Method for determining output power taking into account air turbine starter control valve opening rate

Abstract

The application belongs to the technical field of air turbine starter driving aero-engine starting, and particularly relates to a method for determining output power by considering the opening rate of an air turbine starter control valve, which considers the influence of the opening rate of the air turbine starter control valve on the output power requirement, is based on analysis and construction of a torque output characteristic equation of the air turbine starter driving aero-engine starting, assigns the maximum output power of the air turbine starter and the speed corresponding to the maximum torque output point of the air turbine starter, uses a rotor torque balance equation to iteratively solve the torque output characteristic equation of the air turbine starter driving aero-engine starting, and finally obtains the requirement of the maximum output power of the air turbine starter driving aero-engine starting, so as to guide the design and selection of the air turbine starter, and the possibility of frequent failure of aero-engine starting caused by insufficient output torque of the air turbine starter can be well reduced.

Description

Technical Field

[0001] This application belongs to the field of air turbine starter driving aero-engine starting technology, specifically relating to a method for determining output power considering the opening rate of the air turbine starter control valve. Background Technology

[0002] Currently, the main method for analyzing the power demand of aero-engines on air turbine starters is through simulation calculations. In the simulation calculation process, the influence of frictional drag torque, aerodynamic drag torque, environmental factors, mechanical efficiency, and power extraction on the power demand of air turbine starters is mainly considered, but the influence of the opening rate of the air turbine starter control valve on the power demand is not considered.

[0003] The control valve is located on the air intake pipe of the air turbine starter. After receiving the start command, it gradually opens from the fully closed state to the fully open state. The high-temperature and high-pressure airflow gradually enters the air turbine starter as the control valve opens, driving the output shaft of the air turbine starter to rotate and accelerate the aircraft engine, thus starting the aircraft engine.

[0004] After receiving the start command, the opening of the air turbine starter control valve is a gradual process, not an instantaneous one. A fast opening rate of the control valve results in a rapid rise in air pressure at the air turbine starter inlet, leading to a faster and larger initial torque build-up, which is beneficial for the rapid start of the aircraft engine. Conversely, a slow opening rate of the control valve results in a slower rise in air pressure at the air turbine starter inlet, leading to a slower and smaller initial torque build-up, which is not conducive to the rapid start of the aircraft engine.

[0005] In the simulation calculation of the output power requirement of the air turbine starter, the influence of the control valve opening rate on the output power requirement is ignored. It is assumed that the control valve opens instantaneously and is always in a fully open state. This results in the calculated initial torque of the air turbine starter being established quickly and with a large value. When achieving the same starting performance, the calculated maximum output power requirement of the air turbine starter is lower. If the air turbine starter is designed and selected in this way, there is a possibility that the aircraft engine will fail to start frequently due to insufficient output torque of the air turbine starter. This will affect the test efficiency of the aircraft engine during bench testing. If an in-flight shutdown occurs after installation, it will be difficult to reliably guarantee the efficient starting of the aircraft engine, threatening the safety of the aircraft and its pilots.

[0006] This application is made in view of the aforementioned technical deficiencies. Summary of the Invention

[0007] The purpose of this application is to provide a method for determining output power considering the opening rate of the air turbine starter control valve, in order to overcome or mitigate at least one of the known technical defects.

[0008] The technical solution of this application is:

[0009] A method for determining output power considering the opening rate of an air turbine starter control valve includes:

[0010] Step 1: Determine the control valve opening time and the aircraft engine start-up time;

[0011] Step 2: Construct the torque output characteristic equation for the air turbine starter driving the aero engine. For the part of the torque output less than the speed corresponding to the maximum torque output point, it is represented by a quadratic function of the speed. For the part of the torque output greater than the speed corresponding to the maximum torque output point, it is represented by a linear function of the speed.

[0012] Step 3: Assign a value to the maximum output power of the air turbine starter. Usually, a smaller value can be assigned first.

[0013] Step 4: Assign a value to the speed corresponding to the maximum torque output of the air turbine starter. An appropriate value can be given based on experience.

[0014] Step 5: Based on the maximum output power of the air turbine starter and the rotational speed corresponding to the maximum output point, derive the torque output characteristic equation of the air turbine starter driving the aero engine to start.

[0015] Step 6: Substitute the torque output characteristic equation of the air turbine starter driving the aircraft engine into the rotor torque balance equation to calculate the air turbine starter speed.

[0016] Step 7: Determine whether the rotational speed of the air turbine starter when controlling the opening time matches the rotational speed corresponding to the maximum torque output point of the air turbine starter. If not, adjust the value assigned to the rotational speed corresponding to the maximum torque output point of the air turbine starter.

[0017] Step 8: Substitute the torque output characteristic equation of the air turbine starter driving the aero engine into the rotor torque balance equation to calculate the aero engine speed.

[0018] Step 9: Determine whether the time it takes for the aircraft engine to reach idle speed matches the aircraft engine start-up time. If not, adjust the maximum output power assigned to the air turbine starter.

[0019] According to at least one embodiment of this application, in the above-described method for determining output power considering the opening rate of the air turbine starter control valve, in step two, a torque output characteristic equation for the air turbine starter driving the aero-engine to start is constructed. For the portion of the rotational speed less than the maximum torque output point, it is represented by a quadratic function of the rotational speed; for the portion of the rotational speed greater than the maximum torque output point, it is represented by a linear function of the rotational speed. Specifically:

[0020]

[0021] in,

[0022] M ST The output torque of the air turbine starter is N·m;

[0023] N ST The speed of the air turbine starter is r / min;

[0024] N ST,A The rotational speed (r / min) corresponding to point A, where the output torque of the air turbine starter is at its maximum value.

[0025] a and b are the parts of the rotational speed corresponding to point A, which is less than the maximum torque output of the air turbine starter. The parameters are calculated using a quadratic function relationship.

[0026] M ST0 k ST The parameters are calculated using a linear function for the portion of the rotational speed corresponding to point A, which is greater than the maximum torque output of the air turbine starter.

[0027] According to at least one embodiment of this application, in the above-described method for determining output power considering the opening rate of the air turbine starter control valve, the rotor torque balance equations described in steps six and eight are specifically as follows:

[0028]

[0029] in,

[0030] M ST The output torque of the air turbine starter is N·m;

[0031] M T The torque of an aero-engine turbine is expressed in N·m.

[0032] M C The aerodynamic drag torque of the aero-engine compressor is expressed in N·m.

[0033] M Z The frictional drag torque of the aero-engine is expressed in N·m.

[0034] t represents the engine start-up time, in seconds.

[0035] M F The drag torque of the lubricating oil accessory for aero engines, in N·m;

[0036] M P The drag torque generated by the power extraction of the aircraft engine is expressed in N·m.

[0037] M D The torque reduction of the high-pressure turbine due to the performance degradation of the aero-engine is expressed in N·m.

[0038] J is the moment of inertia of the aero-engine rotor, kg·m2;

[0039] N H The value is the high-pressure rotor speed of the aero-engine, in r / min.

[0040] According to at least one embodiment of this application, in the above-described method for determining output power considering the opening rate of the air turbine starter control valve, step seven, determining whether the rotational speed of the air turbine starter during the control opening time matches the rotational speed corresponding to the maximum torque output point of the air turbine starter, specifically involves:

[0041] When the speed of the air turbine starter at the control opening time and the speed corresponding to the maximum torque output point of the air turbine starter differ by more than the speed difference threshold, it is determined that the speed of the air turbine starter at the control opening time and the speed corresponding to the maximum torque output point of the air turbine starter are inconsistent.

[0042] When the difference between the speed of the air turbine starter during the controlled opening time and the speed corresponding to the maximum torque output point of the air turbine starter is less than the speed difference threshold, it is determined that the speed of the air turbine starter during the controlled opening time and the speed corresponding to the maximum torque output point of the air turbine starter are consistent.

[0043] According to at least one embodiment of this application, in the above-described method for determining output power considering the opening rate of the air turbine starter control valve, the speed difference threshold is taken as 5%.

[0044] According to at least one embodiment of this application, in the above-described method for determining output power considering the opening rate of the air turbine starter control valve, step nine, determining whether the time it takes for the aircraft engine speed to reach idle speed matches the aircraft engine start time, specifically involves:

[0045] When the time it takes for the aircraft engine to reach its idle speed and the time it starts up differ by more than a time difference threshold, it is determined that the time it takes for the aircraft engine to reach its idle speed and the time it starts up are inconsistent.

[0046] When the time it takes for the aircraft engine to reach its idle speed and the time it starts up are less than the time difference threshold, it is determined that the time it takes for the aircraft engine to reach its idle speed and the time it starts up are consistent.

[0047] According to at least one embodiment of this application, in the above-described method for determining output power considering the opening rate of the air turbine starter control valve, the time difference threshold is specifically taken as 1%.

[0048] This application has at least the following beneficial technical effects:

[0049] This paper provides a method for determining the output power considering the opening rate of the air turbine starter control valve. Taking into account the impact of the air turbine starter control valve opening rate on the output power requirement, and based on the analysis and construction of the torque output characteristic equation for the air turbine starter driving the aero-engine, the method assigns values ​​to the maximum output power of the air turbine starter and the rotational speed corresponding to the maximum torque output point of the air turbine starter. Using the rotor torque balance equation, the torque output characteristic equation for the air turbine starter driving the aero-engine is iteratively solved, ultimately yielding the maximum output power requirement for the air turbine starter to drive the aero-engine. This method guides the design and selection of air turbine starters, effectively reducing the possibility of frequent aero-engine starting failures due to insufficient air turbine starter output torque. Attached Figure Description

[0050] Figure 1 This is a schematic diagram of the torque output characteristics of an air turbine starter driving an aero engine, provided in an embodiment of this application.

[0051] Figure 2 This is a schematic diagram of the torque output characteristics of an air turbine starter driving an aero engine and the torque loss related to the opening time of the control valve, provided in an embodiment of this application.

[0052] Figure 3 This is a schematic diagram of the method for determining output power considering the opening rate of the air turbine starter control valve provided in the embodiments of this application.

[0053] To better illustrate this embodiment, some parts of the accompanying drawings may be omitted. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0054] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0055] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms indicating direction used in this application description are used only to indicate relative direction or positional relationship; when the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "comprising" as used in this application description indicates that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, but does not exclude other elements or objects.

[0056] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0057] The analysis of the power demand of an aero-engine on the air turbine starter is based on the rotor torque balance equation. The left side of the equation consists of the active torque and the drag torque, forming the net residual torque. The active torque mainly consists of the output torque of the air turbine starter and the turbine torque of the aero-engine, as detailed below:

[0058]

[0059] in,

[0060] M ST The output torque of the air turbine starter is N·m;

[0061] M T The turbine torque of an aero engine is N·m;

[0062] M C The aerodynamic drag torque of the aero-engine compressor is expressed in N·m.

[0063] M Z The frictional drag torque of the aero-engine is expressed in N·m.

[0064] t represents the engine start-up time, in seconds.

[0065] M F The drag torque of the lubricating oil accessory for aero engines, in N·m;

[0066] M P The drag torque generated by the power extraction of the aircraft engine is expressed in N·m.

[0067] M D The torque reduction of the high-pressure turbine due to the performance degradation of the aero-engine is expressed in N·m.

[0068] J is the moment of inertia of the aero-engine rotor, kg·m2;

[0069] N H The value is the high-pressure rotor speed of the aero-engine, in r / min.

[0070] Upon receiving the start command, the control valve gradually opens, and the torque generated by the air turbine starter gradually increases as the start control valve opens. When the control valve is fully open, the torque generated by the air turbine starter reaches its maximum value. Figure 1 At point A, the output torque gradually decreases linearly as the speed of the air turbine starter increases.

[0071] The torque output characteristics of an air turbine starter driving an aircraft engine can be divided into two segments, with the maximum torque output point A as the dividing point. According to the torque measurement test results of the air turbine starter, for the portion of the torque output less than the speed corresponding to the maximum torque output point A, the output torque of the air turbine starter can be approximately fitted as a quadratic function of the speed. For the portion of the torque output greater than the speed corresponding to the maximum torque output point A, the output torque of the air turbine starter can be approximately fitted as a linear function of the speed, as specifically expressed below:

[0072]

[0073] in,

[0074] M ST The output torque of the air turbine starter is N·m;

[0075] N ST The speed of the air turbine starter is r / min. When the air turbine starter drives the aircraft engine to start, the speed is converted according to the transmission ratio.

[0076] N ST,A The rotational speed (r / min) corresponding to point A, where the output torque of the air turbine starter is at its maximum value.

[0077] a and b are the parts of the rotational speed corresponding to point A, which is less than the maximum torque output of the air turbine starter. The parameters are calculated using a quadratic function relationship.

[0078] MST0 k ST For the portion of the rotational speed corresponding to point A, which is greater than the maximum torque output of the air turbine starter, the parameters are calculated using a linear function, where M ST0 This represents the portion of the torque output exceeding the maximum value of the air turbine starter torque at point A, at which the torque is zero, expressed in N·m. ST This represents the slope of the portion of the rotational speed corresponding to point A, which is greater than the maximum torque output of the air turbine starter.

[0079] a, b, M ST0 k ST The specific values ​​can be determined through experiments, or given empirically, or calculated when determining the speed corresponding to the maximum power and torque output point A of the air turbine starter.

[0080] Analysis reveals that the main difference between considering and not considering the impact of the air turbine starter control valve opening rate on output power demand lies in the speed portion corresponding to the maximum torque output point A of the air turbine starter. Ignoring the impact of the air turbine starter control valve opening rate on output power demand neglects the torque loss during the initial stage of valve opening. Figure 2 As shown in the shaded area, the longer the control valve is open, the greater the torque loss.

[0081] An air turbine starter motor drives the aircraft engine to start.

[0082] Based on the above, this application provides a method for determining output power considering the opening rate of the air turbine starter control valve, such as... Figure 3 As shown.

[0083] Step 1: Determine the control valve opening time and the aircraft engine start-up time.

[0084] Step 2: Construct the torque output characteristic equation for the air turbine starter to drive the aero-engine. For the part of the torque output less than the speed corresponding to the maximum torque output point, it is represented by a quadratic function of the speed. For the part of the torque output greater than the speed corresponding to the maximum torque output point, it is represented by a linear function of the speed, as shown in formula (2).

[0085] Step 3: Assign a value to the maximum output power of the air turbine starter. Usually, a smaller value can be assigned first.

[0086] Step 4: Assign a value to the speed corresponding to the maximum torque output of the air turbine starter. An appropriate value can be given based on experience.

[0087] Step 5: Based on the maximum output power of the air turbine starter and the rotational speed corresponding to the maximum output point, derive the torque output characteristic equation of the air turbine starter driving the aero engine to start.

[0088] Step 6: Substitute the torque output characteristic equation of the air turbine starter driving the aero engine into the rotor torque balance equation, as shown in formula (1), and calculate the air turbine starter speed.

[0089] Step 7: Determine whether the rotational speed of the air turbine starter when controlling the opening time matches the rotational speed corresponding to the maximum torque output point of the air turbine starter, i.e., whether the difference exceeds the speed difference threshold. The speed difference threshold can be set to 5%. If not, adjust the value assigned to the rotational speed corresponding to the maximum torque output point of the air turbine starter.

[0090] Step 8: Substitute the torque output characteristic equation of the air turbine starter driving the aero engine into the rotor torque balance equation, as shown in formula (1), and calculate the aero engine speed.

[0091] Step 9: Determine whether the time it takes for the aircraft engine to reach idle speed matches the aircraft engine start-up time, i.e., whether the difference exceeds the time difference threshold. The time difference threshold can be set to 1%. If not, adjust the maximum output power assignment of the air turbine starter to finally obtain the maximum output power required for the air turbine starter to drive the aircraft engine to start.

[0092] The above-described embodiment discloses a method for determining output power considering the opening rate of the air turbine starter control valve. This method considers the impact of the air turbine starter control valve opening rate on output power requirements. Based on the analysis and construction of the torque output characteristic equation for the air turbine starter driving the aero-engine, it assigns values ​​to the maximum output power of the air turbine starter and the rotational speed corresponding to the maximum torque output point of the air turbine starter. Using the rotor torque balance equation, iteratively solves the torque output characteristic equation for the air turbine starter driving the aero-engine, ultimately obtaining the maximum output power requirement for the air turbine starter to drive the aero-engine. This guides the design and selection of air turbine starters, effectively reducing the possibility of frequent aero-engine starting failures due to insufficient air turbine starter output torque.

[0093] In a specific example, the method for determining the output power considering the opening rate of the air turbine starter control valve is as follows.

[0094] Step 1: Determine the control valve opening time as 2.0s and the aircraft engine start time as 55s.

[0095] Step 2: Construct the torque output characteristic equation for the air turbine starter to drive the aero-engine, as shown in formula (2).

[0096] Step 3: Assign a maximum output power of 80kW to the air turbine starter.

[0097] Step 4: Assign a speed of 500 r / min to the point where the air turbine starter torque output is at its maximum.

[0098] Step 5: Based on the maximum output power of the air turbine starter and the rotational speed corresponding to the maximum output point, the torque output characteristic equation for the air turbine starter driving the aircraft engine is derived as follows:

[0099]

[0100] Step Six: The torque output characteristic equation M for starting the aircraft engine using an air turbine starter. ST,1 Substituting the rotor torque balance equation, as shown in formula (1), the air turbine starter speed is calculated.

[0101] Step 7: When the air turbine starter rotates at 550 r / min during the control opening time of 2.0 s, the difference between this value and the assigned speed of 500 r / min corresponding to the maximum torque output of the air turbine starter exceeds the speed difference threshold by more than 5%. Repeat steps 4 to 6.

[0102] Adjust and increase the value assigned to the speed corresponding to the maximum torque output point of the air turbine starter, and adjust the value assigned to the speed corresponding to the maximum torque output point of the air turbine starter to 525 r / min.

[0103] The torque output characteristic equation for starting an aero engine driven by an air turbine starter is derived as follows:

[0104]

[0105] The torque output characteristic equation M for starting an aircraft engine using an air turbine starter. ST,2 Substituting the rotor torque balance equation, as shown in formula (1), the air turbine starter speed is calculated.

[0106] The air turbine starter rotates at 525 r / min when the control opening time is 2.0 s, which is consistent with the assigned speed of 525 r / min corresponding to the maximum torque output point of the air turbine starter. Therefore, the torque output characteristic equation for the air turbine starter to drive the aero engine is determined to be M. ST,2 .

[0107] Step 8: The torque output characteristic equation M for starting the aircraft engine using an air turbine starter. ST,2Substituting the rotor torque balance equation, as shown in formula (1), the engine speed of the aero-engine is calculated.

[0108] Step 9: Determine that the time it takes for the aircraft engine to reach idle speed is 60 seconds, which is more than 1% different from the aircraft engine start time of 55 seconds. Repeat steps 3 to 8.

[0109] The maximum output power of the air turbine starter was adjusted and increased to 90kW. The calculated time for the aircraft engine to reach idle speed was 57s, which is still more than 1% different from the aircraft engine start time of 55s.

[0110] The maximum output power of the air turbine starter was adjusted and increased again, and the maximum output power of the air turbine starter was adjusted to 100kW. The calculated time for the aircraft engine to reach idle speed was 55s, which is consistent with the aircraft engine start time of 55s.

[0111] Therefore, under the above requirements of a control valve opening time of 2.0s and an aero-engine start-up time of 55s, the maximum output power required for the air turbine starter to drive the aero-engine should not be less than 100kW.

[0112] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A method for determining output power considering the opening rate of an air turbine starter control valve, characterized in that, include: Step 1: Determine the control valve opening time and the aircraft engine start-up time; Step 2: Construct the torque output characteristic equation for the air turbine starter driving the aero engine. For the part of the torque output less than the speed corresponding to the maximum torque output point, it is represented by a quadratic function of the speed. For the part of the torque output greater than the speed corresponding to the maximum torque output point, it is represented by a linear function of the speed. Step 3: Assign a value to the maximum output power of the air turbine starter; Step 4: Assign a value to the speed corresponding to the maximum torque output point of the air turbine starter; Step 5: Based on the maximum output power and the rotational speed corresponding to the maximum torque output point of the air turbine starter, derive the torque output characteristic equation of the air turbine starter driving the aero engine to start. Step 6: Substitute the torque output characteristic equation of the air turbine starter driving the aircraft engine into the rotor torque balance equation to calculate the air turbine starter speed. Step 7: Determine whether the rotational speed of the air turbine starter when controlling the opening time matches the rotational speed corresponding to the maximum torque output point of the air turbine starter. If not, adjust the value assigned to the rotational speed corresponding to the maximum torque output point of the air turbine starter. Step 8: Substitute the torque output characteristic equation of the air turbine starter driving the aero engine into the rotor torque balance equation to calculate the aero engine speed. Step 9: Determine whether the time it takes for the aircraft engine to reach idle speed matches the aircraft engine start-up time. If not, adjust the maximum output power assigned to the air turbine starter.

2. The method for determining output power considering the opening rate of the air turbine starter control valve according to claim 1, characterized in that, In step two, the torque output characteristic equation for the air turbine starter driving the aero-engine is constructed. For the portion of the torque output less than the speed corresponding to the maximum torque output point, it is represented as a quadratic function of the speed; for the portion greater than the speed corresponding to the maximum torque output point, it is represented as a linear function of the speed. Specifically: in, M ST The output torque of the air turbine starter is N·m; N ST The speed of the air turbine starter is r / min; N ST,A The rotational speed (r / min) corresponding to point A, where the output torque of the air turbine starter is at its maximum value. a and b are the parts of the rotational speed corresponding to point A, which is less than the maximum torque output of the air turbine starter. The parameters are calculated using a quadratic function relationship. M ST0 k ST The parameters are calculated using a linear function for the portion of the rotational speed corresponding to point A, which is greater than the maximum torque output of the air turbine starter.

3. The method for determining output power considering the opening rate of the air turbine starter control valve according to claim 1, characterized in that, The rotor torque balance equations mentioned in steps six and eight are as follows: in, M ST The output torque of the air turbine starter is N·m; M T The torque of an aero-engine turbine is expressed in N·m. M C The aerodynamic drag torque of the aero-engine compressor is expressed in N·m. M Z The frictional drag torque of the aero-engine is expressed in N·m. t represents the engine start-up time, in seconds. M F The drag torque of the lubricating oil accessory for aero engines, in N·m; M P The drag torque generated by the power extraction of the aircraft engine is expressed in N·m. M D The torque reduction of the high-pressure turbine due to the performance degradation of the aero-engine is expressed in N·m. J is the moment of inertia of the aero-engine rotor, kg·m2; N H The value is the high-pressure rotor speed of the aero-engine, in r / min.

4. The method for determining output power considering the opening rate of the air turbine starter control valve according to claim 1, characterized in that, In step seven, it is determined whether the rotational speed of the air turbine starter during the controlled opening time matches the rotational speed corresponding to the maximum torque output point of the air turbine starter. Specifically: When the speed of the air turbine starter at the control opening time and the speed corresponding to the maximum torque output point of the air turbine starter differ by more than the speed difference threshold, it is determined that the speed of the air turbine starter at the control opening time and the speed corresponding to the maximum torque output point of the air turbine starter are inconsistent. When the difference between the speed of the air turbine starter during the controlled opening time and the speed corresponding to the maximum torque output point of the air turbine starter is less than the speed difference threshold, it is determined that the speed of the air turbine starter during the controlled opening time and the speed corresponding to the maximum torque output point of the air turbine starter are consistent.

5. The method for determining output power considering the opening rate of the air turbine starter control valve according to claim 4, characterized in that, The speed difference threshold is set to 5%.

6. The method for determining output power considering the opening rate of the air turbine starter control valve according to claim 1, characterized in that, In step nine, it is determined whether the time it takes for the aircraft engine to reach idle speed matches the aircraft engine start-up time. Specifically: When the time it takes for the aircraft engine to reach its idle speed and the time it starts up differ by more than a time difference threshold, it is determined that the time it takes for the aircraft engine to reach its idle speed and the time it starts up are inconsistent. When the time it takes for the aircraft engine to reach its idle speed and the time it takes for the aircraft engine to start are less than the time difference threshold, it is determined that the time it takes for the aircraft engine to reach its idle speed and the time it takes for the aircraft engine to start are consistent.

7. The method for determining output power considering the opening rate of the air turbine starter control valve according to claim 6, characterized in that, The time difference threshold is specifically set at 1%.

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