A method for implementing an aircraft thrust reduction takeoff function

Abstract

The application belongs to the field of aircraft thrust management, and particularly relates to a method for implementing an aircraft thrust reduction take-off function. The method comprises the following steps: step one, determining a thrust reduction take-off scheme, and dividing the thrust reduction take-off scheme into two thrust reduction levels, i.e. a first thrust reduction level and a second thrust reduction level; wherein the first thrust reduction level adopts a graded thrust reduction mode, and the first thrust reduction level comprises a plurality of thrust reduction grades; a second thrust reduction level is arranged between the first thrust reduction grade and the second thrust reduction grade, and the second thrust reduction level adopts a flexible temperature thrust reduction mode; step two, converting thrust values of each thrust reduction grade under standard conditions into take-off weight grades in a manner of equal thrust-weight ratio; step three, selecting a thrust reduction grade according to a take-off weight to calculate take-off performance, and judging whether the selected thrust reduction grade meets take-off requirements; if yes, take-off is performed using the current thrust reduction grade; otherwise, the next thrust reduction grade is judged.

Description

Technical Field

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

[0002] A reduced-thrust takeoff is a takeoff method that uses a lower thrust than the full takeoff thrust of the engine, under certain takeoff conditions and flight environments, while ensuring safe takeoff. This significantly reduces engine turbine inlet temperatures, significantly extending engine life.

[0003] Currently, 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 levels and requires a lot of control logic. As 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 special evaluation and setting work is required for the thrust state used in the climb phase after takeoff. 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 the scope of implementation is constrained by the specification.

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

[0005] The purpose of this 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 the thrust reduction takeoff plan, and divide the thrust reduction takeoff plan into two thrust reduction levels, namely the first thrust reduction level and the second thrust reduction level; wherein,

[0009] The first thrust reduction level adopts a hierarchical 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;

[0010] 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;

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

[0012] Step 3: Select a thrust reduction level based on 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, converting the thrust value under standard conditions of each reduced thrust level into a takeoff weight classification in a manner of equal thrust-to-weight ratio includes:

[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.

[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 three, selecting a thrust reduction level based on 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] A second aspect of the present application provides a device for implementing an aircraft thrust reduction takeoff function, comprising:

[0035] The thrust reduction takeoff plan acquisition module is used to determine the thrust reduction takeoff plan and divide the thrust reduction takeoff plan 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 hierarchical 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;

[0037] 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;

[0038] The 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, comprising a memory, a processor, and a computer program stored in the memory and capable of running on the processor, wherein when the processor executes the computer program, the method for implementing the aircraft thrust reduction takeoff function as described above is implemented.

[0041] A fourth aspect of the present application provides a computer-readable storage medium storing a computer program, which, when executed by a processor, 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 present application discloses a method for implementing the aircraft thrust reduction takeoff function. The first-level thrust reduction level fully utilizes the inherent thrust gear setting of the engine, eliminating the need to add new thrust level settings, thereby greatly reducing the design workload for adding thrust levels. The second-level flexible temperature thrust reduction method is used to achieve precise thrust reduction control between the first and second thrust levels, effectively reducing the operating time of the engine at its maximum state, and achieving a balance between reducing system design complexity, improving reliability, and extending the life of the engine's hot end components. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

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

[0047] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments 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 the embodiments. 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 understood 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 this application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this 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. Therefore, it should not be understood as limiting the scope of protection of this 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 reduced thrust takeoff function, comprising the following steps:

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

[0052] The first thrust reduction level adopts a hierarchical thrust reduction method, and the first thrust reduction level includes multiple thrust reduction levels, namely the first thrust reduction level, the second thrust reduction level, ... the 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 to the takeoff weight classification in the manner of equal thrust-to-weight ratio;

[0055] Step 3: Select a thrust reduction level based on 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 method for implementing the aircraft thrust reduction takeoff function of this application, in step 1, the thrust reduction takeoff plan adopts a thrust reduction method that combines a graded thrust reduction method with a flexible temperature thrust reduction method. This method is achieved by dividing the thrust reduction takeoff plan into two thrust reduction levels: the first thrust reduction level adopts the graded thrust reduction method, and the second thrust reduction level adopts the 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, achieving a macro-thrust reduction function. The engine thrust gears are set in descending order of thrust level: thrust gear 1, thrust gear 2, ..., thrust gear n. The first thrust reduction level corresponds to engine thrust gear 1, the second thrust reduction level corresponds to 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 method for the second thrust reduction level is set within the thrust reduction method for the first thrust reduction level. A flexible temperature thrust reduction method is provided between the first and second thrust reduction levels. That is, when the thrust required for takeoff is between the first and second thrust reduction levels, the flexible temperature thrust reduction adjustment method is used to precisely adjust the thrust demand, minimizing the proportion of maximum thrust used, i.e., the first thrust reduction level.

[0059] In the method for implementing 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.

[0063] In step 3 of the present application's method for implementing the reduced thrust takeoff feature, a detailed thrust level requirement calculation is performed using the takeoff weight classification as the initial quantity for calculating the reduced thrust level / flexible temperature setting value. The selected reduced thrust level is then determined based on takeoff performance to determine whether it meets the takeoff requirements. If the requirements are met, reduced thrust takeoff is implemented. Takeoff performance includes 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 one embodiment of the present application, a certain engine has four thrust state settings: takeoff thrust, maximum continuous thrust, maximum climb thrust, and maximum cruise thrust. The difference between each reduced thrust level is approximately 8% of the maximum takeoff thrust. Given the wide range of aircraft takeoff weights, the specific method for implementing reduced thrust takeoff is as follows:

[0071] 1. Set up a reduced thrust 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] Set the thrust reduction method for the second thrust reduction level: Set a flexible temperature thrust reduction method between the first and second thrust reduction levels. The maximum value of the flexible temperature thrust reduction is 8% of the maximum takeoff thrust. This reduction meets the design specification requirement that the thrust reduction amount does 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 conditions are met, use the current reduced thrust level for takeoff; otherwise, proceed to the next level of judgment. For specific implementation methods and logic, see Figure 3 .

[0078] The present invention relates to a method for implementing an aircraft thrust reduction takeoff function, combining a graded thrust reduction method with a flexible temperature thrust reduction method. The first thrust reduction level utilizes the inherent thrust gear of the engine to set the thrust reduction level to achieve a macroscopic thrust reduction takeoff function. The second thrust reduction level uses the graded thrust reduction method to set the flexible temperature thrust reduction method between the maximum thrust level and the second thrust reduction level within the graded thrust reduction method. The applicable weight of the graded thrust reduction method of the first thrust reduction level is weight-graded, and the weight grades are matched to the corresponding thrust reduction levels. Within a certain weight grade range at the second thrust reduction level, the flexible temperature thrust reduction method is matched within the thrust reduction level based on the difference between the specific takeoff weight and the maximum weight within the weight grade, achieving precise adjustment of the thrust reduction.

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

[0080] 1. Provide a thrust reduction takeoff method that combines a level reduction method with a flexible temperature reduction method, fully utilizing 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 to minimize engine speed when the aircraft takes off at a heavy weight, effectively reducing the time the engine operates at maximum speed and extending 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 this 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, a second aspect of the present application provides an apparatus for implementing the aircraft thrust reduction takeoff function, comprising:

[0085] The thrust reduction takeoff plan acquisition module is used to determine the thrust reduction takeoff plan and divide the thrust reduction takeoff plan 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 hierarchical thrust reduction method, and the first thrust reduction level includes multiple thrust reduction levels, namely the first thrust reduction level, the second thrust reduction level, ... the 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] The 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. When the processor executes the computer program, the above-mentioned method for implementing the aircraft thrust reduction takeoff function is implemented.

[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 method for implementing the aircraft thrust reduction takeoff function.

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

Claims

1. A method for implementing an aircraft thrust reduction takeoff function, characterized in that: include: Step 1: Determine the thrust reduction takeoff plan, and divide the thrust reduction takeoff plan 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 hierarchical 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; 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; Step 2: Convert the thrust value under standard conditions of each reduced thrust level to the takeoff weight classification in the manner of equal thrust-to-weight ratio; Step 3: Select a thrust reduction level based on 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 1, 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 for each reduced thrust level is converted to the takeoff weight classification using 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.

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, select the thrust reduction level based on 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. A device for implementing the reduced thrust takeoff function of an aircraft, characterized in that: include: The thrust reduction takeoff plan acquisition module is used to determine the thrust reduction takeoff plan and divide the thrust reduction takeoff plan 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 hierarchical 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; 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; The 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.

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