Aircraft warning suppression method, system, electronic equipment and storage medium

Abstract

The embodiments of the present application disclose a method, system, electronic device, and storage medium for suppressing aircraft warnings. The method, applied to a command sending end, includes: obtaining first flight data; obtaining second flight data; determining the aircraft's flight status based on the first and second flight data; and issuing a warning operation instruction to a command execution end based on the aircraft's flight status. The warning operation instruction is executed by the command execution end to control the aircraft's warning system. The aircraft warning suppression technical solution proposed in this application can automatically suppress the aircraft's warning system from being activated when an aircraft passes below during flight, preventing the crew from mistakenly believing there is a risk of collision and causing safety issues.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft warning technology, and in particular to an aircraft warning suppression method, system, electronic equipment and storage medium. Background Art

[0002] The GPWS and reactive windshear features of the Terrain Awareness and Warning System (TAWS) primarily provide ground impact protection during low-altitude flight, preventing collisions. They also provide the crew with appropriate warnings when the aircraft approaches the ground, enhancing aircraft safety. To this end, most civil airliners are equipped with a ground proximity warning system (GPAW), which primarily consists of a GPAW computer (GPAW) and warning lights, as well as a control panel. The computer stores threshold data for various warning modes and compares this data with actual aircraft status data from other systems, such as the altitude signal from the radio altimeter, the pressure altitude and rate of change from the air data computer (ADC), and the inertial vertical speed from the inertial navigation system (INS). If this data exceeds the threshold for a particular warning mode, the GPAW computer outputs the appropriate audio and visual warning signals, alerting the pilot to the dangerous situation. The audio and visual warnings remain in effect until appropriate action is taken to resolve the unsafe situation.

[0003] Since radio altitude is calculated by transmitting radio waves to the ground and then receiving radio waves reflected from the ground, when an aircraft is operating on its route and a passing aircraft is below, the radio waves will be transmitted to the aircraft below, resulting in a reduction in the reflection distance and a jump in radio altitude. At this time, the aircraft's warning system will mistakenly believe that the aircraft is too close to the ground and enter the TAWS GPWS function mode 2 warning envelope, thereby triggering the "TERRAIN TERRAIN" warning. Since the aircraft is at high altitude, the appearance of a GPWS warning is a nuisance warning. The frequent appearance of nuisance warnings will reduce pilots' trust in TAWS and pose a safety risk. Summary of the Invention

[0004] The embodiments of the present application provide an aircraft warning suppression method, system, electronic device, and storage medium to solve the technical problem in the prior art of triggering a nuisance warning when an aircraft passes below the aircraft.

[0005] In order to solve the above technical problems, the embodiments of the present application disclose the following technical solutions:

[0006] In a first aspect, a method for suppressing aircraft warnings is provided. The method is applied to a command sending end and includes:

[0007] Acquire first flight data;

[0008] Acquire second flight data;

[0009] determining a flight status of the aircraft according to the first flight data and the second flight data;

[0010] An alarm operation instruction is sent to the instruction execution terminal according to the flight status of the aircraft. The alarm operation instruction is executed by the instruction execution terminal to control the aircraft warning system.

[0011] In combination with the first aspect, the first flight data includes an aircraft radio altitude jump value, and the aircraft radio altitude jump value acquisition method includes:

[0012] Transmitting radio waves to the ground in real time through the onboard radio device;

[0013] Receive radio waves reflected from the ground;

[0014] According to the round-trip time of the radio wave, the current aircraft radio altitude value is calculated;

[0015] Subtract the aircraft radio altitude value at the previous moment from the current aircraft radio altitude value to obtain the aircraft radio altitude jump value.

[0016] In combination with the first aspect, the second flight data includes an aircraft height above the ground, and the method for obtaining the aircraft height above the ground includes:

[0017] Determine the aircraft's location based on its latitude and longitude or GPS altitude;

[0018] The aircraft's altitude above the ground is calculated based on the aircraft's positioning and terrain database data.

[0019] In conjunction with the first aspect, a method for determining an aircraft flight status based on first flight data and second flight data includes the following steps:

[0020] Comparing the acquired first flight data with a set altitude threshold H2;

[0021] Comparing the acquired second flight data with a set altitude threshold H1;

[0022] The aircraft flight status is obtained according to the comparison result.

[0023] In conjunction with the first aspect, the aircraft flight status includes:

[0024] A first state, wherein the first state satisfies: the aircraft's ground clearance value h1> the height threshold H1, and at the same time, the aircraft's radio altitude jump value h2≥ the height threshold H2;

[0025] A second state, wherein the second state satisfies: the aircraft's ground clearance value h1> the height threshold H1, and at the same time, the aircraft's radio altitude jump value h2< the height threshold H2;

[0026] A third state, wherein the third state satisfies: the aircraft ground clearance value h1 ≤ the height threshold H1, and at the same time, the aircraft radio altitude jump value h2 ≥ the height threshold H2;

[0027] The fourth state satisfies: the aircraft height above the ground h1 ≤ the height threshold H1 , and the aircraft radio altitude jump value h2 < the height threshold H2 .

[0028] In combination with the first aspect, the height threshold H1 satisfies: H1≥5000ft; the height threshold H2 satisfies: 2000ft>H2≥450ft.

[0029] In conjunction with the first aspect, the method for issuing an alarm operation instruction according to the flight status of an aircraft includes the following steps:

[0030] When the acquired aircraft flight status is the first status, issuing an alarm suppression instruction;

[0031] When the acquired aircraft flight status is the second status, issuing an alarm recovery instruction;

[0032] When the acquired aircraft flight status is the third status, issuing an alarm recovery instruction;

[0033] When the acquired aircraft flight status is the fourth status, an alarm recovery instruction is issued.

[0034] In a second aspect, a method for suppressing aircraft warnings is provided. The method is applied to a command execution end and includes:

[0035] Receive the warning control command issued by the command sending end;

[0036] Control the aircraft warning system according to the type of warning operation instruction;

[0037] The warning operation instruction is obtained by the instruction sending end according to the flight status of the aircraft, and the flight status of the aircraft is obtained by comparing the first flight data and the second flight data.

[0038] In combination with the second aspect, the alarm operation instruction includes an alarm suppression instruction and an alarm recovery instruction.

[0039] In combination with the second aspect, the warning suppression instruction is used to suppress the function of the aircraft warning system.

[0040] In combination with the second aspect, the warning recovery instruction is used to restore the function of the aircraft warning system.

[0041] The third aspect provides an aircraft warning suppression system.

[0042] A first acquisition module, configured to acquire first flight data;

[0043] A second acquisition module, configured to acquire second flight data;

[0044] a data processing module, configured to determine a flight status of the aircraft based on the first flight data and the second flight data;

[0045] The instruction sending module is used to send an alarm operation instruction to the instruction execution end according to the flight status of the aircraft. The alarm operation instruction is executed by the instruction execution end to control the aircraft warning system.

[0046] In a fourth aspect, an aircraft warning suppression system is provided, the system comprising:

[0047] The command receiving module is used to receive the alarm control command sent by the command sending end;

[0048] The instruction execution module is used to control the aircraft warning system according to the type of warning operation instruction;

[0049] The warning operation instruction is obtained by the instruction sending end according to the flight status of the aircraft, and the flight status of the aircraft is obtained by comparing the first flight data and the second flight data.

[0050] In a fifth aspect, an electronic device is provided, comprising a memory and a processor; the memory is used to store a computer program; and the processor is used to implement the aircraft warning suppression method as described in the first aspect or the second aspect when executing the computer program.

[0051] In a sixth aspect, a computer-readable storage medium is provided, on which a computer program is stored. When the computer program is executed by a processor, the aircraft warning suppression method as described in the first aspect or the second aspect is implemented.

[0052] One of the above technical solutions has the following advantages or beneficial effects:

[0053] Compared with the prior art, the aircraft warning suppression method of the present application is applied to the instruction sending end, including: obtaining first flight data; obtaining second flight data; judging the aircraft flight status based on the first flight data and the second flight data; issuing an alarm operation instruction to the instruction execution end according to the aircraft flight status, and the alarm operation instruction is executed by the instruction execution end to control the aircraft warning system. Through the aircraft warning suppression technical solution proposed in the present application, when an aircraft passes below during flight, the aircraft warning system can be automatically suppressed from opening, thereby avoiding the crew mistakenly believing that there is a risk of collision and causing safety problems. BRIEF DESCRIPTION OF THE DRAWINGS

[0054] The following detailed description of the specific embodiments of the present application in conjunction with the accompanying drawings will make the technical solutions and other beneficial effects of the present application apparent.

[0055] Figure 1 A schematic diagram of a method flow diagram of an instruction sending end provided in an embodiment of the present application;

[0056] Figure 2 A schematic diagram of a method flow of an instruction execution terminal provided in an embodiment of the present application;

[0057] Figure 3 A schematic diagram of a process for obtaining first flight data provided in an embodiment of the present application;

[0058] Figure 4 A schematic diagram of the system structure of the instruction sending end provided in an embodiment of the present application;

[0059] Figure 5 A schematic diagram of the system structure of the instruction execution terminal provided in an embodiment of the present application;

[0060] Figure 6 Schematic diagram of an aircraft in a first and second state provided by an embodiment of the present application;

[0061] Figure 7 Schematic diagram of the aircraft in the third and fourth states provided in the embodiment of the present application. DETAILED DESCRIPTION

[0062] The technical solutions in the embodiments of the present application will be described clearly and completely below in conjunction with the drawings in the embodiments of the present application. In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first" and "second" are used only for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, features defined as "first" and "second" may explicitly or implicitly include one or more of the said features. In the description of the present application, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined.

[0063] The specific implementation of this application is described below through examples:

[0064] like Figure 1As shown, an embodiment of the present application provides an aircraft warning suppression method, which is applied to a command sending end and includes:

[0065] S11: Acquire first flight data;

[0066] The first flight data includes an aircraft radio altitude jump value, and the method for obtaining the aircraft radio altitude jump value includes:

[0067] Transmitting radio waves to the ground in real time through the onboard radio device;

[0068] Receive radio waves reflected from the ground;

[0069] According to the round-trip time of the radio wave, the current aircraft radio altitude value is calculated;

[0070] Subtract the aircraft radio altitude value at the previous moment from the current aircraft radio altitude value to obtain the aircraft radio altitude jump value;

[0071] Radio altitude is calculated by transmitting radio waves to the ground through an onboard radio transmitter and then receiving the radio waves reflected from the ground. Because the ground is uneven, there are often protruding terrain such as mountains and earth slopes, as well as submerged terrain such as basins and rivers. Therefore, the radio altitude value is constantly fluctuating. To obtain the radio altitude jump value, the radio altitude value at each moment needs to be recorded. The radio altitude jump value is obtained by subtracting the radio altitude value at the previous moment from the current radio altitude value. Because the aircraft flies at very high speeds at high altitudes, it can fly 200-300 meters per second. Therefore, in order to accurately obtain the real-time radio altitude of the aircraft and enable the crew to obtain accurate data as soon as possible, the time interval is set to 0.05-0.2s. That is, when the selected time interval is 0.1s, the radio altitude jump value will be calculated every 0.1s. At the same time, 0.05s, 0.06s, 0.07s, 0.08s, 0.09s, 0.1s, 0.11s, 0.12s, 0.13s, 0.14s, 0.15s, 0.16s, 0.17s, 0.18s, 0.19s, and 0.2s can all be used as time interval settings.

[0072] S12: Acquire second flight data;

[0073] The second flight data includes an aircraft height above the ground, and a method for obtaining the aircraft height above the ground includes:

[0074] Determine the aircraft's location based on its latitude and longitude or GPS altitude;

[0075] The aircraft's altitude above the ground is calculated based on the aircraft's positioning and terrain database data;

[0076] The aircraft's position is determined based on its longitude and latitude, or its GPS altitude (altitude), and its altitude is calculated using terrain maps in a terrain database. The terrain database is pre-installed in the aircraft's system and uses longitude and latitude to determine the terrain. Combined with the aircraft's GPS altitude and the altitude of the terrain, the aircraft's actual height relative to the terrain, or altitude, can be calculated. Terrain maps include, but are not limited to, Baidu Maps, Amap, and Beidou Maps.

[0077] like Figure 3 As shown, S13: determining the flight status of the aircraft according to the first flight data and the second flight data;

[0078] The method for determining the flight status of an aircraft based on first flight data and second flight data comprises the following steps:

[0079] S131: Compare the acquired first flight data with the set altitude threshold H2;

[0080] The first flight data is the aircraft radio altitude jump value. When the radio altitude jumps from a value above 2600 ft or the radio altimeter data NCD to below 2150 ft within t seconds, that is, the radio altitude jump value is greater than H2, it is considered that the radio altitude value has jumped. Among them, the altitude threshold H2 satisfies: 2000 ft>H2≥450 ft; t satisfies: 1≥t>0;

[0081] S132: Compare the acquired second flight data with the set altitude threshold H1;

[0082] After confirming that the radio altitude value has jumped, it is determined whether the aircraft altitude exceeds 5000ft, that is, whether the aircraft altitude exceeds the altitude threshold H1, wherein the altitude threshold H1 satisfies: H1 ≥ 5000ft;

[0083] S133: If Figure 6 、 7 As shown, the flight status of the aircraft is obtained according to the comparison result;

[0084] The aircraft flight status includes:

[0085] The first state satisfies: the aircraft's ground clearance value h1> the height threshold H1, and at the same time, the aircraft's radio altitude jump value h2≥ the height threshold H2;

[0086] The second state satisfies: the aircraft's ground clearance value h1> the height threshold H1, and at the same time, the aircraft's radio altitude jump value h2< the height threshold H2;

[0087] The third state satisfies: the aircraft's ground clearance value h1 ≤ the height threshold H1, and at the same time, the aircraft's radio altitude jump value h2 ≥ the height threshold H2;

[0088] The fourth state satisfies: the aircraft's ground clearance value h1 ≤ the height threshold H1, and at the same time, the aircraft's radio altitude jump value h2 < the height threshold H2;

[0089] When it is confirmed that the aircraft radio altitude jump value is greater than H2 and the aircraft altitude above the ground is greater than the altitude threshold H1, the aircraft flight state is determined to be the first state;

[0090] When the aircraft is in the first state, a warning suppression command is sent to the aircraft's warning system. The command includes suppressing the reactive windshear function of TAWS and the GPWS function for 60 seconds. At this time, the aircraft's warning system will be suppressed. When there is an aircraft passing below, the aircraft will not emit any lights or alarm sounds.

[0091] Alternatively, when it is confirmed that the aircraft radio altitude jump value is greater than H2, but the aircraft altitude above the ground is less than or equal to the altitude threshold H1, it can be obtained that the flight state of the aircraft at this time is the third state;

[0092] When the aircraft is in the third state, an alarm recovery command is sent to the aircraft's alarm system, and the command content includes: the TAWS reactive wind shear function works normally, and the GPWS function works normally;

[0093] When it is confirmed that the aircraft radio altitude jump value is less than the altitude threshold H2,

[0094] If the height of the aircraft above the ground is greater than the height threshold H1, the flight state of the aircraft is the second state;

[0095] If the height of the aircraft above the ground is less than or equal to the height threshold H1, the flight state of the aircraft is the fourth state;

[0096] When the aircraft is in the second or fourth flight state, an alarm recovery command is sent to the aircraft's alarm system, the command content including: the TAWS reactive wind shear function is working normally, and the GPWS function is working normally;

[0097] It can be concluded that when it is confirmed that the aircraft radio altitude jump value is less than the altitude threshold H2, regardless of whether the aircraft altitude above the ground is greater than the altitude threshold H1, the alarm recovery instruction is finally sent to the alarm system. Therefore, in this step, in order to make a judgment quickly, when it is confirmed that the aircraft radio altitude jump value is less than the altitude threshold H2, the judgment of the aircraft altitude above the ground can be skipped and the alarm recovery instruction can be sent directly;

[0098] S14: Sending an alarm operation instruction to the instruction execution terminal according to the aircraft flight status. The alarm operation instruction is executed by the instruction execution terminal to control the aircraft warning system;

[0099] The method for issuing warning operation instructions according to the flight status of the aircraft includes the following steps:

[0100] When the acquired aircraft flight status is the first status, issuing an alarm suppression instruction;

[0101] When the acquired aircraft flight status is the second status, an alarm recovery instruction is issued;

[0102] When the acquired aircraft flight status is the third status, an alarm recovery instruction is issued;

[0103] When the acquired aircraft flight status is the fourth status, an alarm recovery instruction is issued.

[0104] Warning suppression command, used to send to the aircraft's warning system, the command content includes: suppressing the reactive windshear function of TAWS and GPWS function for 60 seconds;

[0105] During the suppression process, the aircraft's ground collision warning function will be blocked, so when an aircraft passes below, the system will not issue an alarm, thereby reducing the burden on the crew;

[0106] Warning recovery command, used to send to the aircraft warning system, the command content includes: TAWS reactive wind shear function is working normally, GPWS function is working normally;

[0107] During normal operation, when the warning system detects changes in the terrain below the aircraft, it will output corresponding voice and light warning signals to remind the crew to respond in time;

[0108] like Figure 2 As shown, an embodiment of the present application provides an aircraft warning suppression method, which is applied to an instruction execution end and includes:

[0109] S21: receiving the alarm control command sent by the command sending end;

[0110] Alarm operation instructions include alarm suppression instructions and alarm recovery instructions;

[0111] The warning suppression command is used to suppress the function of the aircraft warning system;

[0112] The warning restoration command is used to restore the function of the aircraft warning system;

[0113] When the alarm system receives an alarm suppression instruction or an alarm recovery instruction, it performs corresponding operations according to the type of instruction;

[0114] Among them, the warning suppression command is used to send to the aircraft's warning system. The command content includes: suppressing the reactive wind shear function of TAWS and GPWS function for 60 seconds;

[0115] During the suppression process, the aircraft's ground collision warning function will be blocked, so when an aircraft passes below, the system will not issue an alarm, thereby reducing the burden on the crew;

[0116] Warning recovery command, used to send to the aircraft warning system, the command content includes: TAWS reactive wind shear function is working normally, GPWS function is working normally;

[0117] S22: Control the aircraft warning system according to the type of warning operation instruction;

[0118] The warning operation instruction is obtained by the instruction sending end according to the flight status of the aircraft. The flight status of the aircraft is obtained by comparing the first flight data and the second flight data. The specific comparison step is as described in step S13 above and will not be repeated here.

[0119] like Figure 4 As shown, an embodiment of the present application provides an aircraft warning suppression system, the system comprising:

[0120] The first acquisition module is configured to acquire first flight data; the first flight data includes an aircraft radio altitude jump value, and a method for acquiring the aircraft radio altitude jump value includes:

[0121] Transmitting radio waves to the ground in real time through the onboard radio device;

[0122] Receive radio waves reflected from the ground;

[0123] According to the round-trip time of the radio wave, the current aircraft radio altitude value is calculated;

[0124] Subtract the aircraft radio altitude value at the previous moment from the current aircraft radio altitude value to obtain the aircraft radio altitude jump value;

[0125] A second acquisition module, configured to acquire second flight data;

[0126] The second flight data includes an aircraft height above the ground. A method for obtaining the aircraft height above the ground includes:

[0127] Determine the aircraft's location based on its latitude and longitude or GPS altitude;

[0128] The aircraft's altitude above the ground is calculated based on the aircraft's positioning and terrain database data;

[0129] a data processing module, configured to determine a flight status of the aircraft based on the first flight data and the second flight data;

[0130] Comparing the acquired first flight data with a set altitude threshold H2;

[0131] Comparing the acquired second flight data with a set altitude threshold H1;

[0132] Obtaining the flight status of the aircraft according to the comparison result;

[0133] The command sending module is used to send warning operation instructions to the command execution terminal according to the aircraft's flight status. The warning operation instructions are executed by the command execution terminal to control the aircraft warning system;

[0134] The alarm operation instructions include alarm suppression instructions and alarm recovery instructions;

[0135] The warning suppression instruction is used to suppress the function of the aircraft warning system;

[0136] The warning restoration instruction is used to restore the function of the aircraft warning system.

[0137] like Figure 5 As shown, an embodiment of the present application provides an aircraft warning suppression system, the system comprising:

[0138] The command receiving module is used to receive the alarm control command sent by the command sending end;

[0139] The instruction execution module is used to control the aircraft warning system according to the type of warning operation instruction;

[0140] The alarm operation instructions include alarm suppression instructions and alarm recovery instructions;

[0141] The warning suppression instruction is used to suppress the function of the aircraft warning system;

[0142] The warning restoration instruction is used to restore the function of the aircraft warning system;

[0143] The warning operation instruction is obtained by the instruction sending end according to the flight status of the aircraft, and the flight status of the aircraft is obtained by comparing the first flight data and the second flight data.

[0144] An embodiment of the present application provides an electronic device, including a memory and a processor; the memory is used to store a computer program; the processor is used to implement an aircraft warning suppression method such as steps S11-S14 or steps S21-S22 when executing the computer program.

[0145] An embodiment of the present application provides a computer-readable storage medium having a computer program stored thereon. When the computer program is executed by a processor, an aircraft warning suppression method such as steps S11-S14 or steps S21-S22 is implemented.

[0146] The above is a detailed introduction to an aircraft warning suppression method, system, electronic device and storage medium provided in the embodiments of the present application. Specific examples are used herein to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the technical solutions and core ideas of the present application. Ordinary technicians in this field should understand that they can still modify the technical solutions recorded in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. These modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present application.

Claims

1. A method for suppressing aircraft warnings, characterized in that: The method is applied to the instruction sending end, and includes: Acquiring first flight data, where the first flight data includes a radio altitude jump value of the aircraft; Acquiring second flight data, where the second flight data includes an altitude value of the aircraft above the ground; determining a flight status of the aircraft according to the first flight data and the second flight data; The aircraft flight status includes: A first state, wherein the first state satisfies: the aircraft's ground clearance value h1> the height threshold H1, and at the same time, the aircraft's radio altitude jump value h2≥ the height threshold H2; The second state satisfies: the aircraft's ground clearance value h1> the height threshold H1, and the aircraft's radio altitude jump value h2< the height threshold H2; A third state, wherein the third state satisfies: the aircraft ground clearance value h1 ≤ the height threshold H1, and at the same time, the aircraft radio altitude jump value h2 ≥ the height threshold H2; A fourth state, wherein the fourth state satisfies: the aircraft ground clearance value h1 ≤ the altitude threshold H1, and at the same time, the aircraft radio altitude jump value h2 < the altitude threshold H2; An alarm operation instruction is sent to the instruction execution terminal according to the flight status of the aircraft. The alarm operation instruction is executed by the instruction execution terminal to control the aircraft warning system.

2. The aircraft warning suppression method according to claim 1, characterized in that: The method for obtaining the aircraft radio altitude jump value comprises: Transmitting radio waves to the ground in real time through the onboard radio device; Receive radio waves reflected from the ground; According to the round-trip time of the radio wave, the current aircraft radio altitude value is calculated; Subtract the aircraft radio altitude value at the previous moment from the current aircraft radio altitude value to obtain the aircraft radio altitude jump value.

3. The aircraft warning suppression method according to claim 2, characterized in that: The method for obtaining the height of the aircraft above the ground comprises: Determine the aircraft's location based on its latitude and longitude or GPS altitude; The aircraft's altitude above the ground is calculated based on the aircraft's positioning and terrain database data.

4. The aircraft warning suppression method according to claim 3, characterized in that: The method for determining the flight status of an aircraft based on first flight data and second flight data comprises the following steps: Comparing the acquired first flight data with a set altitude threshold H2 to obtain a first comparison result; Comparing the acquired second flight data with the set altitude threshold H1 to obtain a second comparison result; The flight status of the aircraft is obtained according to the first comparison result and the second comparison result.

5. The aircraft warning suppression method according to claim 4, characterized in that: The height threshold H1 satisfies: H1≥5000ft; the height threshold H2 satisfies: 2000ft>H2≥450ft.

6. The aircraft warning suppression method according to claim 5, characterized in that: The method for issuing warning operation instructions according to the flight status of the aircraft includes the following steps: When the acquired aircraft flight status is the first status, issuing an alarm suppression instruction; When the acquired aircraft flight status is the second status, issuing an alarm recovery instruction; When the acquired aircraft flight status is the third status, issuing an alarm recovery instruction; When the acquired aircraft flight status is the fourth status, an alarm recovery instruction is issued.

7. An aircraft warning suppression method, characterized in that: The method is applied to an instruction execution end, and the method receives an alarm operation instruction sent by the aircraft alarm suppression method according to any one of claims 1 to 6, comprising: Receive the warning control command issued by the command sending end; Control the aircraft warning system according to the type of warning operation instruction; The warning operation instruction is obtained by the instruction sending end according to the flight status of the aircraft, and the flight status of the aircraft is obtained by comparing the first flight data and the second flight data.

8. The aircraft warning suppression method according to claim 7, characterized in that: The alarm operation instructions include alarm suppression instructions and alarm recovery instructions.

9. The aircraft warning suppression method according to claim 8, characterized in that: The warning suppression instruction is used to suppress the warning function of the aircraft warning system.

10. The aircraft warning suppression method according to claim 9, characterized in that: The alarm restoration instruction is used to restore the alarm function of the aircraft warning system.

11. An aircraft warning suppression system, characterized in that: The system is applied to the instruction sending end, and includes: A first acquisition module is configured to acquire first flight data, wherein the first flight data includes a radio altitude jump value of the aircraft; A second acquisition module is used to acquire second flight data, where the second flight data includes a height of the aircraft above the ground; a data processing module, configured to determine a flight status of the aircraft based on the first flight data and the second flight data; The aircraft flight status includes: A first state, wherein the first state satisfies: the aircraft's ground clearance value h1> the height threshold H1, and at the same time, the aircraft's radio altitude jump value h2≥ the height threshold H2; The second state satisfies: the aircraft's ground clearance value h1> the height threshold H1, and the aircraft's radio altitude jump value h2< the height threshold H2; A third state, wherein the third state satisfies: the aircraft ground clearance value h1 ≤ the height threshold H1, and at the same time, the aircraft radio altitude jump value h2 ≥ the height threshold H2; A fourth state, wherein the fourth state satisfies: the aircraft ground clearance value h1 ≤ the altitude threshold H1, and at the same time, the aircraft radio altitude jump value h2 < the altitude threshold H2; The instruction sending module is used to send an alarm operation instruction to the instruction execution end according to the flight status of the aircraft. The alarm operation instruction is executed by the instruction execution end to control the aircraft warning system.

12. An aircraft warning suppression system, characterized in that: The system is applied to an instruction execution end, and the instruction execution end is capable of implementing the aircraft warning suppression method according to any one of claims 7 to 10 after receiving an instruction operation instruction, including: The command receiving module is used to receive the alarm control command sent by the command sending end; The instruction execution module is used to control the aircraft warning system according to the type of warning operation instruction; The warning operation instruction is obtained by the instruction sending end according to the flight status of the aircraft, and the flight status of the aircraft is obtained by comparing the first flight data and the second flight data.

13. An electronic device, characterized in that: The invention comprises a memory and a processor; the memory is used to store a computer program; the processor is used to implement the aircraft warning suppression method according to any one of claims 1 to 6, or 7 to 10 when executing the computer program.

14. A computer-readable storage medium, characterized in that: The storage medium stores a computer program, and when the computer program is executed by the processor, the aircraft warning suppression method according to any one of claims 1 to 6, or 7 to 10 is implemented.

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