controls, and timely maintenance of lithium batteries extends their lifespan. In practical aerospace engineering applications, such as operations at high-altitude, cold-weather airports, lithium batteries require cryogenic heating. During this heating process, the aircraft battery is heated. Currently, aircraft battery testing does not include testing for batteries heated in cryogenic environments, leading to inaccurate battery status assessments by the flight crew and hindering battery maintenance. Summary of the Invention

[0003] This application provides a method, device, electronic device, and storage medium for displaying the status of an aircraft battery, in order to solve the technical problem in existing aircraft technology that the crew cannot accurately obtain the battery status, and thus cannot complete battery maintenance.

[0004] In a first aspect, a method for displaying the status of an aircraft battery is provided, the method comprising:

[0005] The temperature of each individual cell in the aircraft battery is detected, and the average temperature of the aircraft battery is calculated based on the temperature of each individual cell.

[0006] Calculate the temperature difference between the temperature of each individual cell and the average temperature of the aircraft battery;

[0007] Determine whether the absolute value of the temperature difference corresponding to each individual battery exceeds a first temperature threshold. If the absolute value of the temperature difference corresponding to any individual battery exceeds the first temperature threshold, determine whether the start-up time of the aircraft auxiliary power unit exceeds a start-up time threshold. If the start-up time exceeds the start-up time threshold and the aircraft is on the ground, issue a battery pack maintenance instruction.

[0008] The system determines whether the average temperature of the aircraft battery has reached a second temperature threshold. If the average temperature of the aircraft battery has reached the second temperature threshold, it determines whether the average temperature of the aircraft battery has reached a third temperature threshold. If the average temperature of the aircraft battery has reached the third temperature threshold, a first-level battery pack alarm indication is issued. If the average temperature of the aircraft battery has not reached the second temperature threshold, the aircraft battery is heated. If the average temperature of the heated aircraft battery reaches a fourth temperature threshold, a battery pack availability indication is issued.

[0009] In conjunction with the first aspect, in one possible implementation, the step of issuing a battery pack level-one alarm indication if the average temperature of the aircraft battery reaches the third temperature threshold includes: if the average temperature of the aircraft battery reaches the third temperature threshold, obtaining a first duration of the aircraft battery in the state of reaching the third temperature threshold; if the first duration reaches a first duration threshold, issuing a battery pack level-one alarm indication.

[0010] In conjunction with the first aspect, in one possible implementation, the step of issuing a battery pack level one alarm indication if the average temperature of the aircraft battery reaches the third temperature threshold is further included as follows: determining whether the average temperature of the aircraft battery reaches a fifth temperature threshold; and issuing a battery pack level two alarm indication if the average temperature of the aircraft battery reaches the fifth temperature threshold.

[0011] In conjunction with the first aspect, in one possible implementation, the step of issuing a secondary alarm indication for the battery pack if the average temperature of the aircraft battery reaches the fifth temperature threshold includes: if the average temperature of the aircraft battery reaches the fifth temperature threshold, obtaining a second duration of the aircraft battery in the state of reaching the fifth temperature threshold; if the second duration reaches a second duration threshold, issuing a secondary alarm indication for the battery pack.

[0012] In conjunction with the first aspect, in one possible implementation, the step of heating the aircraft battery if the average temperature of the aircraft battery does not reach the second temperature threshold includes: if the average temperature of the aircraft battery does not reach the second temperature threshold, obtaining a third duration of the aircraft battery in the state where the second temperature threshold is not reached; if the third duration reaches the third duration threshold, heating the aircraft battery.

[0013] In conjunction with the first aspect, in one possible implementation, the step of issuing a battery pack availability indication if the average temperature of the heated aircraft battery reaches a fourth temperature threshold includes: if the average temperature of the heated aircraft battery reaches the fourth temperature threshold, obtaining a fourth duration of the heated aircraft battery in the state of reaching the fourth temperature threshold; and if the fourth duration reaches a fourth duration threshold, issuing a battery pack availability indication.

[0014] In conjunction with the first aspect, in one possible implementation, the step of issuing a battery pack maintenance instruction if the startup duration exceeds the startup time threshold and the aircraft is in a ground state includes: if the startup duration exceeds the startup time threshold, determining the air-to-ground state of the aircraft; if the air-to-ground state is a ground state, issuing a battery pack maintenance instruction.

[0015] In conjunction with the first aspect, in one possible implementation, the status display method further includes: acquiring the charge status parameter of the aircraft battery; determining whether the charge status parameter is less than a charge status threshold; if the charge status parameter is less than the charge status threshold, determining whether the aircraft is in a non-emergency power supply state; if the aircraft is in a non-emergency power supply state and the aircraft is in the ground state, issuing a battery pack maintenance instruction.

[0016] In conjunction with the first aspect, in one possible implementation, the status display method further includes: acquiring the battery life parameters of the aircraft battery; determining whether the battery life parameters have reached the life cycle count or the aircraft scheduled maintenance time; if the battery life parameters have reached the life cycle count or the aircraft scheduled maintenance time, and the aircraft is in the ground state, then issuing a battery pack maintenance instruction.

[0017] Secondly, a status display device for an aircraft battery is provided, the status display device comprising:

[0018] A temperature processing module is used to detect the temperature of each individual cell in the aircraft battery and calculate the average temperature of the aircraft battery based on the temperature of each individual cell.

[0019] A temperature difference calculation module is used to calculate the temperature difference between the temperature of each individual battery cell and the average temperature of the aircraft battery.

[0020] The battery pack maintenance instruction generation module is used to determine whether the absolute value of the temperature difference corresponding to each individual battery cell exceeds a first temperature threshold. If the absolute value of the temperature difference corresponding to any individual battery cell exceeds the first temperature threshold, it determines whether the start-up time of the aircraft auxiliary power unit exceeds the start-up time threshold. If the start-up time exceeds the start-up time threshold and the aircraft is on the ground, a battery pack maintenance instruction is issued.

[0021] An average temperature determination module is used to determine whether the average temperature of the aircraft battery has reached a second temperature threshold.

[0022] The battery pack level 1 alarm indication generation module is used to determine whether the average temperature of the aircraft battery has reached a third temperature threshold if the average temperature of the aircraft battery reaches a second temperature threshold, and to issue a battery pack level 1 alarm indication if the average temperature of the aircraft battery reaches the third temperature threshold.

[0023] The battery pack availability indicator generation module is used to heat the aircraft battery if the average temperature of the aircraft battery does not reach a second temperature threshold, and to issue a battery pack availability indicator if the average temperature of the heated aircraft battery reaches a fourth temperature threshold.

[0024] In conjunction with the second aspect, in one possible implementation, the battery pack level-one alarm indication generation module is specifically used to: if the average temperature of the aircraft battery reaches the third temperature threshold, obtain the first duration of the aircraft battery in the state of reaching the third temperature threshold; if the first duration reaches the first duration threshold, issue a battery pack level-one alarm indication.

[0025] In conjunction with the second aspect, in one possible implementation, the status display device further includes a battery pack secondary alarm indication generation module, which is used to: determine whether the average temperature of the aircraft battery has reached a fifth temperature threshold; if the average temperature of the aircraft battery reaches the fifth temperature threshold, then issue a battery pack secondary alarm indication.

[0026] In conjunction with the second aspect, in one possible implementation, the battery pack secondary alarm indication generation module is specifically used to: if the average temperature of the aircraft battery reaches the fifth temperature threshold, obtain the second duration of the aircraft battery in the state of reaching the fifth temperature threshold; if the second duration reaches the second duration threshold, issue a battery pack secondary alarm indication.

[0027] In conjunction with the second aspect, in one possible implementation, the battery pack may be specifically used by the indication generation module to: if the average temperature of the aircraft battery does not reach the second temperature threshold, then obtain a third duration of the aircraft battery in the state where the second temperature threshold is not reached; if the third duration reaches the third duration threshold, then heat the aircraft battery.

[0028] In conjunction with the second aspect, in one possible implementation, the battery pack level-one alarm indication generation module is further configured to: if the average temperature of the heated aircraft battery reaches the fourth temperature threshold, obtain the fourth duration of the heated aircraft battery in the state of reaching the fourth temperature threshold; if the fourth duration reaches the fourth duration threshold, issue a battery pack availability indication.

[0029] In conjunction with the second aspect, in one possible implementation, the battery pack maintenance instruction generation module is specifically used to: determine the air-to-ground status of the aircraft if the startup duration exceeds the startup time threshold; and issue a battery pack maintenance instruction if the air-to-ground status is a ground status.

[0030] In conjunction with the second aspect, in one possible implementation, the status display device further includes: a charge status parameter processing module, which is used to acquire the charge status parameters of the aircraft battery; the battery pack maintenance instruction generation module is further used to: determine whether the charge status parameters are less than a charge status threshold; if the charge status parameters are less than the charge status threshold, determine whether the aircraft is in a non-emergency power supply state; if the aircraft is in a non-emergency power supply state and the aircraft is in the ground state, issue a battery pack maintenance instruction.

[0031] In conjunction with the second aspect, in one possible implementation, the status display device further includes a battery life parameter processing module, which is used to: acquire the battery life parameters of the aircraft battery; the battery pack maintenance instruction generation module is further used to: determine whether the battery life parameters have reached the life cycle count or the aircraft scheduled maintenance time; if the battery life parameters have reached the life cycle count or the aircraft scheduled maintenance time, and the aircraft is in the ground state, then a battery pack maintenance instruction is issued.

[0032] Thirdly, an electronic device is provided, including a memory and a processor, the memory storing a computer program that, when executed by the processor, causes the processor to perform the aircraft battery status display method as described in the first aspect.

[0033] Fourthly, a computer-readable storage medium is provided, storing a computer program that, when executed by a processor, causes the processor to perform the aircraft battery status display method as described in the first aspect.

[0034] This application achieves the following beneficial effects: When the absolute value of the temperature difference corresponding to any single battery cell exceeds the first temperature threshold, it determines whether the start-up time of the aircraft's auxiliary power unit exceeds the start-up time threshold; if the start-up time exceeds the start-up time threshold and the aircraft is on the ground, a battery pack maintenance instruction is issued; this avoids misjudging battery heating caused by the start-up of the auxiliary power unit as a battery malfunction, improving the accuracy of battery status display. By heating the aircraft battery when its average temperature has not reached the second temperature threshold, if the average temperature of the heated aircraft battery reaches the fourth temperature threshold, a battery pack availability indication is issued; this enables accurate battery status display when the battery pack uses the heating function, avoiding inaccurate status display caused by the use of the heating function; by determining whether the average temperature of the aircraft battery reaches the third temperature threshold when its average temperature reaches the second temperature threshold, if the average temperature of the aircraft battery reaches the third temperature threshold, a battery pack level one alarm indication is issued; this avoids battery overheating when the battery pack uses the heating function, further improving the accuracy of battery status display. Attached Figure Description

[0035] 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. Obviously, 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 the structures shown in these drawings without creative effort.

[0036] Figure 1 This is a schematic diagram of the structure of an aircraft battery status display system provided in an embodiment of this application;

[0037] Figure 2 This is a schematic diagram of the structure of an aircraft battery status display system provided in an embodiment of this application;

[0038] Figure 3 This is a schematic diagram of the structure of an aircraft battery status display system provided in an embodiment of this application;

[0039] Figure 4 A flowchart illustrating a method for displaying the status of an aircraft battery, provided in an embodiment of this application;

[0040] Figure 5A flowchart illustrating a method for displaying the status of an aircraft battery, provided in an embodiment of this application;

[0041] Figure 6 A flowchart illustrating a method for displaying the status of an aircraft battery, provided in an embodiment of this application;

[0042] Figure 7 A flowchart illustrating a method for displaying the status of an aircraft battery, provided in an embodiment of this application;

[0043] Figure 8 This is a schematic diagram of the structure of an aircraft battery status display device provided in an embodiment of this application;

[0044] Figure 9 This is a schematic diagram of the structure of an electronic device provided in an embodiment of this application. Detailed Implementation

[0045] The technical solutions in the embodiments of this application will now be described with reference to the accompanying drawings.

[0046] The technical solution of this application is applicable to various scenarios for displaying the status of aircraft batteries. Specifically, the technical solution of this application is applicable to scenarios for displaying the status of aircraft batteries in extremely cold environments. Specifically, the technical solution of this application can be used to detect the temperature of individual aircraft batteries and the aircraft's air-to-ground status when the aircraft is in an extremely cold environment, and to complete the status display of the aircraft battery based on the temperature of the individual aircraft batteries and the aircraft's air-to-ground status.

[0047] In one embodiment, such as Figure 1 As shown, Figure 1 This is a schematic diagram of an aircraft battery status display system provided in an embodiment of this application. The aircraft battery status display system includes a lithium battery unit 10, a lithium battery controller 20, a cockpit display screen 30, and an aircraft bus device 40. The lithium battery unit 10, the cockpit display screen 30, and the aircraft bus device 40 are respectively connected to the lithium battery controller 20.

[0048] The lithium battery unit 10 includes an aircraft battery. The lithium battery unit 10 is used to acquire temperature data of the lithium battery, including the temperature of each individual cell within the aircraft battery and the average temperature of the aircraft battery.

[0049] The aircraft bus device 40 is used to acquire aircraft information, including the aircraft's air-to-ground status, auxiliary power unit start-up information, and emergency power supply status information.

[0050] The lithium battery controller 20 is used to generate battery pack maintenance instructions, battery pack alarm instructions, and / or battery pack availability instructions based on the temperature data of the lithium battery and the aircraft information.

[0051] Specifically, the lithium battery controller 20 is also used for timing the start-up of the aircraft APU (Auxiliary Power Unit), specifically for recording the start-up duration of the aircraft APU after receiving the APU start-up information sent by the aircraft bus device 40. The lithium battery controller 20 is also used to generate battery pack maintenance instructions based on the lithium battery temperature data, the start-up duration of the aircraft APU, and the aircraft's air-to-ground status.

[0052] Specifically, the lithium battery controller 20 is also used for battery SOC (State of charge) estimation to obtain charge state parameters; and battery RUL (Remaining Useful Life) estimation to obtain battery life information; the lithium battery controller 20 is used to generate battery pack maintenance instructions based on the charge state parameters and the aircraft's air-to-ground status, or to generate battery pack maintenance instructions based on battery life information and the aircraft's air-to-ground status.

[0053] Specifically, the lithium battery controller 20 is also used to monitor the operating time of the lithium battery, and the lithium battery controller 20 is used to generate a battery pack alarm indication or a battery pack availability indication based on the operating time and the temperature data of the lithium battery.

[0054] The cockpit display screen 30 is used for battery pack maintenance instructions, battery pack alarm instructions, and / or battery pack availability instructions.

[0055] Specifically, the cockpit display screen 30 is located inside the cockpit.

[0056] In this embodiment, compared to setting the display screen that displays the battery pack maintenance indication, battery pack alarm indication, and / or battery pack availability indication in the non-cockpit area, by setting the display screen that displays the battery pack maintenance indication, battery pack alarm indication, and / or battery pack availability indication in the cockpit, the battery pack maintenance indication, battery pack alarm indication, and / or battery pack availability indication can be accurately and timely obtained even when the lithium battery pack 110 is heated in a cold environment.

[0057] In one embodiment, such as Figure 2 As shown, Figure 2This is a schematic diagram of the structure of an aircraft battery status display system provided in an embodiment of this application. The lithium battery unit 10 includes a lithium battery pack 110, a temperature detection unit 120 for detecting the temperature of the lithium battery pack 110, and a heating unit 130 for heating the lithium battery pack 110. The input terminal of the temperature detection unit 120 is connected to the lithium battery pack 110, and the output terminal of the temperature detection unit 120 is connected to the lithium battery controller 20. The input terminal of the heating unit 130 is connected to the lithium battery controller 20. The lithium battery pack 110 includes individual cells 1, 2, ..., n. The temperature detection unit 120 includes temperature sensors corresponding to each individual cell 1, 2, ..., n. After the temperature sensors acquire the temperature T1 of individual cell 1, the temperature T2 of individual cell 2, and the temperature Tn of individual cell n, they send the temperatures T1, T2, and Tn to the lithium battery controller 20. The lithium battery controller 20 controls the start or stop of the heating unit 130 based on the individual cell temperatures sent by the temperature sensors. It should be noted that the temperature detection unit 120 can also be composed of other devices or integrated or packaged devices with temperature detection functions.

[0058] In one embodiment, such as Figure 3 As shown, Figure 3 This is a schematic diagram of an aircraft battery status display system provided in an embodiment of this application. The cockpit display screen 30 includes a maintenance instruction area 310, an alarm instruction area 320, and an availability instruction area 330. The maintenance instruction area 310 is used to display battery pack maintenance instructions, the alarm instruction area 320 is used to display a primary or secondary alarm instruction for the battery pack, and the availability instruction area 330 is used to display a battery pack availability indicator.

[0059] The aircraft bus device 40 sends the aircraft's air-to-ground status, auxiliary power unit start-up information, and emergency power supply status information to the lithium battery controller 20. The lithium battery controller 20 generates battery pack maintenance instructions, battery pack level 1 alarm instructions, battery pack level 2 alarm instructions, and / or battery pack availability instructions based on the data sent by the aircraft bus device 40 and the data sent by the lithium battery unit 10.

[0060] In one embodiment, this application proposes a method for displaying the status of an aircraft battery. This method can... Figures 1-3 The aforementioned aircraft battery status display system is implemented.

[0061] In one embodiment, this application proposes a method for displaying the status of an aircraft battery to solve the technical problem in existing aircraft technology where the crew cannot accurately obtain the battery status, thus making it impossible to complete battery maintenance. The status display method includes: detecting the temperature of each individual cell in the aircraft battery and calculating the average temperature of the aircraft battery based on the temperature of each individual cell; calculating the temperature difference between the temperature of each individual cell and the average temperature of the aircraft battery; determining whether the absolute value of the temperature difference corresponding to each individual cell exceeds a first temperature threshold; if the absolute value of the temperature difference corresponding to any individual cell exceeds the first temperature threshold, determining whether the start-up time of the aircraft auxiliary power unit exceeds a start-up time threshold; if the start-up time exceeds the start-up time threshold and the aircraft is on the ground, issuing a battery pack maintenance instruction; determining whether the average temperature of the aircraft battery reaches a second temperature threshold; if the average temperature of the aircraft battery reaches the second temperature threshold, determining whether the average temperature of the aircraft battery reaches a third temperature threshold; if the average temperature of the aircraft battery reaches the third temperature threshold, issuing a battery pack level one alarm instruction; if the average temperature of the aircraft battery does not reach the second temperature threshold, heating the aircraft battery; if the average temperature of the heated aircraft battery reaches a fourth temperature threshold, issuing a battery pack availability instruction.

[0062] In this embodiment, as Figure 4 As shown, Figure 4 This is a flowchart illustrating a method for displaying the status of an aircraft battery, provided in an embodiment of this application. The status display method includes:

[0063] Step S401: Detect the temperature of each individual cell in the aircraft battery.

[0064] Among them, aircraft batteries can be Figure 3 The lithium battery pack 110 in the aircraft battery status display system shown can be a single cell 1 to a single cell n in the lithium battery pack 110.

[0065] Specifically, it can be done through Figure 3 The temperature detection unit 120 in the aircraft battery status display system detects the temperature of each individual cell in the aircraft battery.

[0066] Step S402: Calculate the average temperature of the aircraft battery based on the temperature of each individual cell.

[0067] Once the temperature of each individual cell in the aircraft battery is detected, the average temperature of the aircraft battery can be calculated based on the temperature of each individual cell.

[0068] Specifically, the average temperature of the aircraft battery is calculated according to the following average temperature calculation formula:

[0069]

[0070] Among them, T t h represents the average temperature of the aircraft battery, T i Let be the temperature of the i-th individual cell in the aircraft battery, and n be the total number of individual cells in the aircraft battery.

[0071] Specifically, after calculating the average temperature of the aircraft battery, step S403 and / or step S408 can be executed.

[0072] Step S403: Calculate the temperature difference between the temperature of each individual cell and the average temperature of the aircraft battery.

[0073] After calculating the average temperature of the aircraft battery, the temperature difference between the temperature of each individual cell and the average temperature of the aircraft battery is calculated according to the following formula:

[0074] ΔT i =T i -T t h;

[0075] Where, ΔT i Let T be the temperature difference between the temperature of the i-th individual cell in the aircraft battery and the average temperature of the aircraft battery. i T represents the temperature of the i-th individual cell within the aircraft's battery. t h represents the average temperature of the aircraft battery.

[0076] Step S404: Determine whether the absolute value of the temperature difference corresponding to each individual battery cell exceeds the first temperature threshold.

[0077] The absolute value of the temperature difference corresponding to each individual cell is used to reflect the temperature consistency of the aircraft's battery. The smaller the absolute value of the temperature difference corresponding to each individual cell, the better the temperature consistency of the aircraft's battery and the healthier the aircraft battery is; the larger the absolute value of the temperature difference corresponding to each individual cell, the worse the temperature consistency of the aircraft's battery and the less healthy the aircraft battery is.

[0078] The first temperature threshold reflects the maximum absolute value of the temperature difference for each individual cell, and the absolute value of the temperature difference can fluctuate from zero to the first temperature threshold. If the absolute value of the temperature difference for any individual cell exceeds the first temperature threshold, it indicates that the temperature consistency of the aircraft battery exceeds the safe range, posing a safety risk. If the absolute value of the temperature difference for no individual cell exceeds the first temperature threshold, it indicates that the temperature consistency of the aircraft battery is within the safe range, there is no safety risk, and the aircraft battery can continue to be used.

[0079] Specifically, if the absolute value of the temperature difference corresponding to any single cell exceeds the first temperature threshold, then step S405 is executed; if the absolute value of the temperature difference corresponding to any single cell does not exceed the first temperature threshold, then it indicates that there is no safety risk to the aircraft battery, and step S401 is executed to detect the temperature of each single cell in the aircraft battery.

[0080] Step S405: Determine whether the start-up time of the aircraft's auxiliary power unit exceeds the start-up time threshold.

[0081] Among them, the start-up time of the aircraft auxiliary power unit is used to reflect the start-up status of the aircraft auxiliary power unit; the start-up time threshold is used to reflect the time required for the aircraft auxiliary power unit to start up completely.

[0082] Specifically, the timing begins after the aircraft's auxiliary power unit (APU) is started. If the start-up time exceeds the start-up time threshold, it indicates that the APU has started successfully; if the start-up time does not exceed the start-up time threshold, it indicates that the APU has not started successfully.

[0083] Specifically, if the start-up time of the aircraft's auxiliary power unit (APU) exceeds the start-up time threshold, it indicates that the APU has started successfully. This means the current temperature uniformity of the aircraft battery exceeding the safe range is not caused by the APU's start-up, but rather by the aircraft battery itself. If the start-up time of the APU does not exceed the start-up time threshold, it indicates that the APU has not started successfully. This means the current temperature uniformity of the aircraft battery exceeding the safe range is caused by overheating from the APU's start-up, and the aircraft battery itself is not faulty.

[0084] Specifically, if the startup time of the aircraft's auxiliary power unit exceeds the startup time threshold, then step S407 is executed; if the startup time of the aircraft's auxiliary power unit does not exceed the startup time threshold, then step S401 is executed.

[0085] Step S406: Determine whether the aircraft is on the ground.

[0086] The ground status indicator is used to indicate that the aircraft is on the ground and has not taken off.

[0087] Specifically, if it is determined that the temperature uniformity of the aircraft battery is exceeding the safe range due to the aircraft battery itself, then it is determined whether the aircraft is on the ground. If the aircraft is on the ground, a battery maintenance instruction is issued, i.e., step S408 is executed. If the aircraft is not on the ground, the issuance of the battery maintenance instruction is suppressed, i.e., step S407 is executed; the battery maintenance instruction is issued again when the aircraft is on the ground.

[0088] Step S407, Battery pack maintenance indication suppressed.

[0089] Among them, battery pack maintenance instruction suppression means temporarily not sending battery pack maintenance instructions.

[0090] Step S408: Issue a battery pack maintenance instruction.

[0091] Among them, battery pack maintenance instructions can be obtained through Figure 3 The lithium battery controller 20 in the aircraft battery status display system issues battery pack maintenance instructions via [the system]. Figure 3 The maintenance instruction area 310 of the aircraft battery status display system is shown.

[0092] Step S409: Determine whether the average temperature of the aircraft battery has reached the second temperature threshold.

[0093] Specifically, after detecting the temperature of each individual cell in the aircraft battery and calculating the average temperature of the aircraft battery based on the temperature of each individual cell, it is possible to determine whether the aircraft battery is in a low-temperature state based on the average temperature of the aircraft battery.

[0094] The second temperature threshold is the critical value for whether the aircraft battery is in a low temperature state. If the average temperature of the aircraft battery reaches the second temperature threshold, it means that the aircraft battery is not in a low temperature state; if the average temperature of the aircraft battery does not reach the second temperature threshold, it means that the aircraft battery is in a low temperature state.

[0095] Specifically, if the aircraft battery is in a low-temperature state, it needs to be heated to ensure that the aircraft battery can release sufficient electrical energy, that is, to execute step S412. If the aircraft battery is not in a low-temperature state, it is necessary to further determine whether the aircraft battery is in an over-temperature state, that is, to execute step S410.

[0096] Step S410: Determine whether the average temperature of the aircraft battery has reached the third temperature threshold.

[0097] The third temperature threshold is the critical value for determining whether the aircraft battery is in a Level 1 over-temperature state. If the average temperature of the aircraft battery reaches the third temperature threshold, it indicates that the aircraft battery is in a Level 1 over-temperature state. If the aircraft battery is in a Level 1 over-temperature state, a Level 1 battery pack alarm indication is issued, i.e., step S411 is executed. If the aircraft battery is not in a Level 1 over-temperature state, it means that the aircraft battery is neither too cold nor too hot, and is in normal working condition; at this time, the step of detecting the temperature of each individual cell in the aircraft battery continues, i.e., step S401 is executed.

[0098] Step S411: Issue a first-level alarm indication for the battery pack.

[0099] Among them, the first-level alarm indication can be obtained through Figure 3 The lithium battery controller 20 in the aircraft battery status display system issued a level one alarm indication via [the system]. Figure 3 The alarm indication area 320 of the aircraft battery status display system is shown.

[0100] Step S412: Heat the aircraft battery.

[0101] When the aircraft battery is in a low temperature state, it needs to be heated.

[0102] Specifically, it can be done through Figure 3 The aircraft battery status display system shown in Figure 130 heats the aircraft battery.

[0103] Step S413: Determine whether the average temperature of the heated aircraft battery reaches the fourth temperature threshold.

[0104] The fourth temperature threshold is used to indicate whether the aircraft battery is in a usable state. If the average temperature of the heated aircraft battery reaches the fourth temperature threshold, it indicates that the battery pack is in a usable state, and a battery pack availability indication is issued, i.e., step S414 is executed. If the average temperature of the heated aircraft battery does not reach the fourth temperature threshold, it indicates that the battery pack is in an unusable state, and the aircraft battery needs to be heated further, i.e., step S412 is executed.

[0105] Step S414: Issue a battery pack availability indication.

[0106] Among them, the battery pack availability indicator can be accessed via Figure 3 The lithium battery controller 20 in the aircraft battery status display system indicates that the battery pack is available. Figure 3 The available indicator area 330 of the aircraft battery status display system is shown.

[0107] This application proposes a method for displaying the status of an aircraft battery. By determining whether the start-up time of the auxiliary power unit (APU) exceeds a start-up time threshold when the absolute value of the temperature difference corresponding to any individual battery exceeds a first temperature threshold, and if the start-up time exceeds the start-up time threshold while the aircraft is on the ground, a battery pack maintenance instruction is issued. This avoids misjudging battery heating caused by APU startup as a battery malfunction, improving the accuracy of battery status display. By heating the aircraft battery when its average temperature has not reached a second temperature threshold, and if the average temperature of the heated aircraft battery reaches a fourth temperature threshold, a battery pack availability indication is issued. This enables accurate battery status display when the battery pack heating function is used, avoiding inaccurate status display caused by the use of the heating function. By determining whether the average temperature of the aircraft battery reaches a third temperature threshold when the average temperature reaches the second temperature threshold, and if the average temperature of the aircraft battery reaches the third temperature threshold, a first-level battery pack alarm indication is issued. This avoids battery overheating when the battery pack heating function is used, further improving the accuracy of battery status display.

[0108] In some embodiments, the step of issuing a battery pack level one alarm indication if the average temperature of the aircraft battery reaches the third temperature threshold includes: if the average temperature of the aircraft battery reaches the third temperature threshold, obtaining a first duration of the aircraft battery in the state of reaching the third temperature threshold; if the first duration reaches a first duration threshold, issuing a battery pack level one alarm indication.

[0109] If the average temperature of the aircraft battery is detected to reach the third temperature threshold, the timing function is activated to obtain the duration of the aircraft battery in the state where the average temperature reaches the third temperature threshold, and this duration is recorded as the first duration.

[0110] The first duration threshold is the longest time that the aircraft battery can remain in the state where the average temperature reaches the third temperature threshold. If the first duration threshold is reached, it means that the aircraft battery has entered the first-level over-temperature state, and a first-level alarm indication for the battery pack needs to be issued.

[0111] Specifically, the third temperature threshold can be 60℃, and the first duration threshold can be 1 minute. The timing function can be implemented through... Figure 3 The lithium battery controller 20 in the aircraft battery status display system is now complete.

[0112] In this embodiment, by performing a threshold judgment on the first duration of the aircraft battery in the state of reaching the third temperature threshold, it is possible to avoid over-temperature misjudgment caused by transient temperature rise of the aircraft battery at a certain moment, thereby improving the accuracy of aircraft battery status display.

[0113] In some embodiments, such as Figure 5 As shown, Figure 5 This is a flowchart illustrating a method for displaying the status of an aircraft battery according to an embodiment of this application. The step of issuing a first-level alarm indication for the battery pack if the average temperature of the aircraft battery reaches the third temperature threshold is followed by:

[0114] Step S415: Determine whether the average temperature of the aircraft battery has reached the fifth temperature threshold.

[0115] The fifth temperature threshold is the critical value for determining whether the aircraft battery is in a level 2 over-temperature state. If the average temperature of the aircraft battery reaches the fifth temperature threshold, it indicates that the aircraft battery is in a level 2 over-temperature state. If the aircraft battery is in a level 2 over-temperature state, a level 2 battery pack alarm indication is issued, i.e., step S416 is executed. If the average temperature of the aircraft battery does not reach the fifth temperature threshold, it indicates that the aircraft battery is in a level 1 over-temperature state, but not in a level 2 over-temperature state; at this time, the step of detecting the temperature of each individual cell in the aircraft battery continues, i.e., step S401 is executed.

[0116] Specifically, there is a hierarchical relationship between Level 1 and Level 2 overheating states. Level 1 overheating state is lower than Level 2 overheating state, meaning that Level 2 overheating state has a higher temperature than Level 1 overheating state.

[0117] Step S416: Issue a secondary alarm indication for the battery pack.

[0118] Among them, the battery pack secondary alarm indication can be... Figure 3 The lithium battery controller 20 in the aircraft battery status display system indicates that a secondary battery pack alarm can be triggered. Figure 3 The alarm indication area 320 of the aircraft battery status display system is shown.

[0119] In this embodiment, by determining whether the aircraft battery is in a level 2 over-temperature state based on the level 1 over-temperature state, the status of the aircraft battery can be more accurately determined, improving the accuracy of the aircraft battery status display, and thus enabling accurate maintenance of the aircraft battery.

[0120] In some embodiments, the step of issuing a secondary alarm indication for the battery pack if the average temperature of the aircraft battery reaches the fifth temperature threshold includes: if the average temperature of the aircraft battery reaches the fifth temperature threshold, obtaining a second duration of the aircraft battery in the state of reaching the fifth temperature threshold; if the second duration reaches a second duration threshold, issuing a secondary alarm indication for the battery pack.

[0121] If the average temperature of the aircraft battery is detected to reach the fifth temperature threshold, the timing function is activated to obtain the duration of the aircraft battery in the state where the average temperature reaches the fifth temperature threshold, and this duration is recorded as the second duration.

[0122] The second duration threshold is the longest time that the aircraft battery can remain in the state where the average temperature reaches the fifth temperature threshold. If the second duration threshold is reached, it indicates that the aircraft battery has entered the second-level over-temperature state, at which point a second-level battery alarm indication needs to be issued.

[0123] Specifically, the fifth temperature threshold can be 70℃, and the second duration threshold can be 2 seconds. The timing function can be implemented through... Figure 3 The lithium battery controller 20 in the aircraft battery status display system is now complete.

[0124] In this embodiment, by performing a threshold judgment on the second duration of the aircraft battery in the state of reaching the fifth temperature threshold, it is possible to avoid over-temperature misjudgment caused by transient temperature rise of the aircraft battery at a certain moment, thereby improving the accuracy of aircraft battery status display.

[0125] In some embodiments, the step of heating the aircraft battery if the average temperature of the aircraft battery does not reach the second temperature threshold includes: if the average temperature of the aircraft battery does not reach the second temperature threshold, obtaining a third duration of the aircraft battery in the state where the second temperature threshold is not reached; if the third duration reaches the third duration threshold, heating the aircraft battery.

[0126] If the average temperature of the aircraft battery does not reach the second temperature threshold, it indicates that the aircraft battery is not in an overheated state, but may be in a low-temperature state. In this case, a timing function is activated to obtain the duration of the aircraft battery's average temperature not reaching the second temperature threshold, and this duration is recorded as the third duration. By recording the third duration of the aircraft battery, it is determined whether the aircraft battery experienced a transient temperature drop at a certain moment. If the temperature drop time is very short, it indicates that the aircraft battery has not truly entered a low-temperature state.

[0127] The third duration threshold is the longest time that the aircraft battery can remain in a state where the average temperature has not reached the second temperature threshold. If the third duration reaches the second duration threshold, it means that the aircraft battery has entered a low temperature state, and the aircraft battery needs to be heated.

[0128] Specifically, the second temperature threshold can be -15℃, and the third duration threshold can be 5 seconds. The timing function can be implemented through... Figure 3 The lithium battery controller 20 in the aircraft battery status display system is now complete.

[0129] In this embodiment, by performing a threshold judgment on the third duration of the aircraft battery in a state where the second temperature threshold has not been reached, it is possible to avoid false low-temperature judgments caused by transient cooling of the aircraft battery at a certain moment, thereby improving the accuracy of the aircraft battery status display.

[0130] In some embodiments, the step of issuing a battery pack availability indication if the average temperature of the heated aircraft battery reaches a fourth temperature threshold includes: if the average temperature of the heated aircraft battery reaches the fourth temperature threshold, obtaining a fourth duration of the heated aircraft battery in the state of reaching the fourth temperature threshold; and if the fourth duration reaches a fourth duration threshold, issuing a battery pack availability indication.

[0131] When the aircraft battery is overheated, its temperature after heating can be detected simultaneously, and its average temperature after heating can be calculated. If the average temperature of the heated aircraft battery reaches the fourth temperature threshold, and the fourth duration of the heated aircraft battery at the fourth temperature threshold reaches the fourth duration threshold, it indicates that the current battery temperature can ensure stable battery discharge, and a battery pack availability indicator is issued.

[0132] In this embodiment, by determining the fourth duration of the heated aircraft battery when it reaches the fourth temperature threshold, the temperature of the heated aircraft battery can be accurately determined, thereby improving the accuracy of the aircraft battery status display and the safety of the aircraft battery.

[0133] In some embodiments, the step of issuing a battery pack maintenance instruction if the startup duration exceeds the startup time threshold and the aircraft is in a ground state includes: if the startup duration exceeds the startup time threshold, determining the air-to-ground state of the aircraft; if the air-to-ground state is a ground state, issuing a battery pack maintenance instruction.

[0134] The aircraft's air-to-ground status indicates whether the aircraft is on the ground or not. If the air-to-ground status is "ground," it means the aircraft is on the ground; if the air-to-ground status is "non-ground," it means the aircraft is not on the ground.

[0135] Specifically, if the start-up time of the aircraft's auxiliary power unit (APU) exceeds the start-up time threshold, it indicates that the APU has completed its startup. This further suggests that the current battery temperature uniformity exceeding the safe range is not caused by the APU startup, but rather by the aircraft battery itself. In this case, if the aircraft is in a ground-based state, a battery maintenance instruction will be issued immediately; if the aircraft is in a non-ground-based state, the instruction will be issued when the aircraft is in a ground-based state.

[0136] In this embodiment, by determining the aircraft's air-to-ground status, it is possible to avoid issuing battery pack maintenance instructions while the aircraft is in flight, thereby avoiding impacting flight personnel and improving flight safety.

[0137] In some embodiments, the status display method further includes: acquiring the charge status parameter of the aircraft battery; determining whether the charge status parameter is less than a charge status threshold; if the charge status parameter is less than the charge status threshold, determining whether the aircraft is in a non-emergency power supply state; if the aircraft is in a non-emergency power supply state and the aircraft is in the ground state, issuing a battery pack maintenance instruction.

[0138] In this embodiment, as Figure 6 As shown, Figure 6 This is a flowchart illustrating a method for displaying the status of an aircraft battery, provided in an embodiment of this application. The status display method further includes:

[0139] Step S601: Obtain the charge state parameters of the aircraft battery.

[0140] Among them, the state of charge (SOC) parameter indicates the remaining charge of the aircraft battery. The SOC parameter can be obtained through... Figure 3 The status of the aircraft battery is obtained from the aircraft bus device 40 in the aircraft battery status display system shown.

[0141] Step S602: Determine whether the charge state parameter is less than the charge state threshold.

[0142] The charge state threshold is used to indicate the minimum charge level of the aircraft battery. If the charge state parameter is less than the charge state threshold, it indicates that the remaining charge level of the aircraft battery is too low. In this case, it is necessary to determine whether the aircraft is in an emergency power supply state, i.e., to execute step S603.

[0143] Step S603: Determine whether the aircraft is in emergency power supply mode.

[0144] The emergency power supply status refers to a state where the aircraft lacks energy supply. If the aircraft is in an emergency power supply status, it means that using the aircraft battery for power is necessary, and the aircraft battery cannot be stopped supplying power; that is, step S604 continues. If the aircraft is in a non-emergency power supply status, it means that the aircraft battery can be stopped supplying power; in this case, step S406 is executed to determine whether the aircraft is on the ground.

[0145] In step S604, the aircraft battery continues to provide power.

[0146] Step S406: Determine whether the aircraft is on the ground.

[0147] The ground status indicator is used to indicate that the aircraft is on the ground and has not taken off.

[0148] Specifically, if it is determined that the aircraft is in a non-emergency power supply state, then it is determined whether the aircraft is on the ground. If the aircraft is on the ground, a battery pack maintenance instruction is issued, i.e., step S408 is executed. If the aircraft is not on the ground, the issuance of the battery pack maintenance instruction is suppressed, i.e., step S407 is executed; the battery pack maintenance instruction is issued only when the aircraft is on the ground.

[0149] Step S407, Battery pack maintenance indication suppressed.

[0150] Among them, battery pack maintenance instruction suppression means temporarily not sending battery pack maintenance instructions.

[0151] Step S408: Issue a battery pack maintenance instruction.

[0152] Among them, battery pack maintenance instructions can be obtained through Figure 3 The lithium battery controller 20 in the aircraft battery status display system issues battery pack maintenance instructions via [the system]. Figure 3 The maintenance instruction area 310 of the aircraft battery status display system is shown.

[0153] In this embodiment, by obtaining the charge state parameters of the aircraft battery to indicate the status of the aircraft battery, the comprehensiveness of the status display can be effectively improved, thereby improving the accuracy of the status display.

[0154] In some embodiments, the status display method further includes: acquiring the battery life parameters of the aircraft battery; determining whether the battery life parameters have reached the life cycle count or the aircraft scheduled maintenance time; if the battery life parameters have reached the life cycle count or the aircraft scheduled maintenance time, and the aircraft is on the ground, then issuing a battery pack maintenance instruction.

[0155] In this embodiment, as Figure 7 As shown, Figure 7 This is a flowchart illustrating a method for displaying the status of an aircraft battery, provided in an embodiment of this application. The status display method further includes:

[0156] Step S701: Obtain the battery life parameters of the aircraft battery.

[0157] Among these, battery life parameters include the current number of battery life cycles and the interval between scheduled maintenance. Battery life parameters can be obtained through... Figure 3 The status of the aircraft battery is obtained from the aircraft bus device 40 in the aircraft battery status display system shown.

[0158] Step S702: Determine whether the battery life parameter has reached the life cycle number.

[0159] Among them, the life cycle count refers to the number of times an aircraft battery can undergo repeated charge and discharge cycles.

[0160] Specifically, after obtaining the battery life parameters of the aircraft battery, it can be determined whether the current life cycle count of the aircraft battery has reached the life cycle count. If the current life cycle count of the aircraft battery has reached the life cycle count, it means that the life of the aircraft battery is about to end and maintenance and replacement are required. At this time, continue to execute step S406.

[0161] Step S703: Determine whether the battery life parameters have reached the aircraft's scheduled maintenance time.

[0162] Aircraft scheduled maintenance time refers to the time allotted for regular aircraft maintenance.

[0163] Specifically, after obtaining the battery life parameters of the aircraft battery, it can be determined whether the time remaining before the scheduled maintenance of the aircraft battery has reached the scheduled maintenance time. If the time remaining before the scheduled maintenance of the aircraft battery has reached the scheduled maintenance time, it indicates that the aircraft needs to be inspected. At this time, continue to execute step S406.

[0164] Step S406: Determine whether the aircraft is on the ground.

[0165] The ground status indicator is used to indicate that the aircraft is on the ground and has not taken off.

[0166] Specifically, if the battery life parameter is determined to have reached the life cycle count, it is then determined whether the aircraft is on the ground. If the aircraft is on the ground, a battery maintenance instruction is issued, i.e., step S408 is executed. If the aircraft is not on the ground, the issuance of the battery maintenance instruction is suppressed, i.e., step S407 is executed; the battery maintenance instruction is issued only when the aircraft is on the ground.

[0167] Specifically, if it is determined that the time remaining before the scheduled maintenance of the aircraft battery has reached the scheduled maintenance time, it is then determined whether the aircraft is on the ground. If the aircraft is on the ground, a battery maintenance instruction is issued, i.e., step S408 is executed. If the aircraft is not on the ground, the issuance of the battery maintenance instruction is suppressed, i.e., step S407 is executed; the battery maintenance instruction is issued only when the aircraft is on the ground.

[0168] Step S407, Battery pack maintenance indication suppressed.

[0169] Among them, battery pack maintenance instruction suppression means temporarily not sending battery pack maintenance instructions.

[0170] Step S408: Issue a battery pack maintenance instruction.

[0171] Among them, battery pack maintenance instructions can be obtained through Figure 3 The lithium battery controller 20 in the aircraft battery status display system issues battery pack maintenance instructions via [the system]. Figure 3 The maintenance instruction area 310 of the aircraft battery status display system is shown.

[0172] In this embodiment, by obtaining the battery life parameters of the aircraft battery to indicate the status of the aircraft battery, the comprehensiveness of the status display can be effectively improved, thereby improving the accuracy of the status display.

[0173] The method of this application has been described above. In order to better implement the method of this application, the apparatus of this application will be described next.

[0174] like Figure 8 As shown, in one embodiment, the present invention provides a status display device for an aircraft battery, the status display device comprising:

[0175] Temperature processing module 801 is used to detect the temperature of each individual cell in the aircraft battery and calculate the average temperature of the aircraft battery based on the temperature of each individual cell.

[0176] Temperature difference calculation module 802 is used to calculate the temperature difference between the temperature of each individual battery cell and the average temperature of the aircraft battery.

[0177] The battery pack maintenance instruction generation module 803 is used to determine whether the absolute value of the temperature difference corresponding to each individual battery cell exceeds a first temperature threshold. If the absolute value of the temperature difference corresponding to any individual battery cell exceeds the first temperature threshold, it determines whether the start-up time of the aircraft auxiliary power unit exceeds the start-up time threshold. If the start-up time exceeds the start-up time threshold and the aircraft is on the ground, a battery pack maintenance instruction is issued.

[0178] The average temperature determination module 804 is used to determine whether the average temperature of the aircraft battery has reached a second temperature threshold.

[0179] The battery pack level 1 alarm indication generation module 805 is used to determine whether the average temperature of the aircraft battery has reached a third temperature threshold if the average temperature of the aircraft battery reaches a second temperature threshold, and to issue a battery pack level 1 alarm indication if the average temperature of the aircraft battery reaches the third temperature threshold.

[0180] The battery pack availability indicator generation module 806 is used to heat the aircraft battery if the average temperature of the aircraft battery does not reach a second temperature threshold, and to issue a battery pack availability indicator if the average temperature of the heated aircraft battery reaches a fourth temperature threshold.

[0181] like Figure 9 As shown, in one embodiment, this is an internal structural diagram of an electronic device. This electronic device may be a status display device for an aircraft battery, or a terminal or server connected to such a device. Figure 9 As shown, the electronic device includes a processor, a memory, and a network interface connected via a system bus. The memory includes a non-volatile storage medium and internal memory. The non-volatile storage medium stores an operating system and may also store a computer program. When executed by the processor, this computer program enables the processor to implement a method for displaying the status of an aircraft battery. The internal memory may also store a computer program, which, when executed by the processor, enables the processor to implement a method for displaying the status of an aircraft battery. The network interface is used for communication with external devices. Those skilled in the art will understand that… Figure 9 The structure shown is merely a block diagram of a portion of the structure related to the present application and does not constitute a limitation on the electronic device to which the present application is applied. The specific electronic device may include more or fewer components than shown in the figure, or combine certain components, or have different component arrangements.

[0182] In one embodiment, the aircraft battery status display method provided in this application can be implemented as a computer program, and the computer program can be implemented as follows: Figure 9 The electronic device shown operates on this device. The memory of the electronic device can store various program templates that make up the status display device of the aircraft battery. For example, temperature processing module 801, temperature difference calculation module 802, battery pack maintenance indication generation module 803, average temperature judgment module 804, battery pack first-level alarm indication generation module 805, and battery pack availability indication generation module 806.

[0183] An electronic device includes a memory and a processor. The memory stores a computer program that, when executed by the processor, causes the processor to perform the following steps: detecting the temperature of each individual cell in an aircraft battery and calculating the average temperature of the aircraft battery based on the temperature of each individual cell; calculating the temperature difference between the temperature of each individual cell and the average temperature of the aircraft battery; determining whether the absolute value of the temperature difference corresponding to each individual cell exceeds a first temperature threshold; and if the absolute value of the temperature difference corresponding to any individual cell exceeds the first temperature threshold, determining whether the start-up time of the aircraft auxiliary power unit exceeds a start-up time threshold. If the startup duration exceeds the startup time threshold and the aircraft is on the ground, a battery maintenance instruction is issued; it is determined whether the average temperature of the aircraft battery has reached a second temperature threshold. If the average temperature of the aircraft battery has reached the second temperature threshold, it is determined whether the average temperature of the aircraft battery has reached a third temperature threshold. If the average temperature of the aircraft battery has reached the third temperature threshold, a first-level battery alarm instruction is issued; if the average temperature of the aircraft battery has not reached the second temperature threshold, the aircraft battery is heated. If the average temperature of the heated aircraft battery reaches a fourth temperature threshold, a battery availability instruction is issued.

[0184] In one embodiment, the step of issuing a battery pack level one alarm indication if the average temperature of the aircraft battery reaches the third temperature threshold includes: if the average temperature of the aircraft battery reaches the third temperature threshold, obtaining a first duration of the aircraft battery in the state of reaching the third temperature threshold; if the first duration reaches a first duration threshold, issuing a battery pack level one alarm indication.

[0185] In one embodiment, the step of issuing a battery pack level one alarm indication if the average temperature of the aircraft battery reaches the third temperature threshold is further included by: determining whether the average temperature of the aircraft battery reaches a fifth temperature threshold; and issuing a battery pack level two alarm indication if the average temperature of the aircraft battery reaches the fifth temperature threshold.

[0186] In one embodiment, the step of issuing a secondary alarm indication for the battery pack if the average temperature of the aircraft battery reaches the fifth temperature threshold includes: if the average temperature of the aircraft battery reaches the fifth temperature threshold, obtaining a second duration of the aircraft battery in the state of reaching the fifth temperature threshold; if the second duration reaches a second duration threshold, issuing a secondary alarm indication for the battery pack.

[0187] In one embodiment, the step of heating the aircraft battery if the average temperature of the aircraft battery does not reach the second temperature threshold includes: if the average temperature of the aircraft battery does not reach the second temperature threshold, obtaining a third duration of the aircraft battery in the state where the second temperature threshold is not reached; if the third duration reaches the third duration threshold, heating the aircraft battery.

[0188] In one embodiment, the step of issuing a battery pack availability indication if the average temperature of the heated aircraft battery reaches a fourth temperature threshold includes: if the average temperature of the heated aircraft battery reaches the fourth temperature threshold, obtaining a fourth duration of the heated aircraft battery in the state of reaching the fourth temperature threshold; and if the fourth duration reaches a fourth duration threshold, issuing a battery pack availability indication.

[0189] In one embodiment, the step of issuing a battery pack maintenance instruction if the startup duration exceeds the startup time threshold and the aircraft is in a ground state includes: if the startup duration exceeds the startup time threshold, determining the air-to-ground state of the aircraft; if the air-to-ground state is a ground state, issuing a battery pack maintenance instruction.

[0190] In one embodiment, when the computer program is executed by a processor, the processor further performs the following steps: acquiring the charge state parameters of the aircraft battery; determining whether the charge state parameters are less than a charge state threshold; if the charge state parameters are less than the charge state threshold, determining whether the aircraft is in a non-emergency power supply state; if the aircraft is in a non-emergency power supply state and the aircraft is in the ground state, issuing a battery pack maintenance instruction.

[0191] In one embodiment, when the computer program is executed by a processor, the processor also performs the following steps: acquiring battery life parameters of the aircraft battery; determining whether the battery life parameters have reached the life cycle count or the aircraft scheduled maintenance time; if the battery life parameters have reached the life cycle count or the aircraft scheduled maintenance time, and the aircraft is in the ground state, then issuing a battery pack maintenance instruction.

[0192] A computer-readable storage medium storing a computer program, which, when executed by a processor, causes the processor to perform the following steps: detecting the temperature of each individual cell in the aircraft battery, and calculating the average temperature of the aircraft battery based on the temperature of each individual cell; calculating the temperature difference between the temperature of each individual cell and the average temperature of the aircraft battery; determining whether the absolute value of the temperature difference corresponding to each individual cell exceeds a first temperature threshold; if the absolute value of the temperature difference corresponding to any individual cell exceeds the first temperature threshold, determining whether the start-up time of the aircraft auxiliary power unit exceeds a start-up time threshold; if the... If the startup time exceeds the startup time threshold and the aircraft is on the ground, a battery maintenance instruction is issued. The system then determines whether the average temperature of the aircraft battery has reached a second temperature threshold. If the average temperature of the aircraft battery reaches the second temperature threshold, it determines whether the average temperature of the aircraft battery has reached a third temperature threshold. If the average temperature of the aircraft battery reaches the third temperature threshold, a first-level battery alarm instruction is issued. If the average temperature of the aircraft battery has not reached the second temperature threshold, the aircraft battery is heated. If the average temperature of the heated aircraft battery reaches a fourth temperature threshold, a battery availability instruction is issued.

[0193] In one embodiment, the step of issuing a battery pack level one alarm indication if the average temperature of the aircraft battery reaches the third temperature threshold includes: if the average temperature of the aircraft battery reaches the third temperature threshold, obtaining a first duration of the aircraft battery in the state of reaching the third temperature threshold; if the first duration reaches a first duration threshold, issuing a battery pack level one alarm indication.

[0194] In one embodiment, the step of issuing a battery pack level one alarm indication if the average temperature of the aircraft battery reaches the third temperature threshold is further included by: determining whether the average temperature of the aircraft battery reaches a fifth temperature threshold; and issuing a battery pack level two alarm indication if the average temperature of the aircraft battery reaches the fifth temperature threshold.

[0195] In one embodiment, the step of issuing a secondary alarm indication for the battery pack if the average temperature of the aircraft battery reaches the fifth temperature threshold includes: if the average temperature of the aircraft battery reaches the fifth temperature threshold, obtaining a second duration of the aircraft battery in the state of reaching the fifth temperature threshold; if the second duration reaches a second duration threshold, issuing a secondary alarm indication for the battery pack.

[0196] In one embodiment, the step of heating the aircraft battery if the average temperature of the aircraft battery does not reach the second temperature threshold includes: if the average temperature of the aircraft battery does not reach the second temperature threshold, obtaining a third duration of the aircraft battery in the state where the second temperature threshold is not reached; if the third duration reaches the third duration threshold, heating the aircraft battery.

[0197] In one embodiment, the step of issuing a battery pack availability indication if the average temperature of the heated aircraft battery reaches a fourth temperature threshold includes: if the average temperature of the heated aircraft battery reaches the fourth temperature threshold, obtaining a fourth duration of the heated aircraft battery in the state of reaching the fourth temperature threshold; and if the fourth duration reaches a fourth duration threshold, issuing a battery pack availability indication.

[0198] In one embodiment, the step of issuing a battery pack maintenance instruction if the startup duration exceeds the startup time threshold and the aircraft is in a ground state includes: if the startup duration exceeds the startup time threshold, determining the air-to-ground state of the aircraft; if the air-to-ground state is a ground state, issuing a battery pack maintenance instruction.

[0199] In one embodiment, when the computer program is executed by a processor, the processor further performs the following steps: acquiring the charge state parameters of the aircraft battery; determining whether the charge state parameters are less than a charge state threshold; if the charge state parameters are less than the charge state threshold, determining whether the aircraft is in a non-emergency power supply state; if the aircraft is in a non-emergency power supply state and the aircraft is in the ground state, issuing a battery pack maintenance instruction.

[0200] In one embodiment, when the computer program is executed by a processor, the processor also performs the following steps: acquiring battery life parameters of the aircraft battery; determining whether the battery life parameters have reached the life cycle count or the aircraft scheduled maintenance time; if the battery life parameters have reached the life cycle count or the aircraft scheduled maintenance time, and the aircraft is in the ground state, then issuing a battery pack maintenance instruction.

[0201] Those skilled in the art will understand that all or part of the processes in the above embodiments can be implemented by a computer program instructing related hardware. The program can be stored in a computer-readable storage medium, and when executed, it can include the processes of the embodiments of the above methods. The storage medium can be a magnetic disk, optical disk, read-only memory (ROM), or random access memory (RAM), etc.

[0202] The above-disclosed embodiments are merely preferred embodiments of this application and should not be construed as limiting the scope of this application. Therefore, any equivalent variations made in accordance with the claims of this application shall still fall within the scope of this application.

Claims

1. A method for displaying the status of an aircraft battery, characterized in that, The status display method includes: The temperature of each individual cell in the aircraft battery is detected, and the average temperature of the aircraft battery is calculated based on the temperature of each individual cell. Calculate the temperature difference between the temperature of each individual cell and the average temperature of the aircraft battery; It is determined whether the absolute value of the temperature difference corresponding to each individual battery exceeds a first temperature threshold. The first temperature threshold is used to reflect the maximum value of the absolute value of the temperature difference corresponding to each individual battery. If the absolute value of the temperature difference corresponding to any individual battery exceeds the first temperature threshold, it is determined whether the start-up time of the aircraft auxiliary power unit exceeds the start-up time threshold. If the start-up time exceeds the start-up time threshold and the aircraft is on the ground, a battery pack maintenance instruction is issued. The system determines whether the average temperature of the aircraft battery has reached a second temperature threshold, which is a critical value for whether the aircraft battery is in a low-temperature state. If the average temperature of the aircraft battery reaches the second temperature threshold, the system determines whether the average temperature of the aircraft battery has reached a third temperature threshold, which is a critical value for whether the aircraft battery is in a first-level over-temperature state. If the average temperature of the aircraft battery reaches the third temperature threshold, a first-level battery alarm indication is issued. If the average temperature of the aircraft battery has not reached the second temperature threshold, the aircraft battery is heated. If the average temperature of the heated aircraft battery reaches a fourth temperature threshold, a battery pack availability indication is issued. The fourth temperature threshold is used to indicate whether the aircraft battery is in a usable state.

2. The status display method according to claim 1, characterized in that, The step of issuing a battery pack level one alarm indication if the average temperature of the aircraft battery reaches the third temperature threshold includes: If the average temperature of the aircraft battery reaches the third temperature threshold, then the first duration of the aircraft battery in the state of reaching the third temperature threshold is obtained. If the first duration reaches the first duration threshold, a first-level alarm indication for the battery pack is issued.

3. The status display method according to claim 1, characterized in that, The step of issuing a battery pack level one alarm indication if the average temperature of the aircraft battery reaches the third temperature threshold is further included, in addition to: Determine whether the average temperature of the aircraft battery has reached the fifth temperature threshold. If the average temperature of the aircraft battery reaches the fifth temperature threshold, a secondary alarm indication for the battery pack will be issued.

4. The status display method according to claim 3, characterized in that, The step of issuing a secondary alarm indication for the battery pack if the average temperature of the aircraft battery reaches the fifth temperature threshold includes: If the average temperature of the aircraft battery reaches the fifth temperature threshold, then the second duration of the aircraft battery in the state of reaching the fifth temperature threshold is obtained; If the second duration reaches the second duration threshold, a battery pack level 2 alarm indication is issued.

5. The status display method according to claim 1, characterized in that, The step of heating the aircraft battery if the average temperature of the battery does not reach the second temperature threshold includes: If the average temperature of the aircraft battery does not reach the second temperature threshold, then obtain the third duration of the aircraft battery in the state where the second temperature threshold is not reached; If the third duration reaches the third duration threshold, the aircraft battery is heated.

6. The status display method according to claim 1, characterized in that, The step of issuing a battery pack availability indication if the average temperature of the heated aircraft battery reaches a fourth temperature threshold includes: If the average temperature of the heated aircraft battery reaches the fourth temperature threshold, then the fourth duration of the heated aircraft battery in the state of reaching the fourth temperature threshold is obtained. If the fourth duration reaches the fourth duration threshold, a battery pack availability indication is issued.

7. The status display method according to claim 1, characterized in that, The step of issuing a battery pack maintenance instruction if the startup duration exceeds the startup time threshold and the aircraft is on the ground includes: If the startup duration exceeds the startup time threshold, the air-to-ground status of the aircraft is determined. If the open-ground state is ground state, a battery pack maintenance instruction is issued.

8. The status display method according to claim 1, characterized in that, The status display method further includes: Obtain the state of charge parameters of the aircraft battery; Determine whether the charge state parameter is less than the charge state threshold; If the charge state parameter is less than the charge state threshold, it is determined whether the aircraft is in a non-emergency power supply state. If the aircraft is in a non-emergency power supply state and the aircraft is in the aforementioned ground state, a battery pack maintenance instruction will be issued.

9. The status display method according to claim 1, characterized in that, The status display method further includes: Obtain the battery life parameters of the aircraft battery; Determine whether the battery life parameters have reached the life cycle count or the aircraft scheduled maintenance time. If the battery life parameter is the number of life cycles or the scheduled aircraft maintenance time, and the aircraft is in the ground state, a battery pack maintenance instruction is issued.

10. A status display device for an aircraft battery, characterized in that, The status display device includes: A temperature processing module is used to detect the temperature of each individual cell in the aircraft battery and calculate the average temperature of the aircraft battery based on the temperature of each individual cell. A temperature difference calculation module is used to calculate the temperature difference between the temperature of each individual battery cell and the average temperature of the aircraft battery. The battery pack maintenance instruction generation module is used to determine whether the absolute value of the temperature difference corresponding to each individual battery cell exceeds a first temperature threshold. The first temperature threshold is used to reflect the maximum value of the absolute value of the temperature difference corresponding to each individual battery cell. If the absolute value of the temperature difference corresponding to any individual battery cell exceeds the first temperature threshold, it is determined whether the start-up time of the aircraft auxiliary power unit exceeds the start-up time threshold. If the start-up time exceeds the start-up time threshold and the aircraft is on the ground, a battery pack maintenance instruction is issued. The average temperature judgment module is used to determine whether the average temperature of the aircraft battery has reached a second temperature threshold, which is a critical value for whether the aircraft battery is in a low temperature state. The battery pack level 1 alarm indication generation module is used to determine whether the average temperature of the aircraft battery has reached a third temperature threshold if the average temperature of the aircraft battery reaches a second temperature threshold. The third temperature threshold is the critical value for whether the aircraft battery is in a level 1 over-temperature state. If the average temperature of the aircraft battery reaches the third temperature threshold, a battery pack level 1 alarm indication is issued. The battery pack availability indicator generation module is used to heat the aircraft battery if the average temperature of the aircraft battery does not reach a second temperature threshold, and to issue a battery pack availability indicator if the average temperature of the heated aircraft battery reaches a fourth temperature threshold. The fourth temperature threshold is used to indicate whether the aircraft battery is in a usable state.

11. An electronic device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that, When the computer program is executed by the processor, the processor performs the steps of the status display method as described in any one of claims 1-9.

12. A computer-readable storage medium storing a computer program, characterized in that, When the computer program is executed by a processor, the processor performs the steps of the status display method as described in any one of claims 1-9.

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