Implementation method of thrust-reduced takeoff function of aircraft

Abstract

The invention belongs to the field of aircraft thrust management, and particularly relates to an implementation method of a thrust-reduced takeoff function of an aircraft. The method comprises the following steps: step 1, determining a thrust-reducing takeoff scheme, and dividing the thrust-reducing takeoff scheme into two thrust-reducing levels, namely a first thrust-reducing level and a second thrust-reducing level; wherein the first thrust reduction level adopts a level thrust reduction mode, and the first thrust reduction level comprises a plurality of thrust reduction levels; setting a second thrust reduction level between the first thrust reduction level and the second thrust reduction level, wherein the second thrust reduction level adopts a flexible temperature thrust reduction mode; step 2, converting the thrust value of each thrust reduction grade under the standard condition into a takeoff weight grade according to an equal thrust-weight ratio mode; and 3, selecting a thrust reduction level according to the takeoff weight to calculate the takeoff performance, judging whether the selected thrust reduction level meets the takeoff requirement or not, if so, taking off by using the current thrust reduction level, and otherwise, entering judgment of the next thrust reduction level.

Description

Technical Field

[0001] The present application belongs to the field of aircraft thrust management, and in particular to a method for implementing an aircraft thrust reduction takeoff function. Background Art

[0002] Reduced thrust takeoff refers to a takeoff method that uses a thrust lower than the full takeoff thrust of the engine under certain takeoff conditions and flight environment, provided that the aircraft takes off safely. Using reduced thrust takeoff can greatly reduce the engine turbine inlet temperature, which is of great significance to extending the engine life.

[0003] At present, the common thrust reduction takeoff methods are divided into the graded thrust reduction method and the flexible temperature thrust reduction takeoff method. Both methods are used on transport aircraft. Airbus series aircraft tend to use the flexible temperature thrust reduction takeoff method, and Boeing series aircraft use the graded thrust reduction and flexible temperature thrust reduction methods. However, the two thrust reduction methods are generally used separately. For aircraft with a large takeoff weight range, the graded thrust reduction method generally requires setting more thrust reduction levels, which requires a lot of work for setting and calibrating the engine thrust level and requires more control logic. For the flexible temperature thrust reduction method, if the flexible temperature thrust reduction method is implemented within the takeoff weight range envelope of the aircraft, the thrust reduction value may often exceed the maximum reduction required by the specification, and the thrust state used in the climb phase after takeoff needs to be specially evaluated and set. In summary, according to the conventional implementation method, the use of the two thrust reduction methods separately has problems such as large design workload, complex logic, and implementation scope restricted by specifications.

[0004] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0005] The purpose of the present application is to provide a method for implementing an aircraft thrust reduction takeoff function to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] A first aspect of the present application provides a method for implementing an aircraft thrust reduction takeoff function, comprising:

[0008] Step 1: Determine a thrust reduction takeoff plan, and divide the thrust reduction takeoff plan into two thrust reduction levels, namely a first thrust reduction level and a second thrust reduction level; wherein,

[0009] The first thrust reduction level adopts a graded thrust reduction method, and the first thrust reduction level includes a plurality of thrust reduction levels, namely a first thrust reduction level, a second thrust reduction level, ... an nth thrust reduction level;

[0010] The second thrust reduction level is set between the first thrust reduction level and the second thrust reduction level, and the second thrust reduction level adopts a flexible temperature thrust reduction method;

[0011] Step 2: Convert the thrust value under standard conditions of each reduced thrust level into the takeoff weight classification in the manner of equal thrust-to-weight ratio;

[0012] Step 3: Select the thrust reduction level according to the takeoff weight to calculate the takeoff performance, and determine whether the selected thrust reduction level meets the takeoff requirements. If so, use the current thrust reduction level for takeoff, otherwise proceed to the next thrust reduction level determination.

[0013] In at least one embodiment of the present application, in step one, the thrust reduction level of the first thrust reduction level is set according to the inherent thrust state of the engine.

[0014] In at least one embodiment of the present application, the first thrust reduction level corresponds to the maximum thrust state of the engine.

[0015] In at least one embodiment of the present application, the thrust reduction levels of the first thrust reduction level include a first thrust reduction level, a second thrust reduction level, a third thrust reduction level, ..., and an nth thrust reduction level, wherein:

[0016] The first thrust reduction level is engine thrust state 1;

[0017] The second thrust reduction level is engine thrust state 2;

[0018] The third thrust reduction level is engine thrust state 3;

[0019] …

[0020] The nth reduced thrust level is engine thrust state n;

[0021] Among them, engine thrust state 1>engine thrust state 2>engine thrust state 3>…>engine thrust state n.

[0022] In at least one embodiment of the present application, the thrust difference between two adjacent thrust reduction levels is x% of the maximum takeoff thrust.

[0023] In at least one embodiment of the present application, the maximum value of the flexible temperature thrust reduction of the second thrust reduction level is x% of the maximum takeoff thrust.

[0024] In at least one embodiment of the present application, in step 2, the thrust value under standard conditions of each reduced thrust level is converted into a takeoff weight classification in a manner of equal thrust-to-weight ratio, including:

[0025] THX1 / W MTO=THX2 / W2=……=THXn / W n

[0026] Among them, W MTO is the maximum takeoff weight, THX1, THX2, ..., THXn are the thrusts of the corresponding reduced thrust levels, W2, ..., W n They are the weights of the corresponding takeoff weight classifications respectively.

[0027] In at least one embodiment of the present application, the takeoff performance includes takeoff field length, takeoff climb capability, and departure trajectory.

[0028] In at least one embodiment of the present application, in step 3, selecting a thrust reduction level according to the takeoff weight includes:

[0029] When the thrust required for takeoff weight is less than or equal to the first thrust reduction level and greater than the second thrust reduction level, use the flexible temperature thrust reduction method for takeoff;

[0030] When the thrust required for takeoff weight is less than or equal to the second reduced thrust level and greater than the third reduced thrust level, use the second reduced thrust level for takeoff;

[0031] When the thrust required for takeoff weight is less than or equal to the third reduced thrust level and greater than the fourth reduced thrust level, use the third reduced thrust level for takeoff;

[0032] …

[0033] When the thrust required for takeoff weight is less than or equal to the n-1th reduced thrust level and greater than the nth reduced thrust level, use the n-1th reduced thrust level for takeoff.

[0034] The second aspect of the present application provides a device for implementing an aircraft thrust reduction takeoff function, comprising:

[0035] The thrust reduction takeoff scheme acquisition module is used to determine the thrust reduction takeoff scheme, and divide the thrust reduction takeoff scheme into two thrust reduction levels, namely the first thrust reduction level and the second thrust reduction level; wherein,

[0036] The first thrust reduction level adopts a graded thrust reduction method, and the first thrust reduction level includes a plurality of thrust reduction levels, namely a first thrust reduction level, a second thrust reduction level, ... an nth thrust reduction level;

[0037] The second thrust reduction level is set between the first thrust reduction level and the second thrust reduction level, and the second thrust reduction level adopts a flexible temperature thrust reduction method;

[0038] A takeoff weight classification conversion module is used to convert the thrust value under standard conditions of each reduced thrust level into the takeoff weight classification in a manner of equal thrust-to-weight ratio;

[0039] The takeoff performance calculation module is used to select the thrust reduction level according to the takeoff weight to calculate the takeoff performance, and determine whether the selected thrust reduction level meets the takeoff requirements. If so, the current thrust reduction level is used for takeoff, otherwise the next thrust reduction level is determined.

[0040] The third aspect of the present application provides an electronic device, including a memory, a processor, and a computer program stored in the memory and capable of running on the processor, wherein the processor implements the method for implementing the aircraft thrust reduction takeoff function as described above when executing the computer program.

[0041] The fourth aspect of the present application provides a computer-readable storage medium, which stores a computer program. When the computer program is executed by a processor, it can implement the method for implementing the aircraft thrust reduction takeoff function as described above.

[0042] The invention has at least the following beneficial technical effects:

[0043] The implementation method of the aircraft thrust reduction takeoff function of the present application is that the first-level thrust reduction level makes full use of the inherent thrust gear setting of the engine, and there is no need to add new thrust level settings, which greatly reduces the design workload of adding thrust levels; through the second-level flexible temperature thrust reduction method, accurate thrust reduction control between the first thrust level and the second thrust level is achieved, effectively reducing the working time of the engine in the maximum state, and achieving a balance between reducing the complexity of system design, improving reliability and extending the life of the engine hot end components. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 This is a design flow chart of a thrust reduction takeoff scheme according to an embodiment of the present application;

[0045] Figure 2 is a flow chart of selecting a thrust reduction level according to takeoff weight in one embodiment of the present application;

[0046] Figure 3 The present invention is a logic diagram for determining takeoff thrust of a reduced thrust takeoff function according to an embodiment of the present application. DETAILED DESCRIPTION

[0047] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0048] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0049] The following is combined with Figures 1 to 3 This application is described in further detail.

[0050] A first aspect of the present application provides a method for implementing an aircraft thrust reduction takeoff function, comprising the following steps:

[0051] Step 1: Determine a thrust reduction takeoff plan, and divide the thrust reduction takeoff plan into two thrust reduction levels, namely a first thrust reduction level and a second thrust reduction level; wherein,

[0052] The first thrust reduction level adopts a graded thrust reduction method, and the first thrust reduction level includes multiple thrust reduction levels, namely, a first thrust reduction level, a second thrust reduction level, ..., an nth thrust reduction level;

[0053] A second thrust reduction level is set between the first thrust reduction level and the second thrust reduction level, and the second thrust reduction level adopts a flexible temperature thrust reduction method;

[0054] Step 2: Convert the thrust value under standard conditions of each reduced thrust level into the takeoff weight classification in the manner of equal thrust-to-weight ratio;

[0055] Step 3: Select the thrust reduction level according to the takeoff weight to calculate the takeoff performance, and determine whether the selected thrust reduction level meets the takeoff requirements. If so, use the current thrust reduction level for takeoff, otherwise proceed to the next thrust reduction level determination.

[0056] In the implementation method of the aircraft thrust reduction takeoff function of the present application, in step 1, the thrust reduction takeoff scheme adopts a thrust reduction method that combines a graded thrust reduction method with a flexible temperature thrust reduction method. The thrust reduction takeoff scheme is divided into two thrust reduction levels, the first thrust reduction level adopts a graded thrust reduction method, and the second thrust reduction level adopts a flexible temperature thrust reduction method.

[0057] In a preferred embodiment of the present application, Figure 1 As shown, the thrust reduction level of the first thrust reduction level is set according to the inherent thrust state of the engine to realize the macro thrust reduction function. Among them, the thrust gear of the engine is set to thrust gear 1, thrust gear 2, ..., thrust gear n in order from large to small according to the thrust level; the first thrust reduction level corresponds to the engine thrust gear 1, the second thrust reduction level corresponds to the engine thrust gear 2, and so on. The first thrust reduction level corresponds to the maximum thrust state of the engine.

[0058] Advantageously, the thrust reduction mode of the second thrust reduction level is set in the thrust reduction mode of the first thrust reduction level. Between the first thrust reduction level and the second thrust reduction level, a flexible temperature thrust reduction mode is set, that is, when the thrust required for takeoff of the aircraft is between the first thrust reduction level and the second thrust reduction level, the flexible temperature thrust reduction adjustment mode is used to accurately adjust the thrust demand, and the ratio of using the maximum thrust, that is, the first thrust reduction level, is minimized.

[0059] In the implementation method of the aircraft thrust reduction takeoff function of the present application, in step 2, the takeoff weight classification is set according to the set thrust reduction level.

[0060] In a preferred embodiment of the present application, the thrust value under standard conditions of each reduced thrust level is converted into a takeoff weight classification in a manner of equal thrust-to-weight ratio, including:

[0061] THX1 / W MTO =THX2 / W2=……=THXn / W n

[0062] Among them, W MTO is the maximum takeoff weight, THX1, THX2, ..., THXn are the thrusts of the corresponding reduced thrust levels, W2, ..., W n They are the weights of the corresponding takeoff weight classifications respectively.

[0063] In the implementation method of the aircraft thrust reduction takeoff function of the present application, in step 3, the takeoff weight classification is used as the initial quantity for calculating the thrust reduction level / flexible temperature setting value, and a detailed thrust level requirement calculation is performed, and the selected thrust reduction level is judged based on the takeoff performance to determine whether it meets the takeoff requirements, and the thrust reduction takeoff is implemented when the takeoff requirements are met. Among them, the takeoff performance includes the takeoff field length, takeoff climb capability, and departure trajectory.

[0064] In a preferred embodiment of the present application, Figure 2 As shown in the figure, the thrust reduction level is selected according to the takeoff weight, including:

[0065] When the thrust required for takeoff weight is less than or equal to the first thrust reduction level and greater than the second thrust reduction level, use the flexible temperature thrust reduction method for takeoff;

[0066] When the thrust required for takeoff weight is less than or equal to the second reduced thrust level and greater than the third reduced thrust level, use the second reduced thrust level for takeoff;

[0067] When the thrust required for takeoff weight is less than or equal to the third reduced thrust level and greater than the fourth reduced thrust level, use the third reduced thrust level for takeoff;

[0068] …

[0069] When the thrust required for takeoff weight is less than or equal to the n-1th reduced thrust level and greater than the nth reduced thrust level, use the n-1th reduced thrust level for takeoff.

[0070] In a specific embodiment of the present application, a certain type of engine has four thrust state settings: takeoff thrust, maximum continuous thrust, maximum climb thrust, and maximum cruise thrust. The thrust difference between each two reduced thrust levels is approximately 8% of the maximum takeoff thrust. The takeoff weight range of the aircraft is relatively large. The specific method for implementing reduced thrust takeoff is as follows:

[0071] 1. Set up a thrust reduction takeoff plan

[0072] Set the thrust reduction method for the first thrust reduction level: level thrust reduction method, the thrust reduction levels are set as follows: the first thrust reduction level is the takeoff thrust state, the second thrust reduction level is the maximum continuous thrust state, the third thrust reduction level is the maximum climb thrust state, and the fourth thrust reduction level is the maximum cruise thrust state.

[0073] Setting the thrust reduction method of the second thrust reduction level: setting a flexible temperature thrust reduction method between the first thrust reduction level and the second thrust reduction level, with the maximum value of the flexible temperature thrust reduction being 8% of the maximum takeoff thrust. This reduction amount meets the requirement of the design specification that the thrust reduction amount shall not exceed 25% of the maximum takeoff thrust.

[0074] 2. Set takeoff weight classification based on the principle of equal thrust-to-weight ratio:

[0075] THX1 / W MTO =THX2 / W2=THX3 / W3=THX4 / W4

[0076] Among them, W MTO is the maximum takeoff weight, which is a known quantity. Thus, W2, W3, and W4 can be calculated.

[0077] 3. For a known takeoff weight Wx, determine whether it is less than the weight classification W3, calculate the takeoff climb gradient, and determine whether the takeoff climb gradient meets the requirements. If so, calculate the takeoff field length and determine whether the takeoff field length meets the requirements. If so, check the departure trajectory. If all are met, use the current thrust reduction level for takeoff; otherwise, proceed to the next level of judgment. For specific implementation methods and logic, see Figure 3 .

[0078] The implementation method of the aircraft thrust reduction takeoff function of the present application combines the graded thrust reduction method with the flexible temperature thrust reduction method. The graded thrust reduction method of the first thrust reduction level uses the inherent thrust gear of the engine to set the thrust reduction level to realize the macroscopic thrust reduction takeoff function. The second thrust reduction level is to set the flexible temperature thrust reduction method between the maximum thrust level and the second thrust reduction level in the graded thrust reduction method, and weight classification is performed on the applicable weight of the graded thrust reduction method of the first thrust reduction level, and the weight classification is matched with the corresponding thrust reduction level; when within a certain weight classification range under the second thrust reduction level, the flexible temperature thrust reduction method is matched within the thrust reduction level according to the difference between the specific takeoff weight and the maximum weight in the weight classification, so as to realize the precise adjustment of thrust reduction.

[0079] The aircraft thrust reduction takeoff function implementation method of the present application has the following beneficial effects:

[0080] 1. Provide a thrust reduction takeoff method that combines the thrust reduction method with the flexible temperature thrust reduction method, making full use of the original thrust level setting of the engine and greatly reducing the design workload of increasing the thrust level;

[0081] 2. A flexible temperature thrust reduction mode is set between the maximum thrust reduction level and the second thrust reduction level, so that the engine operating speed can be reduced as much as possible when the aircraft takes off with a large weight, effectively reducing the time the engine works at the maximum state and extending the engine life;

[0082] 3. Strike a balance between reducing system design complexity, improving reliability and extending the life of engine hot end components.

[0083] 4. The method for determining the takeoff thrust reduction level / flexible temperature provided in the present application facilitates the development of computer calculation programs, forming calculation software for the thrust reduction takeoff function, which is convenient for users to use.

[0084] Based on the above-mentioned method for implementing the aircraft thrust reduction takeoff function, the second aspect of the present application provides an aircraft thrust reduction takeoff function implementation device, comprising:

[0085] The thrust reduction takeoff scheme acquisition module is used to determine the thrust reduction takeoff scheme, and divide the thrust reduction takeoff scheme into two thrust reduction levels, namely the first thrust reduction level and the second thrust reduction level; wherein,

[0086] The first thrust reduction level adopts a graded thrust reduction method, and the first thrust reduction level includes multiple thrust reduction levels, namely, a first thrust reduction level, a second thrust reduction level, ..., an nth thrust reduction level;

[0087] A second thrust reduction level is set between the first thrust reduction level and the second thrust reduction level, and the second thrust reduction level adopts a flexible temperature thrust reduction method;

[0088] A takeoff weight classification conversion module is used to convert the thrust value under standard conditions of each reduced thrust level into the takeoff weight classification in a manner of equal thrust-to-weight ratio;

[0089] The takeoff performance calculation module is used to select the thrust reduction level according to the takeoff weight to calculate the takeoff performance, and determine whether the selected thrust reduction level meets the takeoff requirements. If so, the current thrust reduction level is used for takeoff, otherwise the next thrust reduction level is determined.

[0090] The third aspect of the present application provides an electronic device, including a memory, a processor, and a computer program stored in the memory and capable of running on the processor, and the processor implements the above-mentioned method for implementing the aircraft thrust reduction takeoff function when executing the computer program.

[0091] The fourth aspect of the present application provides a computer-readable storage medium, which stores a computer program. When the computer program is executed by a processor, it can realize the above-mentioned aircraft thrust reduction takeoff function implementation method.

[0092] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A method for implementing an aircraft thrust reduction takeoff function, characterized in that: include: Step 1: Determine a thrust reduction takeoff plan, and divide the thrust reduction takeoff plan into two thrust reduction levels, namely a first thrust reduction level and a second thrust reduction level; wherein, The first thrust reduction level adopts a graded thrust reduction method, and the first thrust reduction level includes a plurality of thrust reduction levels, namely a first thrust reduction level, a second thrust reduction level, ... an nth thrust reduction level; The second thrust reduction level is set between the first thrust reduction level and the second thrust reduction level, and the second thrust reduction level adopts a flexible temperature thrust reduction method; Step 2: Convert the thrust value under standard conditions of each reduced thrust level into the takeoff weight classification in the manner of equal thrust-to-weight ratio; Step 3: Select the thrust reduction level according to the takeoff weight to calculate the takeoff performance, and determine whether the selected thrust reduction level meets the takeoff requirements. If so, use the current thrust reduction level for takeoff, otherwise proceed to the next thrust reduction level determination.

2. The method for implementing the aircraft thrust reduction takeoff function according to claim 1, characterized in that: In step one, the thrust reduction level of the first thrust reduction level is set according to the inherent thrust state of the engine.

3. The method for implementing the aircraft thrust reduction takeoff function according to claim 2, characterized in that: The first thrust reduction level corresponds to the maximum thrust state of the engine.

4. The method for implementing the aircraft thrust reduction takeoff function according to claim 3, characterized in that: The thrust reduction levels of the first thrust reduction level include a first thrust reduction level, a second thrust reduction level, a third thrust reduction level, ..., and an nth thrust reduction level, wherein: The first thrust reduction level is engine thrust state 1; The second thrust reduction level is engine thrust state 2; The third thrust reduction level is engine thrust state 3; … The nth reduced thrust level is engine thrust state n; Among them, engine thrust state 1>engine thrust state 2>engine thrust state 3>…>engine thrust state n.

5. The method for implementing the aircraft thrust reduction takeoff function according to claim 4, characterized in that: The thrust difference between two adjacent reduced thrust levels is x% of the maximum takeoff thrust.

6. The method for implementing the aircraft thrust reduction takeoff function according to claim 5, characterized in that: The maximum value of the flexible temperature thrust reduction of the second thrust reduction level is x% of the maximum takeoff thrust.

7. The method for implementing the aircraft thrust reduction takeoff function according to claim 1, characterized in that: In step 2, the thrust value under standard conditions of each reduced thrust level is converted to the takeoff weight classification in the same thrust-to-weight ratio, including: THX1 / W MTO =THX2 / W2=……=THXn / W n Among them, W MTO is the maximum takeoff weight, THX1, THX2, ..., THXn are the thrusts of the corresponding reduced thrust levels, W2, ..., W n They are the weights of the corresponding takeoff weight classifications respectively.

8. The method for implementing the aircraft thrust reduction takeoff function according to claim 7, characterized in that: The takeoff performance includes takeoff field length, takeoff climb capability, and departure trajectory.

9. The method for implementing the aircraft thrust reduction takeoff function according to claim 8, characterized in that: In step 3, the thrust reduction level is selected based on the takeoff weight, including: When the thrust required for takeoff weight is less than or equal to the first thrust reduction level and greater than the second thrust reduction level, use the flexible temperature thrust reduction method for takeoff; When the thrust required for takeoff weight is less than or equal to the second reduced thrust level and greater than the third reduced thrust level, use the second reduced thrust level for takeoff; When the thrust required for takeoff weight is less than or equal to the third reduced thrust level and greater than the fourth reduced thrust level, use the third reduced thrust level for takeoff; … When the thrust required for takeoff weight is less than or equal to the n-1th reduced thrust level and greater than the nth reduced thrust level, use the n-1th reduced thrust level for takeoff.

10. An aircraft thrust reduction takeoff function implementation device, characterized in that: include: The thrust reduction takeoff scheme acquisition module is used to determine the thrust reduction takeoff scheme, and divide the thrust reduction takeoff scheme into two thrust reduction levels, namely the first thrust reduction level and the second thrust reduction level; wherein, The first thrust reduction level adopts a graded thrust reduction method, and the first thrust reduction level includes a plurality of thrust reduction levels, namely a first thrust reduction level, a second thrust reduction level, ... an nth thrust reduction level; The second thrust reduction level is set between the first thrust reduction level and the second thrust reduction level, and the second thrust reduction level adopts a flexible temperature thrust reduction method; A takeoff weight classification conversion module is used to convert the thrust value under standard conditions of each reduced thrust level into the takeoff weight classification in a manner of equal thrust-to-weight ratio; The takeoff performance calculation module is used to select the thrust reduction level according to the takeoff weight to calculate the takeoff performance, and determine whether the selected thrust reduction level meets the takeoff requirements. If so, the current thrust reduction level is used for takeoff, otherwise the next thrust reduction level is determined.

11. An electronic device comprising a memory, a processor, and a computer program stored in the memory and capable of running on the processor, characterized in that: When the processor executes the computer program, the method for implementing the aircraft thrust reduction takeoff function as described in any one of claims 1 or 9 is implemented.

12. A computer-readable storage medium storing a computer program, characterized in that: When the computer program is executed by a processor, it is capable of implementing the aircraft thrust reduction takeoff function implementation method as described in any one of claims 1 or 9.

Images