A warning suppression method based on flight phase transition of amphibious aircraft

Abstract

The present invention provides an alarm suppression method based on the flight phase transition of an amphibious aircraft, comprising receiving and identifying flight state parameters during the aircraft's flight; screening valid flight data used to characterize the current flight phase; determining the transition conditions for each flight phase, creating a flight phase transition model based thereon, and performing simulation analysis of the actual flight state based on the valid flight data; determining whether the aircraft has entered a flight phase transition process; if so, determining the current flight phase transition point of the aircraft, and automatically matching a corresponding alarm suppression mechanism based on the flight phase transition point; activating the alarm suppression mechanism to automatically suppress alarm information within the mechanism; and determining whether the aircraft has exited the flight phase transition process; if so, releasing the current alarm suppression state. The present invention analyzes the flight phase transition process through a model and activates the alarm suppression mechanism during this process, thereby automatically suppressing unnecessary alarm information and improving flight safety and efficiency.

Description

Technical Field

[0001] The present invention relates to the field of aviation engineering, and in particular to an alarm suppression method based on flight phase transition of an amphibious aircraft. Background Art

[0002] With the development of aviation technology, amphibious aircraft, as a new type of transportation, are seaplanes that can take off and land at land airports. They have powerful capabilities for performing a variety of special missions, such as emergency rescue, forest fire fighting, and marine patrols. Therefore, there is great potential demand in the domestic and international aviation market. Because amphibious aircraft need to operate on the water and complete rescue missions in addition to aerial patrol, their flight phases are more complex than those of ordinary cruise aircraft, especially during the transition between flight phases, which places higher demands on the aircraft's flight efficiency and safety.

[0003] However, during the entire flight, the aircraft's onboard warning system will inform the flight crew of various warning information, including warning information from various systems on board, threat information from the aircraft's external environment, and even false alarms and false warnings. Even during the critical flight phase transition process, unnecessary warning information interference may occur, which causes the crew to have to deal with a large amount of warning information, causing fatigue and distraction, greatly reducing the safety and efficiency of the flight phase transition process.

[0004] Therefore, a method is needed to automatically suppress unnecessary warning information during the flight phase transition of an amphibious aircraft. Summary of the Invention

[0005] The present invention provides an alarm suppression method based on the flight phase transition of an amphibious aircraft, which is mainly used to solve the problem that unnecessary alarm information appears during the flight phase transition of existing amphibious aircraft and interferes with the flight, thereby achieving the effect of automatically suppressing unnecessary alarm information, reducing false alarms and false warnings, and improving flight safety and efficiency.

[0006] The present invention achieves the above-mentioned purpose through the following technical solutions:

[0007] A warning suppression method based on flight phase transition of an amphibious aircraft, comprising:

[0008] S1: Collect parameters of the amphibious aircraft during flight and identify the parameters related to the flight status.

[0009] S2: Perform data processing on the flight status parameters, including validity screening and data smoothing, to screen out valid flight data that characterizes the current flight phase of the aircraft.

[0010] S3: Determine the transition conditions for each flight phase, and create a flight phase transition model accordingly, and simulate and analyze the actual flight status based on the valid flight data in the model database.

[0011] S4: Determine whether the aircraft has entered the flight phase transition process. If so, determine the current flight phase transition point of the aircraft and automatically match the corresponding alarm suppression mechanism based on the flight phase transition point; if not, repeat step S1.

[0012] S5: Activate the alarm suppression mechanism to automatically suppress the alarm information within the mechanism.

[0013] S6: Determine whether the aircraft has left the flight phase transition process. If so, release the current alarm suppression state and repeat step S1; if not, maintain the current alarm suppression state.

[0014] A further solution is to collect flight parameters in real time through a bus data acquisition system. The flight status parameters include but are not limited to engine speed, landing gear up / down position signal, flap handle position, flap angle, radio altitude, throttle angle, door position / status signal, water hopper position signal and water dropping signal.

[0015] A further solution is to process the flight status parameters through a computer data processing program, filter and analyze the flight status parameters according to a preset filtering protocol and obtain the valid flight data therefrom, and perform sliding average filtering on the valid flight data through a filtering program.

[0016] A further solution is that the flight stages include but are not limited to powering on the aircraft, starting the aircraft engine, accelerating the aircraft, the aircraft leaving the ground or water, the aircraft climbing to a specified altitude, the aircraft descending to a specified altitude, the aircraft landing or landing on water, the aircraft decelerating and rolling, shutting down the engine, the aircraft performing a water-drawing mission, the aircraft performing a water-dropping mission, and the aircraft climbing from the air to a specified altitude.

[0017] A further solution is that the transition condition from the aircraft leaving the ground to the take-off phase is: the aircraft is from the ground to the air and meets either of the following two conditions:

[0018] Condition 1: Radio altitude < 450m and any two or more engines are at non-landing power.

[0019] Condition 2: The radio altitude is less than 300 m and any two or more engines are increased to ≥82° by landing power.

[0020] A further solution is that the transition condition from the aircraft leaving the water surface to the take-off phase is: the aircraft is from the water surface to the air, and the following two conditions are met at the same time:

[0021] Condition 1: Radio altitude < 450m.

[0022] Condition 2: Any two or more engines are at non-landing power.

[0023] A further solution is to change the aircraft into the water-drawing mission when the landing gear is fully retracted and locked and the following two conditions are met at the same time:

[0024] Condition 1: Ground speed > 70 km / h.

[0025] Condition 2: RA < 15m, the water bucket lowering command is valid.

[0026] The transition conditions for the aircraft to exit the water-lifting mission are: the landing gear is fully retracted and locked, and any one of the following three conditions is met:

[0027] Condition 1: The water bucket retraction command is valid and both water buckets are retracted into place.

[0028] Condition 2: The water bucket receiving instruction is valid and any electric valve is closed.

[0029] Condition 3: After the water bucket receives the command and it is valid for 6 seconds, any electric valve closes timeout.

[0030] A further solution is that the conversion conditions for the aircraft to enter the water-dropping mission are: the water-dropping door unlocking preparation command is valid, or the emergency water-dropping preparation command is valid.

[0031] The conditions for the aircraft to exit the water-dropping mission are: the water-dropping door unlock preparation command is cancelled, or the emergency receive command is valid and lasts for 5 seconds.

[0032] A further solution is to determine the relationship and structure between the valid flight data and the actual flight status according to the flight phase transition conditions, and to refine the structure of the database through a logical model.

[0033] A further solution is to deploy the flight phase transition model into the airborne warning system, and to achieve warning suppression by suppressing part of the warning information in the airborne warning system according to the flight phase transition point where the aircraft is located.

[0034] It can be seen that the present invention has the following beneficial effects:

[0035] 1. This invention establishes a mathematical model for flight phase transitions based on the characteristics and flight requirements of amphibious aircraft. By simulating parameter changes during flight, the flight phase transition process is analyzed. During this process, a corresponding warning suppression mechanism is activated to suppress unnecessary warning messages, thereby reducing interference during flight phase transitions. Especially during high-risk flight phases, such as takeoff and landing, the automatic suppression of unnecessary warning messages can significantly reduce pilot distraction, improve flight control focus, reduce operational errors caused by distraction, and ensure focus on critical mission execution.

[0036] 2. The present invention suppresses non-essential warning information during the transition between critical flight phases and releases the warning suppression after the transition is completed, allowing the crew to process the suppressed warning information at an appropriate time (such as when the aircraft reaches a safe altitude and the operation is stable), avoiding crew fatigue and distraction caused by processing a large amount of warning information, thereby improving the crew's work efficiency.

[0037] 3. The present invention deploys the flight phase transition model in the airborne warning system and suppresses unnecessary warning information based on the flight phase transition point, which helps to optimize the management of warning information, reduce the false alarm and false alarm rate of the warning system, ensure that key warning information can be transmitted in a timely and accurate manner, and improve the overall reliability of the warning system.

[0038] 4. By suppressing unnecessary warning information during flight phase transitions with heavy workloads, the present invention makes the warning system more intelligent and humane in serving flight safety. The crew does not have to constantly process various warning information in a high-intensity working environment, thereby reducing the crew's work pressure and fatigue and providing a better work experience.

[0039] In summary, the flight phase transition alarm suppression method of the present invention is of great significance for improving flight safety, crew work efficiency, and the development of intelligent and humanized alarm systems. It also promotes the continuous progress and improvement of modern civil aircraft alarm systems.

[0040] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 The present invention is a flow chart of an alarm suppression method based on flight phase transition of an amphibious aircraft.

[0042] Figure 2 It is a schematic diagram of the flight phase conversion model of the present invention.

[0043] Figure 3 It is a schematic diagram of the vector relationship of jumping between flight phases of the present invention. DETAILED DESCRIPTION

[0044] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the described embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0045] An embodiment of an alarm suppression method based on flight phase transition of an amphibious aircraft

[0046] See also Figure 1 The present invention relates to an alarm suppression method based on flight phase transition of an amphibious aircraft, comprising:

[0047] S1: Collect parameters of the amphibious aircraft during flight and identify the parameters related to the flight status.

[0048] S2: Perform data processing on the flight status parameters, including validity screening and data smoothing, to screen out valid flight data that characterizes the current flight phase of the aircraft.

[0049] S3: Determine the transition conditions for each flight phase, and create a flight phase transition model accordingly, and simulate and analyze the actual flight status based on the valid flight data in the model database.

[0050] S4: Determine whether the aircraft has entered the flight phase transition process. If so, determine the current flight phase transition point of the aircraft and automatically match the corresponding alarm suppression mechanism based on the flight phase transition point; if not, repeat step S1.

[0051] S5: Activate the alarm suppression mechanism to automatically suppress the alarm information within the mechanism.

[0052] S6: Determine whether the aircraft has left the flight phase transition process. If so, release the current alarm suppression state and repeat step S1; if not, maintain the current alarm suppression state.

[0053] Specifically, the amphibious aircraft of this embodiment has a hull structure, which can achieve floating on water without relying on other external assistance. At the same time, the aircraft also has landing gear for traveling on land.

[0054] Among them, amphibious aircraft use a glide slope to achieve the transition between land and water.

[0055] Specifically, this embodiment determines the optimal parameter combination during the flight phase transition process through simulation analysis to ensure the flight efficiency and safety of the aircraft in different environments.

[0056] Specifically, this embodiment is applicable to amphibious aircraft of different types and specifications, and has strong versatility and adaptability; at the same time, the method can also be flexibly adjusted and optimized according to specific application scenarios and needs.

[0057] In this embodiment, flight parameters are collected in real time through a bus data acquisition system. The flight status parameters include but are not limited to engine speed, landing gear up / down position signal, flap handle position, flap angle, radio altitude, throttle angle, door position / status signal, water hopper position signal and water dropping signal.

[0058] In this embodiment, the flight status parameters are processed by a computer data processing program, the flight status parameters are filtered and analyzed according to a preset filtering protocol to obtain the valid flight data, and the valid flight data is subjected to sliding average filtering by a filtering program.

[0059] Specifically, this embodiment performs smooth filtering, burr removal, or jitter removal on valid flight data through a filtering program.

[0060] Specifically, the data processing in this embodiment also includes data packet verification, data conversion, etc., to ensure the accuracy and integrity of the data.

[0061] Specifically, the data processing scheme by computer program in the present embodiment is merely exemplary and is not the only way. For example, data can also be processed by hardware processor chips and filter elements.

[0062] In this embodiment, the flight phases include but are not limited to the aircraft powering on, the aircraft engine starting, the aircraft accelerating and rolling, the aircraft leaving the ground or water, the aircraft climbing to a specified altitude, the aircraft descending to a specified altitude, the aircraft landing or landing on water, the aircraft decelerating and rolling, the engine shutting down, the aircraft performing a water-drawing mission, the aircraft performing a water-dropping mission, and the aircraft climbing from the air to a specified altitude.

[0063] Specifically, the flight phases described in this embodiment are used to characterize the entire operation scenario of the aircraft, including powering on the ground to engine starting, from ground acceleration and taxiing to takeoff from land or water, from climbing to air cruising to specific mission execution and then landing, from landing or water landing to aircraft deceleration and taxiing, from aircraft stopping to engine shutdown and then powering off, etc.

[0064] See also Figure 2 Specifically, this embodiment determines the following 18 flight phase transition conditions based on the above flight phases:

[0065] Flight phase transition conditions 1: The transition conditions for the land flight preparation phase are: the aircraft is on land, powered on, system checks are being carried out and all engines are not started.

[0066] Flight phase transition conditions 2: The transition conditions for the water flight preparation phase are: the aircraft is on water, powered on, system checks are being performed, and all engines are not started.

[0067] Flight phase transition condition 3: The transition condition from ground flight preparation to aircraft stationary standby / low-speed taxiing phase is: the aircraft is on the ground, any engine is started successfully, and the ground speed is ≤ 60 km / h.

[0068] The ground speed is the maximum speed of the front wheels when the handwheel is operated.

[0069] Flight phase transition condition 4: The transition condition from surface flight preparation to aircraft stationary standby / taxi / rescue phase is: the aircraft is on the water surface, any engine is started successfully, and the ground speed is ≤ 70 km / h.

[0070] The above ground speed is the maximum speed at which the water rudder operates.

[0071] Flight phase transition condition 5: The transition condition from land stationary / low-speed taxiing to takeoff roll phase is: the aircraft is on the ground, any two or more engines are at takeoff power, and the ground speed is greater than 60 km / h.

[0072] Flight phase transition condition 6: The transition condition from the water stationary / taxiing / rescue phase to the takeoff roll phase is: the aircraft is on the water surface, with any two or more engines at takeoff power, and the ground speed is greater than 70 km / h.

[0073] Flight Phase Transition Condition 7: The transition condition from the ground to the takeoff phase is: the aircraft is from the ground to the air and either of the following two conditions is met:

[0074] Condition 1: Radio altitude < 450m and any two or more engines are at non-landing power.

[0075] Condition 2: The radio altitude is less than 300 m and any two or more engines are increased to ≥82° by landing power.

[0076] Flight Phase Transition Condition 8: The transition condition from the aircraft leaving the water to the takeoff phase is: the aircraft is from the water surface to the air, and both of the following conditions are met:

[0077] Condition 1: Radio altitude < 450m.

[0078] Condition 2: Any two or more engines are at non-landing power.

[0079] Flight phase transition condition 9: The transition condition for the aircraft to enter the climb / cruise / descent phase is: after rising to a radio altitude of more than 450m; the transition condition for the aircraft to enter the climb / cruise / descent phase is: after descending to a radio altitude of less than 300m.

[0080] Flight Phase Transition Condition 10: The aircraft enters the water-lifting mission when the landing gear is fully retracted and locked, and both of the following conditions are met:

[0081] Condition 1: Ground speed > 70 km / h.

[0082] Condition 2: RA < 15m, the water bucket lowering command is valid.

[0083] The transition conditions for the aircraft to exit the water-lifting mission are: the landing gear is fully retracted and locked, and any one of the following three conditions is met:

[0084] Condition 1: The water bucket retraction command is valid and both water buckets are retracted into place.

[0085] Condition 2: The water bucket receiving instruction is valid and any electric valve is closed.

[0086] Condition 3: After the water bucket receives the command and it is valid for 6 seconds, any electric valve closes timeout.

[0087] Flight phase transition condition 11: The transition condition for the aircraft to enter the water-dropping mission is: the water-dropping door unlock preparation command is valid, or the emergency water-dropping preparation command is valid.

[0088] The conditions for the aircraft to exit the water-dropping mission are: the water-dropping door unlock preparation command is cancelled, or the emergency receive command is valid and lasts for 5 seconds.

[0089] Flight phase transition condition 12: The transition condition for the aircraft to enter the landing phase from the air is: the aircraft is in the air, any two or more engines are at landing power, the radio altitude is less than 300m, and the land and water selector switch is not in the "landing" position.

[0090] Flight phase transition condition 13: The transition condition for the aircraft to enter the water landing phase from the air is: the aircraft is in the air, any two or more engines are at landing power, the radio altitude is less than 300m, and the water and land selector switch is in the "landing" position.

[0091] Flight phase transition condition 14: The transition condition for the aircraft to enter the landing taxi phase from the air is: the aircraft is on the ground, any two or more engines are at landing power, and the ground speed is greater than 60 km / h.

[0092] The ground speed is the maximum speed of the front wheels when the handwheel is operated.

[0093] Flight phase transition condition 15: The transition condition for the aircraft to enter the water taxiing phase from the air is: the aircraft is on the water surface, any two or more engines are at landing power, and the ground speed is greater than 70 km / h.

[0094] The above ground speed is the maximum speed at which the water rudder operates.

[0095] Flight phase transition condition 16: The transition condition for the aircraft from land low-speed taxiing to shutdown phase is: the aircraft is on the ground, any two or more engines are at landing power, and the ground speed is ≤ 60 km / h (after the ground speed is > 60 km / h).

[0096] Flight phase transition condition 17: The transition condition for the aircraft from low-speed taxiing on water to the shutdown phase is: the aircraft is on the water surface, any two or more engines are at landing power, and the ground speed is ≤ 70 km / h (after the ground speed is > 70 km / h).

[0097] Flight phase transition condition 18: Aircraft shutdown phase: The aircraft is on the ground or water, and all engines are shut down for 5 minutes.

[0098] Specifically, this embodiment determines whether the aircraft is on land / water / in the air based on the wheel-load signal fed back by the aircraft's main landing gear system. If there is a wheel-load signal, the aircraft is on land; if there is no wheel-load signal and the radio altitude is less than 3m, the aircraft is on the water; otherwise, the aircraft is in the air.

[0099] See also Figure 3 In this embodiment, the relationship and structure between the valid flight data and the actual flight status are determined according to the flight phase transition conditions, and the structure of the database is refined through a logical model.

[0100] Specifically, this embodiment Figure 3 The flight phase jump state diagram is obtained by creating a flight phase transition model. The flight phase jump state diagram includes all flight phase jump vector relationships that may be experienced during the use of the aircraft, including but not limited to the 45 jump vector relationships shown in the figure, where:

[0101] Jump vector relationship T1 is when the aircraft is powered on and in the land state; jump vector relationship T2 is when the aircraft is started on land; jump vector relationship T3 is when the aircraft accelerates and rolls on land; jump vector relationship T4 is when the aircraft takes off on land; jump vector relationship T5 is when the aircraft climbs to a specified altitude; jump vector relationship T6 is when the aircraft descends to a specified altitude during landing; jump vector relationship T7 is when the aircraft lands; jump vector relationship T8 is when the aircraft decelerates and rolls; jump vector relationship T9 is when the engine is shut down; jump vector relationship T10 is when the engine is started again; jump vector relationship T11 is when the aircraft accelerates and rolls; jump vector relationship T Relationship T12 is the aircraft taking off from the ground; jump vector relationship T13 is the aircraft ending landing and changing to air cruising; jump vector relationship T14 is the aircraft stopping climbing after taking off from the ground; jump vector relationship T15 is the aircraft landing; jump vector relationship T16 is the aircraft decelerating and rolling; jump vector relationship T17 is the engine shut down; jump vector relationship T18 is the aircraft powering off; jump vector relationship T19 is the aircraft performing the water-drawing task; jump vector relationship T20 is the aircraft ending the water-drawing task; jump vector relationship T21 is the aircraft performing the water-dropping task; jump vector relationship T22 is the aircraft preparing to land; jump vector relationship T23 is the aircraft performing the water-dropping mission; jump vector relationship T24 is the aircraft performing the water-dropping mission; jump vector relationship T25 is the aircraft landing and taxiing; jump vector relationship T26 is the aircraft powering on the water surface; jump vector relationship T27 is the aircraft driving on the water surface; jump vector relationship T28 is the aircraft accelerating and taxiing on the water surface; jump vector relationship T29 is the aircraft taking off from the water surface; jump vector relationship T30 is the aircraft climbing to the specified height; jump vector relationship T31 is the aircraft landing on the water and landing at the specified height; jump vector relationship T32 is the aircraft landing on the water; jump vector relationship T33 is the aircraft decelerating and taxiing; jump vector relationship T34 is the aircraft engine shutdown; jump vector relationship T35 is the aircraft engine startup; jump vector relationship T36 is the aircraft acceleration taxiing; jump vector relationship T37 is the aircraft taking off from the water; jump vector relationship T38 is the aircraft climbing to the specified altitude; jump vector relationship T39 is the aircraft landing to the specified altitude; jump vector relationship T40 is the aircraft landing on the water; jump vector relationship T41 is the aircraft deceleration taxiing; jump vector relationship T42 is the aircraft engine shutdown; jump vector relationship T43 is the aircraft power off; jump vector relationship T44 is the aircraft landing on the water; jump vector relationship T45 is the aircraft performing the water dropping mission.

[0102] In this embodiment, the flight phase transition model is deployed in the airborne warning system, and warning suppression is achieved by suppressing part of the warning information in the airborne warning system according to the flight phase transition point where the aircraft is located.

[0103] The above embodiments are only preferred embodiments of the present invention and cannot be used to limit the scope of protection of the present invention. Any non-substantial changes and replacements made by technicians in this field on the basis of the present invention fall within the scope of protection required by the present invention.

Claims

1. A warning suppression method based on the flight phase transition of an amphibious aircraft, characterized in that: include: S1: Collect the parameters of the amphibious aircraft during flight and identify the parameters related to the flight status; S2: Process the flight status parameters, including validity screening and data smoothing, to select valid flight data that characterizes the aircraft's current flight phase; S3: Determine the transition conditions for each flight phase, create a flight phase transition model accordingly, and simulate and analyze the actual flight state based on the valid flight data in the model database; S4: Determine whether the aircraft has entered a flight phase transition process. If so, determine the current flight phase transition point of the aircraft and automatically match the corresponding alarm suppression mechanism based on the flight phase transition point. If not, repeat step S1. S5: Activate the alarm suppression mechanism to automatically suppress the alarm information within the mechanism; S6: Determine whether the aircraft has left the flight phase transition process. If so, release the current alarm suppression state and repeat step S1; if not, maintain the current alarm suppression state.

2. The method for suppressing warnings based on flight phase transition of an amphibious aircraft according to claim 1, characterized in that: Flight parameters are collected in real time through a bus data acquisition system. The flight status parameters include engine speed, landing gear up / down position signal, flap handle position, flap angle, radio altitude, throttle angle, door position / status signal, water hopper position signal, and water release signal.

3. The method for suppressing warnings based on flight phase transition of an amphibious aircraft according to claim 2, characterized in that: The flight status parameters are processed by a computer data processing program, the flight status parameters are screened and analyzed according to a preset screening protocol to obtain the valid flight data, and the valid flight data are subjected to sliding average filtering by a filtering program.

4. The method for suppressing warnings based on flight phase transition of an amphibious aircraft according to claim 3, characterized in that: The flight phases include powering on the aircraft, starting the aircraft engine, accelerating the aircraft, the aircraft leaving the ground or water, climbing to a specified altitude, descending to a specified altitude, landing or landing on water, decelerating the aircraft, shutting down the engine, the aircraft performing a water-pumping mission, the aircraft performing a water-dropping mission, and the aircraft climbing from the air to a specified altitude.

5. The method for suppressing warnings based on flight phase transition of an amphibious aircraft according to claim 4, characterized in that: The transition from the ground to the takeoff phase is when the aircraft is in the air and either of the following two conditions is met: Condition 1: Radio altitude < 450m and any two or more engines are at non-landing power; Condition 2: The radio altitude is less than 300 m and any two or more engines are increased to ≥82° by landing power.

6. The method for suppressing warnings based on flight phase transition of an amphibious aircraft according to claim 4, characterized in that: The transition from leaving the water to taking off is when the aircraft is in the air and both of the following conditions are met: Condition 1: Radio altitude < 450m; Condition 2: Any two or more engines are at non-landing power.

7. The method for suppressing warnings based on flight phase transition of an amphibious aircraft according to claim 4, characterized in that: The aircraft's transition to a water-lifting mission requires that the landing gear be fully retracted and locked, and both of the following conditions be met: Condition 1: Ground speed > 70 km / h; Condition 2: RA < 15m, the water bucket lowering command is valid; The transition conditions for the aircraft to exit the water-lifting mission are: the landing gear is fully retracted and locked, and any one of the following three conditions is met: Condition 1: The water bucket retraction command is valid and both water buckets are retracted into place; Condition 2: The water bucket receiving instruction is valid and any electric valve is closed; Condition 3: After the water bucket receives the command and it is valid for 6 seconds, any electric valve closes timeout.

8. The method for suppressing warnings based on flight phase transition of an amphibious aircraft according to claim 4, characterized in that: The conditions for the aircraft to enter the water-dropping mission are: the water-dropping door unlock preparation command is valid, or the emergency water-dropping preparation command is valid; The conditions for the aircraft to exit the water-dropping mission are: the water-dropping door unlock preparation command is cancelled, or the emergency receive command is valid and lasts for 5 seconds.

9. The method for suppressing warnings based on flight phase transition of an amphibious aircraft according to any one of claims 1 to 8, characterized in that: The relationship and structure between the valid flight data and the actual flight status are determined according to the flight phase transition conditions, and the structure of the database is refined through a logical model.

10. The method for suppressing warnings based on flight phase transition of an amphibious aircraft according to any one of claims 1 to 9, characterized in that: The flight phase transition model is deployed in the airborne warning system, and warning suppression is achieved by suppressing part of the warning information in the airborne warning system according to the flight phase transition point of the aircraft.

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