Alarm suppression method based on flight phase conversion of amphibious aircraft

Abstract

The invention provides an alarm suppression method based on flight phase conversion of an amphibious aircraft. The method comprises the following steps: receiving and identifying flight state parameters in the flight process of the aircraft; screening out effective flight data for representing the current flight stage; determining conversion conditions of each flight stage, creating a flight stage conversion model according to the conversion conditions, and performing simulation analysis on the actual flight state according to the effective flight data; judging whether the aircraft enters a flight stage conversion process or not, if so, determining a flight stage conversion point where the aircraft is located currently, and automatically matching a corresponding alarm suppression mechanism according to the flight stage conversion point; starting an alarm suppression mechanism, and automatically suppressing alarm information in the mechanism; and judging whether the aircraft leaves the flight stage conversion process, and if so, releasing the current alarm suppression state. According to the method, the flight stage conversion process is analyzed through the model, and the alarm suppression mechanism is started in the process, so that the effects of automatically suppressing unnecessary alarm information and improving the flight safety and efficiency are achieved.

Description

Technical Field

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

[0002] With the development of aviation technology, amphibious aircraft, as a new type of transportation, can be used as seaplanes for taking off and landing at land airports. It has powerful functions for performing emergency rescue, forest fire fighting, marine patrol and other special tasks. Therefore, there is great potential for demand in the domestic and foreign aviation markets. In addition to air cruising, amphibious aircraft also need to operate on the water surface and complete rescue missions. Therefore, its flight phase is more complicated than that of ordinary cruise aircraft, especially during the transition process of flight phases, which puts higher requirements on the flight efficiency and safety of the aircraft.

[0003] However, during the entire flight, the aircraft's onboard warning system will inform the flight crew of various warning information such as warning information of various systems on board, threat information of the aircraft's external environment, and even false alarms and false alarms. Even during the critical flight phase transition process, unnecessary warning information interference may occur, which causes the crew to process a large amount of warning information and cause 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 the safety and efficiency of flight.

[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 comprises:

[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 to characterize the current flight phase of the aircraft.

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

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

[0012] S5: Start the alarm suppression mechanism to automatically suppress the alarm information in the mechanism.

[0013] S6: Determine whether the aircraft leaves 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, wherein the flight status parameters include but are not limited to engine speed, landing gear retraction / 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 parse 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 any one 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 from landing power to ≥ 82°.

[0020] A further solution is that the transition condition from the aircraft leaving the water surface to the take-off stage 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 that the transition condition for the aircraft to enter the water-drawing mission is that the landing gear is fully retracted and locked, and the following two conditions are met at the same time:

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

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

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

[0027] Condition 1: The water bucket collection instruction 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 condition for the aircraft to enter the water dropping mission is: 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 unlocking preparation command is cancelled, or the emergency receiving 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 to 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. The present invention establishes a mathematical model of flight phase transition according to the characteristics and flight requirements of amphibious aircraft, analyzes the flight phase transition process by simulating parameter changes during flight, and activates the corresponding warning suppression mechanism during this process to suppress unnecessary warning information, thereby reducing interference during flight phase transition. Especially in high-risk flight phases, such as takeoff and landing, automatically suppressing unnecessary warning information can greatly avoid distracted operations by pilots, improve the concentration of flight control, reduce operational errors caused by distraction, and ensure focus on critical mission execution.

[0036] 2. The present invention suppresses unnecessary warning information during the transition of critical flight phases and releases the warning suppression after the transition is completed, so that the crew can 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. The present invention suppresses unnecessary warning information during the flight phase transition process with a large workload, making the warning system more intelligent and humane in serving flight safety. The crew does not have to continuously 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 alarm suppression method for flight phase transition of the present invention is of great significance for improving flight safety, crew work efficiency, and the intelligent and humanized development of the alarm system. It also promotes the continuous progress and improvement of the modern civil aircraft alarm system.

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

[0041] Figure 1 The present invention is a flow chart of the warning suppression method based on the 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] In order to make the purpose, technical solution and advantages of the embodiment of the present invention clearer, the technical solution of the embodiment of the present invention will be clearly and completely described below in conjunction with the drawings of the embodiment of the present invention. Obviously, the described embodiment is a part of the embodiment of the present invention, not all of the embodiments. Based on the described embodiment 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 a warning 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 to characterize the current flight phase of the aircraft.

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

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

[0051] S5: Start the alarm suppression mechanism to automatically suppress the alarm information in the mechanism.

[0052] S6: Determine whether the aircraft leaves 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 float on water without relying on other external assistance. At the same time, the aircraft also has a landing gear for traveling on land.

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

[0055] Specifically, this embodiment determines the best 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 can be applied 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 requirements.

[0057] In this embodiment, flight parameters are collected in real time through a bus data acquisition system, and 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 are subjected to sliding average filtering by a filtering program.

[0059] Specifically, this embodiment performs smooth filtering, burr removal or jitter removal on the effective 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 through computer program in the present embodiment is only exemplary and not the only way. For example, data can also be processed through hardware processor chips and filter elements.

[0062] In this embodiment, the flight phases 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.

[0063] Specifically, the flight phase described in this embodiment is used to characterize the entire operation scenario of the aircraft, including powering on the ground to starting the engine, from accelerating and taxiing on the ground to taking off from land or water, from climbing to cruising in the air to executing a specific mission and then landing, from landing or landing on the water to decelerating and taxiing of the aircraft, from stopping the aircraft to shutting down the engine 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 condition 1: The transition condition for the land flight preparation phase is: the aircraft is on land, powered on, system checks are being carried out and all engines are not started.

[0066] Flight phase transition condition 2: The transition condition for the water flight preparation phase is: the aircraft is on water, powered on, system checks are being carried out 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 ≤60km / h.

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

[0069] Flight phase transition condition 4: The transition condition from surface flight preparation to aircraft stationary standby / taxiing / rescue phase is: the aircraft is on the water surface, any engine is started successfully, and the ground speed is ≤70km / 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 take-off rolling phase is: the aircraft is on the ground, and any two or more engines are at take-off power, and the ground speed is greater than 60km / h.

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

[0073] Flight phase transition condition 7: 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:

[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 from landing power to ≥ 82°.

[0076] Flight phase transition condition 8: 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:

[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 transition condition for the aircraft to enter the water-drawing mission is: the landing gear is fully retracted and locked, and the following two conditions are met at the same time:

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

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

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

[0084] Condition 1: The water bucket collection instruction 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 unlocking preparation command is cancelled, or the emergency receiving 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, and the radio altitude is less than 300m, and the land and water selection 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, and the radio altitude is less than 300m, and the water and land selection switch is in the "water 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 60km / h.

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

[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 70km / 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 low-speed taxiing on land to the 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 greater than 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 ≤70km / h (after the ground speed is greater than 70km / 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 / air through the wheel-load signal fed back by the aircraft 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 conversion 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, and 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 45 jump vector relationships as shown in the figure, where:

[0101] Jump vector relationship T1 means the aircraft is powered on and in land state; jump vector relationship T2 means starting the aircraft on land; jump vector relationship T3 means the aircraft is accelerating and rolling on land; jump vector relationship T4 means the aircraft is taking off on land; jump vector relationship T5 means the aircraft is climbing to a specified altitude; jump vector relationship T6 means the aircraft is descending to a specified altitude during landing; jump vector relationship T7 means the aircraft is landing; jump vector relationship T8 means the aircraft is decelerating and rolling; jump vector relationship T9 means the engine is shut down; jump vector relationship T10 means the engine is started again; jump vector relationship T11 means the aircraft is accelerating and rolling; jump vector relationship T24 means the aircraft is turning off the engine; jump vector relationship T25 means the aircraft is turning off the engine; jump vector relationship T26 means the aircraft is turning on the engine again; jump vector relationship T27 means the aircraft is turning on the engine again; jump vector relationship T28 means the aircraft is accelerating and rolling; jump vector relationship T29 means the aircraft is turning off the engine; jump vector relationship T29 means the aircraft is turning on the engine again; jump vector relationship T21 means the aircraft is accelerating and rolling; jump vector relationship T22 means the aircraft is turning on the engine again; jump vector relationship T23 means the aircraft is turning on the engine again; jump vector relationship T24 means the aircraft is turning on the engine again; jump vector relationship T25 means the aircraft is turning on the engine again; jump vector relationship T26 means the aircraft is turning on the engine again; jump vector relationship T27 means the aircraft is turning on the engine again; jump vector relationship T28 means the aircraft is turning on the engine again; jump vector relationship T29 ... Relationship T12 means the aircraft takes off from the ground; jump vector relationship T13 means the aircraft terminates landing and changes to aerial cruising; jump vector relationship T14 means the aircraft stops climbing after leaving the ground; jump vector relationship T15 means the aircraft lands; jump vector relationship T16 means the aircraft decelerates and rolls; jump vector relationship T17 means the engine is shut down; jump vector relationship T18 means the aircraft powers off; jump vector relationship T19 means the aircraft performs a water-drawing task; jump vector relationship T20 means the aircraft ends the water-drawing task; jump vector relationship T21 means the aircraft performs a water-dropping task; jump vector relationship T22 means the aircraft is ready 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 means shutting down the aircraft engine; jump vector relationship T35 means starting the aircraft engine; jump vector relationship T36 means accelerating and taxiing of the aircraft; jump vector relationship T37 means taking off from the water; jump vector relationship T38 means climbing to a specified height; jump vector relationship T39 means descending to a specified height; jump vector relationship T40 means landing on the water; jump vector relationship T41 means decelerating and taxiing of the aircraft; jump vector relationship T42 means shutting down the aircraft; jump vector relationship T43 means powering off the aircraft; jump vector relationship T44 means landing on the water; jump vector relationship T45 means the aircraft performs a 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-mentioned 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 substitutions made by technicians in this field on the basis of the present invention shall fall within the scope of protection required by the present invention.

Claims

1. A warning suppression method based on flight phase transition of 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: Perform data processing on the flight status parameters, including validity screening and data smoothing, to screen out valid flight data for characterizing the current flight phase of the aircraft; S3: determining the transition conditions of each flight phase, and creating a flight phase transition model accordingly, and performing simulation analysis on the actual flight state according to the valid flight data in the model database; S4: Determine whether the aircraft enters the flight phase transition process. If so, determine the flight phase transition point where the current aircraft is located, and automatically match the corresponding alarm suppression mechanism according to the flight phase transition point; if not, repeat step S1; S5: starting the alarm suppression mechanism to automatically suppress the alarm information in the mechanism; S6: Determine whether the aircraft leaves 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 amphibious aircraft according to claim 1 is characterized in that: The flight parameters are collected in real time through the bus data acquisition system, and 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.

3. The warning suppression method based on the flight phase transition of an amphibious aircraft according to claim 2 is 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 and the valid flight data are obtained therefrom, and the valid flight data are subjected to sliding average filtering by a filtering program.

4. The warning suppression method based on the flight phase transition of an amphibious aircraft according to claim 3 is characterized in that: The flight phases 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-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 amphibious aircraft according to claim 4 is characterized in 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: 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 from landing power to ≥ 82°.

6. The warning suppression method based on the flight phase transition of an amphibious aircraft according to claim 4 is characterized in 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: 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 amphibious aircraft according to claim 4 is characterized in that: The transition conditions for the aircraft to enter the water-drawing mission are: the landing gear is fully retracted and locked, and the following two conditions are met at the same time: Condition 1: Ground speed > 70km / h; Condition 2: RA<15m, the water bucket lowering command is valid; The transition conditions for the aircraft to exit the water-pumping mission are: the landing gear is fully retracted and locked, and any of the following three conditions is met: Condition 1: The water bucket collection instruction 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 amphibious aircraft according to claim 4 is characterized in that: The transition 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; The conditions for the aircraft to exit the water-dropping mission are: the water-dropping door unlocking preparation command is cancelled, or the emergency receiving 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 effective flight data and the actual flight status are determined according to the flight phase conversion 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 to 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.

Images