Civil high-bypass-ratio turbofan engine thrust management flight test method
By acquiring the thrust management flight test points and engine test state speed points, and controlling the test engine to conduct flight tests, the lack of thrust management flight tests for civil high-bypass turbofan engines has been solved, and the performance verification and optimization of the thrust management system has been realized, meeting the high economy and low noise requirements of modern civil aircraft.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- AECC COMML AIRCRAFT ENGINE CO LTD
- Filing Date
- 2024-11-27
- Publication Date
- 2026-05-29
Smart Images
Figure CN122108614A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of aircraft engine technology, and more specifically, to a flight test method for thrust management of a civil high-bypass turbofan engine. Background Technology
[0002] High-bypass turbofan engines, as the mainstream power plant for modern civil aircraft, possess advantages such as high thrust, low fuel consumption, and low noise. With the rapid development of aviation technology, more stringent requirements have been placed on civil engines, such as higher fuel economy, lower noise, and fewer pollutant emissions. To meet these requirements, thrust management flight test methods have emerged, aiming to verify the performance and reliability of engine thrust management systems through flight tests. However, specific thrust management flight test techniques are currently lacking. Summary of the Invention
[0003] The following provides a brief overview of one or more aspects to offer a basic understanding of them. This overview is not an exhaustive summary of all conceived aspects, nor is it intended to identify key or decisive elements of all aspects, nor to define the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form to prepare for the more detailed descriptions that follow.
[0004] The present invention includes, for example, providing a flight test method for thrust management of a civil high-bypass turbofan engine, which can improve the shortcomings of flight tests for thrust management of civil high-bypass turbofan engines.
[0005] The embodiments of the present invention can be implemented as follows:
[0006] An embodiment of the present invention provides a flight test method for thrust management of a civil high-bypass turbofan engine, comprising:
[0007] Obtain thrust management flight test sites;
[0008] Obtain the engine's test operating speed point;
[0009] Based on the priority of the thrust management flight test points and the engine's operating speed points, the test engine is controlled to conduct flight tests.
[0010] Based on the engine flight test results, the engine steady-state test parameters were collected.
[0011] In addition, the flight test method for thrust management of a civil high-bypass turbofan engine provided in the embodiments of the present invention may also have the following additional technical features:
[0012] Optionally, the step of obtaining the thrust management flight test point includes:
[0013] The flight envelope engine thrust assessment point and the flight envelope engine fuel consumption rate assessment point are obtained as thrust management flight test points.
[0014] Optionally, the step of obtaining the thrust management flight test point further includes:
[0015] Typical points on the boundary of the engine flight envelope required by the aircraft, as well as typical points on the flight profile required by the aircraft, are obtained as thrust management flight test points.
[0016] Optionally, the step of obtaining the thrust management flight test point further includes:
[0017] Typical points for engine model correction within the flight envelope were obtained, with flight altitude intervals of 1500m and Mach number intervals of 0.05 to 0.1, serving as thrust management flight test points.
[0018] Optionally, the step of controlling the test engine to conduct flight tests based on the priority of thrust management flight test points and the engine's operating speed points includes:
[0019] Control the aircraft platform to fly to the required flight altitude and speed for the thrust management flight test point, where the ambient temperature is lower than the thrust holding inflection point temperature;
[0020] Control the non-test engines to ensure the flight platform maintains stable straight-line level flight at the thrust management flight test point;
[0021] The test engine was controlled to operate at the test speed point for flight testing.
[0022] Optionally, the step of controlling the test engine to conduct flight tests at the test operating speed point includes:
[0023] The test engine is controlled to operate stably at the test operating speed point for 5 minutes. If the allowable tolerance of the flight altitude relative to the thrust management flight test point is ±100m, the allowable tolerance of the flight Mach number relative to the thrust management flight test point is ±0.01, and the change in the total temperature of the engine inlet is less than or equal to 2℃, then the engine steady-state test parameters are collected.
[0024] Otherwise, repeat the steps described above for controlling the non-test engine to enable the flight platform to fly stably in a straight line at the thrust management flight test point.
[0025] Optionally, the step of collecting engine steady-state test parameters based on engine flight test results includes:
[0026] After 5 minutes of steady-state flight of the engine, the steady-state test parameters of the engine are collected for 30 seconds. If the allowable tolerance of flight altitude relative to thrust management flight test point is ±50m, the allowable tolerance of flight Mach number relative to thrust management flight test point is ±0.005, and the change in total engine inlet temperature is less than or equal to 2℃, then the engine working status is judged.
[0027] Otherwise, if the allowable tolerance for flight altitude relative to thrust management flight test points is ±100m, the allowable tolerance for flight Mach number relative to thrust management flight test points is ±0.01, and the total temperature variation of the engine inlet is less than or equal to 2℃, the data should be collected again.
[0028] If the tolerance for the flight altitude relative to the thrust management flight test point is ±100m, the tolerance for the flight Mach number relative to the thrust management flight test point is ±0.01, and the total temperature change of the engine inlet is less than or equal to 2℃, then the steps of controlling the non-test engine to make the flight platform fly stably in a straight line at the thrust management flight test point are repeated.
[0029] Optionally, the step of obtaining the test operating speed point of the engine includes:
[0030] Obtain the test operating speed points of the engine from its maximum stable operating state to its idle state in the air;
[0031] If the allowable tolerance for the flight altitude relative to the thrust management flight test point is ±50m, the allowable tolerance for the flight Mach number relative to the thrust management flight test point is ±0.005, and the engine inlet total temperature variation is less than or equal to 2℃, then the steps for judging the engine operating status include:
[0032] If the engine is in idle state, execute the process of acquiring the thrust management flight test point; otherwise, execute the process of acquiring the engine's test operating speed point.
[0033] Optionally, the step of acquiring the thrust management flight test point is performed when the engine is in idle operating condition; otherwise, the step of acquiring the engine's test operating speed point includes:
[0034] If the engine is in idle speed mode, execute the process of acquiring the thrust management flight test point; otherwise, execute the process of acquiring the engine speed points of the last three test operating states of the engine in the previous thrust management flight test point.
[0035] Optionally, the test operating speed points include typical speed points and steady-state speed points.
[0036] The beneficial effects of the flight test method for thrust management of a civilian high-bypass turbofan engine according to embodiments of the present invention include, for example:
[0037] A flight test method for thrust management of a civil high-bypass turbofan engine includes: acquiring thrust management flight test points; acquiring the engine's test operating speed points; and controlling the test engine to conduct flight tests based on the priority of the thrust management flight test points and the engine's operating speed points.
[0038] Flight tests were conducted at different thrust management flight test points, and at different operating speed points for the same thrust management flight test point. Steady-state test parameters of the engine were recorded to determine the engine's steady-state flight performance, benchmark against the aircraft's thrust requirements, and verify the degree to which the engine's thrust requirements in the flight state are met. The applicability of the thrust management adjustment plan during flight was verified, and condition-based optimization was achieved. The overall engine performance steady-state model was calibrated and corrected, the overall performance steady-state model correction technology was verified, and the steady-state model was optimized. Attached Figure Description
[0039] The above-described features and advantages of the present invention will be better understood after reading the following detailed description of embodiments of the present disclosure in conjunction with the accompanying drawings. In the drawings, components are not necessarily drawn to scale, and components having similar related characteristics or features may have the same or similar reference numerals.
[0040] Figure 1 A flowchart illustrating the flight test method for thrust management of a civil high-bypass turbofan engine provided in an embodiment of the present invention;
[0041] Figure 2 A flowchart of a flight test method for thrust management of a civil high-bypass turbofan engine provided in an embodiment of the present invention. Detailed Implementation
[0042] The present invention will now be described in detail with reference to the accompanying drawings and specific embodiments. It should be noted that the aspects described below with reference to the accompanying drawings and specific embodiments are merely exemplary and should not be construed as limiting the scope of protection of the present invention in any way.
[0043] In the description of this invention, it should be noted that if terms such as "upper," "lower," "inner," "outer," or "vertical" appear, the orientation or positional relationship indicated is based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of this invention is usually placed when in use, and does not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.
[0044] At the same time, it should be noted that the terms "first" and "second" are used only for distinguishing descriptions and should not be interpreted as indicating or implying relative importance.
[0045] In the description of this invention, it should also be noted that, unless otherwise explicitly specified or limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, an integral connection, or a detachable connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium, or a connection within two components, etc. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.
[0046] The following is combined with Figures 1 to 2 The flight test method for thrust management of a civil high-bypass turbofan engine provided in this embodiment is described in detail.
[0047] Please refer to Figure 1 This embodiment provides a flight test method for thrust management of a civilian high-bypass turbofan engine.
[0048] An embodiment of the present invention provides a flight test method for thrust management of a civil high-bypass turbofan engine, comprising:
[0049] Step S1: Obtain the thrust management flight test point;
[0050] Step S2: Obtain the test operating speed point of the engine;
[0051] Step S3: Control the test engine to conduct flight tests according to the priority of the thrust management flight test points and the engine's operating speed points;
[0052] Step S4: Collect engine steady-state test parameters based on engine flight test results.
[0053] It should be noted that: Civil High Bypass Ratio Turbofan Engine: A civil high bypass ratio turbofan engine is a turbofan engine with a bypass ratio of 4 or higher installed in civil aircraft. Thrust Management Schedule (PMS): Reasonable and reliable thrust management control is the prerequisite and guarantee for the normal operation of a civil turbofan engine. The thrust management schedule is a table written into the engine's electronic controller for steady-state thrust management control, defining the target and target value of steady-state engine control at different thrust levels within the engine's operating envelope. Flight Test: Flight tests are experimental verifications conducted on the test engine mounted on an aircraft platform.
[0054] Flight tests were conducted at different thrust management flight test points, and at different operating speed points for the same thrust management flight test point. Steady-state test parameters of the engine were recorded to correct and improve the engine thrust, speed, or power.
[0055] This embodiment allows for the testing of thrust management and adjustment plans for civil high-bypass turbofan engines on aircraft platforms. It enables the assessment of the engine's steady-state flight performance, benchmarking against the aircraft's thrust requirements, and verifying the degree to which the engine's thrust requirements are met during flight. It also verifies the applicability of the thrust management and adjustment plan during flight, enabling condition-based optimization; verifies and corrects the engine's overall performance steady-state model, verifies the overall performance steady-state model correction technology, and optimizes the steady-state model.
[0056] In this embodiment, step S1, the step of obtaining the thrust management flight test point, includes:
[0057] Step S11: Obtain the engine thrust assessment point of the flight envelope; and step S12: Obtain the engine fuel consumption rate assessment point of the flight envelope, which will serve as the thrust management flight test point.
[0058] Select points within the engine envelope where engine thrust and fuel consumption need to be assessed. Engine thrust assessment points are generally during takeoff and at maximum continuous speed, while fuel consumption assessment points are generally during cruise.
[0059] In this embodiment, step S1, the step of obtaining the thrust management flight test point, further includes:
[0060] Step S13: Obtain typical points on the boundary of the engine flight envelope required by the aircraft; and Step S14: Obtain typical points on the flight profile required by the aircraft as thrust management flight test points.
[0061] Typical points on the boundary of the engine flight envelope required by the aircraft are selected. These are test points on the boundary of the envelope. The aircraft manufacturer wants to know the state and capability of the engine operating on the boundary, so they require flight tests to be conducted at these test points.
[0062] Typical points in a flight profile refer to the different states an aircraft experiences during a typical flight cycle: takeoff, climb, cruise, descent, and landing. The aircraft manufacturer selects representative points from these different states for engine testing. Typical points in a flight profile are representative test points within the engine's flight envelope, such as test points for thrust level changes at altitude, or commonly used state points specified by the aircraft manufacturer.
[0063] In this embodiment, step S1, the step of obtaining the thrust management flight test point, further includes:
[0064] Step S15: Obtain typical points for engine model correction within the flight envelope, with flight altitude intervals of 1500m and Mach number intervals of 0.05 to 0.1, as thrust management flight test points. For example, select 6 test points at equal speed intervals at each altitude.
[0065] Reference Figure 2 In this embodiment, step S3, which involves controlling the test engine to conduct flight tests based on the priority of the thrust management flight test points and the engine's operating speed, includes:
[0066] Step S31: Control the aircraft platform to fly to the required flight altitude and speed of the thrust management flight test point, wherein the ambient temperature is lower than the thrust holding inflection point temperature;
[0067] Step S32: Control the non-test engine to make the flight platform fly stably in a straight line at the thrust management flight test point;
[0068] Step S33: Control the test engine to conduct a flight test at the test operating speed point.
[0069] Prioritize all thrust management flight test sites, with assessment sites having the highest priority and model correction requirement test sites having the lowest priority. Based on the altitude, Mach number, and flight test priority of all test sites, and considering the aircraft platform conditions, comprehensively schedule thrust management flight test sorties and test sites.
[0070] Pre-flight simulation analysis was conducted for each test point and test state. Flight test techniques were developed to address potential instability in aircraft platform speed during flight testing. A digital engine model was used for simulation calculations. If the test engine could not maintain a stable Mach number at high speeds, the Mach number was gradually reduced in increments of 0.001 at the same altitude until the highest Mach number at which the aircraft platform could maintain stable flight was reached. If the test engine could not maintain a stable Mach number at low speeds, a lower Mach number test at the same altitude was conducted.
[0071] For each selected thrust management flight test point, from the engine's maximum stable operating state to its idle state, 10-15 typical engine speed points or steady-state speed points for the engine thrust management adjustment plan are determined. Under the same flight conditions, maintaining the same altitude and speed, the engine speed is varied, and the engine steady-state performance is recorded at different speeds (10-15 speeds). In other words, the engine steady-state performance at different speeds is recorded for each thrust management flight test point.
[0072] In this embodiment, step S33, controlling the test engine to perform flight tests at the test operating speed point, includes:
[0073] The test engine is controlled to operate stably at the test operating speed point for 5 minutes. If the allowable tolerance of the flight altitude relative to the thrust management flight test point is ±100m, the allowable tolerance of the flight Mach number relative to the thrust management flight test point is ±0.01, and the change in the total temperature of the engine inlet is less than or equal to 2℃, then the engine steady-state test parameters are collected.
[0074] Otherwise, repeat the steps of controlling the non-test engine to make the flight platform fly stably in a straight line at the thrust management flight test point.
[0075] Control steady-state flight for 5 minutes. If not, continue to maintain stable operation by adjusting the non-test engine. If stable operation still cannot be maintained after multiple attempts, conduct flight tests at the next thrust management flight test point or the next test operating speed point.
[0076] In this embodiment, the steps for collecting engine steady-state test parameters based on engine flight test results include:
[0077] After 5 minutes of steady-state flight of the engine, the steady-state test parameters of the engine are collected for 30 seconds. If the allowable tolerance of flight altitude relative to thrust management flight test point is ±50m, the allowable tolerance of flight Mach number relative to thrust management flight test point is ±0.005, and the change in total engine inlet temperature is less than or equal to 2℃, then the engine working status is judged.
[0078] Otherwise, if the allowable tolerance for flight altitude relative to thrust management flight test points is ±100m, the allowable tolerance for flight Mach number relative to thrust management flight test points is ±0.01, and the total temperature variation of the engine inlet is less than or equal to 2℃, the data should be collected again.
[0079] If the tolerance for the flight altitude relative to the thrust management flight test point is ±100m, the tolerance for the flight Mach number relative to the thrust management flight test point is ±0.01, and the variation in the total engine inlet temperature is less than or equal to 2℃, then the steps of controlling the non-test engine to make the flight platform fly stably in a straight line at the thrust management flight test point are repeated.
[0080] After 5 minutes of steady-state flight of the engine, steady-state test parameters are collected. If the data collection conditions are met, the data collection is valid. Further determination is made as to whether the engine operating state has dropped to idle speed. If it is already at idle speed, the test for this thrust management flight test point is completed. If it is not at idle speed, the test for the next operating speed point is conducted. If the data collection conditions are not met, the data is collected again. If the steady-state flight conditions are still not met, the non-test engine is adjusted, and after 5 minutes of steady-state flight, data collection is performed again.
[0081] In this embodiment, the step of obtaining the engine's test operating speed point includes:
[0082] Obtain the test operating speed points of the engine from its maximum stable operating state to its idle state in the air;
[0083] If the allowable tolerance for flight altitude relative to thrust management flight test points is ±50m, the allowable tolerance for flight Mach number relative to thrust management flight test points is ±0.005, and the engine inlet total temperature variation is less than or equal to 2℃, then the steps for judging the engine operating status include:
[0084] If the engine is at idle speed in the air, execute the thrust management flight test point acquisition; otherwise, execute the test operating speed point acquisition of the engine.
[0085] If the data acquisition is valid and the test is in idle state, the test at this thrust management flight test point is completed; if the test is not in idle state, the flight test at this thrust management flight test point continues, and the flight test at the next operating speed state point is carried out.
[0086] In this embodiment, when the engine is operating at idle speed, the step of acquiring the thrust management flight test point is performed; otherwise, the step of acquiring the engine's test operating speed point includes:
[0087] If the engine is at idle speed in the air, execute the acquisition of thrust management flight test points; otherwise, execute the acquisition of the engine's last three test operating speed points at the previous thrust management flight test point.
[0088] A flight test technique was developed that splits a thrust management flight test point into two sorties. If a thrust management flight test point is split into two sorties, the next sortie must repeat the last three test operating speed points to facilitate the connection of test data.
[0089] Because a thrust management flight test requires recording 10-15 test operating speed points, and each test operating speed point requires 5 minutes of stabilization followed by half a minute of data acquisition, each thrust management flight test takes approximately one to one and a half hours. Therefore, it's possible that, for example, if three complete thrust management flight test points are recorded, the fourth test might not be able to record all 10-15 test operating speed points; for instance, only 5 might be recorded initially. In this case, the next flight will repeat the recording of the last 3 test operating speed points.
[0090] Reference Figure 2In this embodiment, the test operating speed points include typical speed points and steady-state speed points.
[0091] Reference Figure 2 According to the flight test method for thrust management of a civil high-bypass turbofan engine provided in this embodiment, the working principle of the flight test method for thrust management of a civil high-bypass turbofan engine includes:
[0092] (1) Control the aircraft platform to fly to the required flight altitude and speed for the thrust management flight test point.
[0093] (2) The ambient temperature shall not exceed the thrust sustaining inflection point temperature (generally ISA+10K). The inflection point temperature refers to the highest ambient temperature at which a given type of aero-engine can maintain its takeoff thrust / power at full thrust / power (branded thrust / power) under standard atmospheric pressure at sea level. This temperature is also called the inflection point temperature or flat rated temperature of that engine type.
[0094] (3) Adjust the non-test engines to ensure that the aircraft platform flies stably in a straight line at the thrust management flight test point.
[0095] (4) Test the engine from its maximum stable operating state to its idle state in the air, and perform tests for each stable operating state of the engine according to steps (5) to (7).
[0096] (5) The test engine operates stably at the test operating speed point for 5 minutes. The requirements for stable operation of the test engine are: the flight altitude is stable at ±100m of the selected altitude, the flight Mach number is stable at the selected Mach number ±0.01, the total temperature change of the engine inlet does not exceed 2℃, and the throttle position of the test engine remains unchanged.
[0097] (6) After the test engine has been running stably for 5 minutes, the engine steady-state test parameters are collected for 30 seconds. During the data collection period, the engine is required to be running stably: the flight altitude is stable at the selected altitude ±50m, the flight Mach number is stable at the selected Mach number ±0.005, the total temperature change of the engine inlet does not exceed 2℃, and the position of the test engine throttle lever remains unchanged.
[0098] (7) If the test engine does not meet the stable operating conditions required in step (6) during the data acquisition period, the steady-state data acquisition shall be carried out again.
[0099] (8) During the data acquisition, if the test engine meets the stable working conditions required in step (6), it indicates that the acquired data is valid and the test of the current engine stable working speed point is completed.
[0100] (9) By judging whether the engine working state has dropped to the idle speed state, it is determined whether the thrust management flight test of all engine working state speed points at the current test point has been completed.
[0101] (10) If the engine operating state has not yet dropped to the idle speed state, pull down the engine throttle lever to test the next engine stable operating speed point.
[0102] (11) If the engine operating state has dropped to the idle speed state, it indicates that the thrust management flight test at this thrust management flight test point has been completed.
[0103] Finally, the effectiveness of the thrust management flight test was determined.
[0104] a. The selected thrust management flight test site and the developed thrust management flight test plan are correct, and the test pilot's operation meets the flight test requirements, that is, it satisfies the above steps (5) and (6).
[0105] b. Under the condition that the engine is in stable operation, the data acquisition equipment works normally and the test data meets the requirements, such as the data being continuous and not misaligned.
[0106] c. The engine steady-state control conforms to the engine thrust management adjustment plan.
[0107] d. If conditions a to c above are met, the thrust management flight test is valid.
[0108] The flight test method for thrust management of a civilian high-bypass turbofan engine provided in this embodiment has at least the following advantages:
[0109] Flight tests were conducted at different thrust management flight test points, and at different operating speed points for the same thrust management flight test point. Steady-state test parameters of the engine were recorded to correct and improve engine thrust, speed, or power. Thrust management flight tests of civil high-bypass turbofan engines were carried out on aircraft platforms to assess the engine's steady-state flight performance, benchmark against the aircraft's thrust requirements, and verify the degree to which the engine meets the thrust requirements in the flight state. The applicability of thrust management during flight was verified, enabling condition-based optimization. The overall engine performance steady-state model was calibrated and corrected, the overall performance steady-state model correction technology was verified, and the steady-state model was optimized.
[0110] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention.
Claims
1. A flight test method for thrust management of a civilian high-bypass turbofan engine, characterized in that, include: Obtain thrust management flight test sites; Obtain the engine's test operating speed point; Based on the priority of the thrust management flight test points and the engine's operating speed points, the test engine is controlled to conduct flight tests. Based on the engine flight test results, the engine steady-state test parameters were collected.
2. The flight test method for thrust management of a civil high-bypass turbofan engine according to claim 1, characterized in that, The steps for obtaining thrust management flight test points include: The flight envelope engine thrust assessment point and the flight envelope engine fuel consumption rate assessment point are obtained as thrust management flight test points.
3. The flight test method for thrust management of a civil high-bypass turbofan engine according to claim 1, characterized in that, The steps for obtaining thrust management flight test points also include: Typical points on the boundary of the engine flight envelope required by the aircraft, as well as typical points on the flight profile required by the aircraft, are obtained as thrust management flight test points.
4. The flight test method for thrust management of a civil high-bypass turbofan engine according to claim 1, characterized in that, The steps for obtaining thrust management flight test points also include: Typical points for engine model correction within the flight envelope were obtained, with flight altitude intervals of 1500m and Mach number intervals of 0.05 to 0.1, serving as thrust management flight test points.
5. The flight test method for thrust management of a civil high-bypass turbofan engine according to any one of claims 1-4, characterized in that, The steps for controlling the test engine to conduct flight tests based on the priority of thrust management flight test points and the engine's operating speed include: Control the aircraft platform to fly to the required flight altitude and speed for the thrust management flight test point, where the ambient temperature is lower than the thrust holding inflection point temperature; Control the non-test engines to ensure the flight platform maintains stable straight-line level flight at the thrust management flight test point; The test engine was controlled to operate at the test speed point for flight testing.
6. The flight test method for thrust management of a civil high-bypass turbofan engine according to claim 5, characterized in that, The steps for conducting flight tests on the controlled test engine at its test operating speed include: The test engine is controlled to operate stably at the test operating speed point for 5 minutes. If the allowable tolerance of the flight altitude relative to the thrust management flight test point is ±100m, the allowable tolerance of the flight Mach number relative to the thrust management flight test point is ±0.01, and the change in the total temperature of the engine inlet is less than or equal to 2℃, then the engine steady-state test parameters are collected. Otherwise, repeat the steps described above for controlling the non-test engine to enable the flight platform to fly stably in a straight line at the thrust management flight test point.
7. The flight test method for thrust management of a civil high-bypass turbofan engine according to claim 6, characterized in that, The steps for collecting engine steady-state test parameters based on engine flight test results include: After 5 minutes of steady-state flight of the engine, the steady-state test parameters of the engine are collected for 30 seconds. If the allowable tolerance of flight altitude relative to thrust management flight test point is ±50m, the allowable tolerance of flight Mach number relative to thrust management flight test point is ±0.005, and the change in total engine inlet temperature is less than or equal to 2℃, then the engine working status is judged. Otherwise, if the allowable tolerance for flight altitude relative to thrust management flight test points is ±100m, the allowable tolerance for flight Mach number relative to thrust management flight test points is ±0.01, and the total temperature variation of the engine inlet is less than or equal to 2℃, the data should be collected again. If the tolerance for the flight altitude relative to the thrust management flight test point is ±100m, the tolerance for the flight Mach number relative to the thrust management flight test point is ±0.01, and the total temperature change of the engine inlet is less than or equal to 2℃, then the steps of controlling the non-test engine to make the flight platform fly stably in a straight line at the thrust management flight test point are repeated.
8. The flight test method for thrust management of a civil high-bypass turbofan engine according to claim 7, characterized in that, The steps for obtaining the engine's test operating speed point include: Obtain the test operating speed points of the engine from its maximum stable operating state to its idle state in the air; If the allowable tolerance for the flight altitude relative to the thrust management flight test point is ±50m, the allowable tolerance for the flight Mach number relative to the thrust management flight test point is ±0.005, and the engine inlet total temperature variation is less than or equal to 2℃, then the steps for judging the engine operating status include: If the engine is in idle state, execute the process of acquiring the thrust management flight test point; otherwise, execute the process of acquiring the engine's test operating speed point.
9. The flight test method for thrust management of a civil high-bypass turbofan engine according to claim 8, characterized in that, The process of acquiring the thrust management flight test point is performed when the engine is in idle state. Otherwise, the steps for obtaining the engine's test operating speed point include: With the engine operating at idle speed in the air, the aforementioned thrust management flight test point is executed; Otherwise, execute the process to obtain the engine's operating speed points during the last three test runs at the previous thrust management flight test point.
10. The flight test method for thrust management of a civil high-bypass turbofan engine according to claim 8, characterized in that, The test operating speed points include typical speed points and steady-state speed points.