Method for testing overall attitude of aero-engine in shadow area under outdoor condition

Abstract

The invention belongs to the technical field of aero-engine attitude test design, and particularly relates to an aero-engine open-air condition shadow area complete machine attitude test method, which comprises the following steps: setting aero-engine attitude test blank area roll and pitch angle test points (X1, Y1) and shadow area roll and pitch angle test points (X2, Y2); the attitude angle and state of the aero-engine are adjusted, the installation flight condition of the aero-engine is highly simulated, it is guaranteed that the complete machine attitude test of the aero-engine in an open-air shadow area is safely and efficiently completed, the working capacity of the aero-engine under the extreme condition is effectively tested, and the development work of the aero-engine is promoted.

Description

Technical Field

[0001] This application belongs to the field of aero-engine attitude test design technology, specifically relating to a method for whole-engine attitude test in the shaded area under open-air conditions. Background Technology

[0002] In the development of aero-engines, experimental research accounts for a large proportion. From design to final delivery, more than 70% of the total development time is spent on experimental research. Aero-engine testing includes component testing and whole-engine testing. Whole-engine testing includes ground testing and high-altitude test bench testing, and ground testing includes indoor test bench testing and open-air test bench testing.

[0003] When the lubrication system of an aircraft engine operates under zero or negative "g" conditions, problems such as oil cut-off, lubrication foam, seal leakage, and oil overflow from the bearing cavity may occur. Whether the aircraft engine can withstand these conditions needs to be verified through testing.

[0004] Attitude testing is a type of airborne test and a special test item in the type certification testing of aero-engines. The purpose of this test is to verify the aero-engine's performance during flight, including pitching up, pitching down, left roll, and right roll, particularly verifying the adaptability of the lubrication system, rotor bearings, and support structure under extreme flight attitudes. To ensure flight safety, aero-engine standards stipulate that attitude testing must be conducted, making it one of the important pre-flight tests.

[0005] The aero-engine standards of the United States, the United Kingdom, and Russia all contain detailed regulations on attitude testing, requiring such tests to be conducted. For example, Pratt & Whitney Canada has an advanced indoor attitude test stand for turboshaft aero-engines, with an attitude angle range of ±50° for left and right roll, 120° for pitch, and 90° for nose-down. Allison Corporation of the United States, which mainly produces turboprop and turboshaft aero-engines, has a complete attitude test stand for turboshaft aero-engines, with performance indicators of ±55° for left and right roll, 105° for pitch, and 90° for nose-down. The Sarrec Test Center in France also has a complete attitude test stand for turboshaft aero-engines.

[0006] The requirements for attitude angle points in aero-engine attitude testing are as follows: Figure 1 As shown in the figure, the horizontal and vertical axes represent the roll angle and pitch angle, respectively. The blank area is bounded by the six blank area attitude angle test boundary points (-20°, 0°), (-10°, -90°), (10°, -90°), (20°, 0°), (10°, 90°), and (-10°, 90°). The shaded area is bounded by the two shaded area attitude angle test boundary points (-45°, 0°) and (45°, 0°) and the six blank area attitude angle test boundary points.

[0007] The standard for aircraft engine attitude testing stipulates that aircraft engines are not required to start and stop in the shaded area. However, the aircraft engine should be able to start in the blank area and then rotate to the shaded area to operate satisfactorily in the intermediate thrust state for 30 seconds, and then rotate back to the blank area. If the aircraft engine can operate satisfactorily and there are no signs of mechanical damage, the attitude test in the shaded area is considered to be successfully completed.

[0008] In the past, due to technical and resource constraints, my country did not pay enough attention to attitude testing. Instead, the corresponding assessment and verification were often carried out in later flight tests or replaced by component tests. This resulted in high flight test risks, which posed a great risk to the development of aero engines and seriously restricted the development of aero engines.

[0009] Currently, my country's regulations for aero-engine attitude testing stipulate that test methods and procedures should be specified in the pre-test documentation. Aero-engines should undergo attitude testing in accordance with the methods and procedures specified in the relevant detailed specifications. Therefore, it is necessary to establish a complete set of aero-engine attitude testing methods to guide aero-engine attitude-related tests. Summary of the Invention

[0010] The purpose of this application is to provide a method for whole-engine attitude testing in the shaded area under open-air conditions, so as to guide the whole-engine attitude testing in the shaded area under open-air conditions, reduce the risk of aero-engine development, and promote the development of aero-engines.

[0011] The technical solution of this application is:

[0012] A method for testing the attitude of an aircraft engine in an open-air shaded area includes:

[0013] Attitude test stand angle calibration steps: Calibrate the pitch and roll angles of the attitude test stand;

[0014] The attitude test stand includes a pitch platform and a roll platform mounted on the pitch platform. The roll platform is used to mount the aircraft engine, and the pitch platform and roll platform are used to adjust the pitch and roll angles of the aircraft.

[0015] Aircraft engine installation steps: Install the aircraft engine onto the open-air attitude test stand;

[0016] Aircraft engine attitude test procedures: Attitude tests for aircraft engines include:

[0017] S21. Set the roll and pitch angle test points (X1, Y1) in the blank area of ​​the aircraft engine attitude test and the roll and pitch angle test points (X2, Y2) in the shaded area.

[0018] S22. Start the aircraft engine to idle position, warm up the aircraft engine, and push the aircraft engine to the intermediate thrust position.

[0019] S23. Control the roll platform angle to rotate to X1, brake and lock;

[0020] Control the pitch platform angle to rotate to Y1, then brake and lock;

[0021] S24. Control the roll platform angle to rotate to X2, then brake and lock;

[0022] Control the pitch platform angle to rotate to Y2, then brake and lock;

[0023] The aircraft engine was operated at intermediate thrust for 30 seconds. Within 30 seconds, the lubrication system was allowed to interrupt the oil supply, and the time of interruption of the oil supply within 30 seconds was recorded.

[0024] S25. Control the pitch platform angle to rotate to a horizontal position, then brake and lock.

[0025] Control the roll platform to rotate to a horizontal position, then brake and lock.

[0026] S26. Pull the aircraft engine from the intermediate thrust state to a low thrust state to perform a cold engine shutdown.

[0027] Change the roll and pitch angle test points (X1, Y1) in the blank area of ​​the aero-engine attitude test and the roll and pitch angle test points (X2, Y2) in the shaded area, repeating S22 to S26. Among them, the roll and pitch angle test points (X1, Y1) in the blank area of ​​the aero-engine attitude test should include at least six blank area attitude angle test boundary points: (-20°, 0°), (-10°, -90°), (10°, -90°), (20°, 0°), (10°, 90°), and (-10°, 90°). The roll and pitch angle test points (X2, Y2) in the shaded area should include at least two shaded area attitude angle test boundary points: (-45°, 0°) and (45°, 0°).

[0028] According to at least one embodiment of this application, in the above-described method for testing the attitude of an aircraft engine in an open-air shaded area, the specific process of calibrating the attitude test stand angle is as follows:

[0029] S11. Use an angle sensor to measure whether the angles of the pitch platform and roll platform are 0°. If not, apply an initial torque to level the pitch platform and roll platform.

[0030] S12. Given the pitch angle adjustment speed, control the pitch platform to operate between α1 and α2, and record the operating speed and pitch angle control accuracy of the attitude test stand. Here, α1 is the pitch limit angle of the aero-engine attitude envelope, and α2 is the pitch limit angle of the aero-engine attitude envelope.

[0031] S12. Control the pitch platform to move from 0° to α1, or from 0° to α2. After stabilization, return to 0° and record the time of the attitude test stand moving forward or returning.

[0032] S13. Given the roll angle adjustment speed, control the roll platform to operate between β1 and β2, and record the operating speed and roll angle control accuracy of the attitude test stand. Here, β1 is the pitch limit angle of the aero-engine attitude envelope, and β2 is the pitch limit angle of the aero-engine attitude envelope.

[0033] S14. Control the roll platform to move forward from 0° to β1, or from 0° to β2. After stabilization, return to 0° and record the time of the attitude test stand moving forward or returning.

[0034] According to at least one embodiment of this application, in the above-mentioned aircraft attitude test method for the aircraft engine in the shaded area under open-air conditions, the pitch limit angle α1 of the aircraft engine attitude envelope is 105°, and the pitch limit angle α2 of the aircraft engine attitude envelope is -90°.

[0035] The pitching limit angle β1 of the aero-engine attitude envelope is taken as 45°, and the pitching limit angle β2 of the aero-engine attitude envelope is taken as -45°.

[0036] According to at least one embodiment of this application, in the above-described method for testing the attitude of an aircraft engine in an open-air shaded area, the aircraft engine installation steps specifically include:

[0037] According to the relevant installation and disassembly requirements of the model, the aero engine, flight attachment casing, process air intake and other components are fixedly installed on the pre-installation frame. Then the pre-installation frame is installed on the roll platform. The roll platform is then transported as a whole to the attitude test stand area and lifted and fixedly installed on the pitch platform using a lifting device.

[0038] According to at least one embodiment of this application, in the above-mentioned method for testing the attitude of an aircraft engine in an open-air shaded area, in the aircraft engine installation step, after the aircraft engine is installed on the open-air attitude test stand, the aircraft engine is accepted. After the acceptance is passed, the aircraft engine process equipment, accessory equipment, electrical system, and test system are installed, and the parameters of the aircraft engine electrical system, fuel system, and health management system are calibrated. The aircraft engine is also filled with oil, bleeds gas, unsealed, and performs a dummy start-up.

[0039] According to at least one embodiment of this application, in the above-described method for testing the attitude of an aircraft engine in an open-air shaded area, the aircraft engine installation step involves reviewing the aircraft engine attitude test technical documents, test equipment, test instruments, and aspects related to organization, support, and safety.

[0040] According to at least one embodiment of this application, in the above-mentioned method for testing the attitude of an aircraft engine in the shaded area under open-air conditions, the aircraft engine attitude test step involves strengthening the monitoring of the aircraft engine vibration, pulsation, and key component parameters of the high-pressure air system, low-pressure air system, and lubricating oil system. If any abnormality is found, it is promptly eliminated or the aircraft engine is stopped.

[0041] According to at least one embodiment of this application, in the above-mentioned method for testing the attitude of an aircraft engine in the shaded area under open-air conditions, in the aircraft engine attitude test steps, after the aircraft engine is shut down, the aircraft engine is checked for external leaks, the validity of the test data is confirmed, and the lubricating oil consumption is calculated to determine whether the lubricating oil consumption exceeds the limit; lubricating oil is collected from the lubricating oil tank, accessory housing, and rear bearing cavity, and lubricating oil spectrum analysis is performed to determine whether the spectra of the main elements Fe, Cu, Ag, Al, and Ti in the lubricating oil exceed the standard; the aircraft engine intake, fan stator, compressor stator, combustion chamber, high-pressure turbine stator, low-pressure turbine stator, and afterburner are checked to see if they are normal.

[0042] This application has at least the following beneficial technical effects:

[0043] This invention provides a method for testing the attitude of an aero-engine in the shaded area under open-air conditions. By setting the roll and pitch angle test points (X1, Y1) in the blank area of ​​the aero-engine attitude test and the roll and pitch angle test points (X2, Y2) in the shaded area, and by adjusting the attitude angles and states of the aero-engine, the method highly simulates the on-board flight conditions of the aero-engine, ensuring the safe and efficient completion of the aero-engine attitude test in the shaded area under open-air conditions. This method effectively tests the working capability of the aero-engine under extreme conditions and promotes the development of aero-engines. Attached Figure Description

[0044] Figure 1 This is a schematic diagram of the attitude angle point requirements for aero-engine attitude testing provided in an embodiment of this application;

[0045] Figure 2 This is a schematic diagram of the procedure for the attitude test of an aero-engine provided in the embodiments of this application.

[0046] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0047] 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.

[0048] 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 word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0049] A method for testing the overall attitude of an aircraft engine in a shaded area under open-air conditions is described below:

[0050] Attitude test stand angle calibration steps: Calibrate the pitch and roll angles of the attitude test stand.

[0051] The attitude test stand includes a pitch platform and a roll platform mounted on the pitch platform. The roll platform is used to mount the aircraft engine, and the pitch and roll platforms are used to adjust the pitch and roll angles of the aircraft.

[0052] To accurately measure and control the pitch and roll angles of the aero-engine during attitude testing, the pitch and roll angles of the attitude test stand need to be calibrated before the formal test operation. The specific process is as follows:

[0053] S11. Use an angle sensor to measure whether the angles of the pitch platform and roll platform are 0°. If not, apply an initial torque to level the pitch platform and roll platform, that is, adjust the angles of the pitch platform and roll platform to 0°.

[0054] S12. Given the pitch angle adjustment speed, control the pitch platform to operate between α1 and α2, and record the operating speed of the attitude test stand and the pitch angle control accuracy. The pitch angle control accuracy is required to reach 0.5%. Here, α1 is the pitch limit angle of the aero-engine attitude envelope, usually taken as 105°, and α2 is the pitch limit angle of the aero-engine attitude envelope, usually taken as -90°.

[0055] S12. Control the pitch platform to move from 0° to α1, or from 0° to α2. After stabilization, return to 0° and record the time of the attitude test stand moving forward or returning.

[0056] S13. Given the roll angle adjustment speed, control the roll platform to operate between β1 and β2, and record the operating speed of the attitude test stand and the roll angle control accuracy. The roll angle control accuracy is required to reach 0.5%. Among them, β1 is the pitch limit angle of the aero-engine attitude envelope, which is usually taken as 45°, and β2 is the pitch limit angle of the aero-engine attitude envelope, which is usually taken as -45°.

[0057] S14. Control the roll platform to move forward from 0° to β1, or from 0° to β2. After stabilization, return to 0° and record the time of the attitude test stand moving forward or returning.

[0058] Aircraft engine installation steps: Install the aircraft engine onto the open-air attitude test stand.

[0059] After the aero-engine is transported to the assembly plant, according to the relevant installation and disassembly requirements of the model, the aero-engine, flight attachment casing, process air intake, etc. are fixedly installed on the pre-assembly frame, and some measurement and control and mechanical interface connections are completed. Then the pre-assembly frame is installed on the roll platform, and the roll platform is transported as a whole to the attitude test stand area. The roll platform is lifted and fixedly installed on the pitch platform by the lifting device, and finally the remaining pipeline connection work is carried out.

[0060] After the aero-engine is installed on the open-air attitude test stand, the chief test engineer, test worker and test inspector will inspect the aero-engine. After the inspection is passed, the test execution unit will install the aero-engine process equipment, accessory equipment, electrical system and test system in accordance with relevant procedures, and complete the parameter calibration of the aero-engine electrical system, fuel system and health management system in accordance with the calibration procedure documents, as well as complete the aero-engine filling, venting, unsealing and dummy start-up work.

[0061] In addition, the technical documents for aero-engine attitude testing, testing equipment, testing instruments, organization, support, and safety can be reviewed in accordance with the pre-test review requirements in the quality procedure documents.

[0062] Aircraft engine attitude test procedures: The specific procedures for conducting attitude tests on aircraft engines are as follows:

[0063] S21. Set the roll and pitch angle test points (X1, Y1) in the blank area of ​​the aircraft engine attitude test and the roll and pitch angle test points (X2, Y2) in the shaded area.

[0064] The angle sensor measures whether the pitch and roll platforms are 0°. If not, the initial torque is applied to level the pitch and roll platforms.

[0065] S22. Start the aircraft engine to idle speed to warm it up, and then push the aircraft engine up to the intermediate thrust state.

[0066] S23. Control the roll platform angle to rotate to X1, brake and lock;

[0067] Control the pitch platform angle to rotate to Y1, then brake and lock.

[0068] S24. Control the roll platform angle to rotate to X2, then brake and lock;

[0069] Control the pitch platform angle to rotate to Y2, then brake and lock;

[0070] The aircraft engine is operated at intermediate thrust for 30 seconds. Within 30 seconds, the lubrication system is allowed to interrupt the oil supply. The time of interruption within 30 seconds is recorded. Whether the lubrication system interrupts the oil supply can be determined by the oil supply pressure.

[0071] S25. Control the pitch platform angle to rotate to a horizontal position, then brake and lock.

[0072] Control the roll platform to rotate to a horizontal position, then brake and lock.

[0073] S26. Pull the aircraft engine from the intermediate thrust state to the low thrust state for cold engine shutdown.

[0074] Change the roll and pitch angle test points (X1, Y1) in the blank area of ​​the aero-engine attitude test and the roll and pitch angle test points (X2, Y2) in the shaded area. Repeat S22 to S26 to complete the aero-engine attitude test point test. Among them, the roll and pitch angle test points (X1, Y1) in the blank area of ​​the aero-engine attitude test should include at least six blank area attitude angle test boundary points: (-20°, 0°), (-10°, -90°), (10°, -90°), (20°, 0°), (10°, 90°), and (-10°, 90°). The roll and pitch angle test points (X2, Y2) in the shaded area should include at least two shaded area attitude angle test boundary points: (-45°, 0°) and (45°, 0°).

[0075] During the attitude test of the aero-engine, strengthen the monitoring of the aero-engine vibration and pulsation, as well as the parameters of key components such as the high-pressure air system, low-pressure air system, and lubricating oil system. If any abnormalities are found, eliminate them in time, and stop the aero-engine if necessary.

[0076] In aero-engine attitude tests, the correspondence between the aero-engine's attitude angles and its state is as follows: Figure 2 As shown:

[0077] 1→2: The attitude test stand is adjusted from the horizontal position to the roll and pitch angle test point (X2,Y2) in the shaded area. At this time, the aero engine is in the intermediate thrust state.

[0078] 2→3: The attitude test stand is located in the shaded area at the roll and pitch angle test points (X2, Y2), and the aero engine operates in the intermediate thrust state for 30 seconds.

[0079] 3→4: The attitude test stand is adjusted from the roll and pitch angle test point (X2,Y2) in the shaded area to a horizontal position. At this time, the aero engine is in the intermediate thrust state.

[0080] a→b: With the attitude test stand in a horizontal position, the aero engine starts and reaches idle speed.

[0081] b→c: The warm-up process of the aero engine in the horizontal position of the attitude test stand.

[0082] c→d: In the horizontal position of the attitude test stand, the aero engine is pushed up to the intermediate thrust state after warming up.

[0083] d→e: The aero-engine operates under intermediate thrust conditions. During the process, the attitude test stand is adjusted from a horizontal position to the roll and pitch angle test point (X2,Y2) in the shaded area, and then returns to the horizontal position.

[0084] e→f: When the attitude test stand is in a horizontal position, the aero engine is pulled from the intermediate thrust state to the low state of cold engine;

[0085] f→g: The aircraft engine stops cold when in the horizontal position on the attitude test stand.

[0086] After the aircraft engine stops, check for external leaks, confirm the validity of test data, and calculate the lubricating oil consumption to determine if it exceeds the limit. Take lubricating oil samples from the oil tank, accessory housing, and rear bearing cavity for spectral analysis to determine if the spectra of major elements such as Fe, Cu, Ag, Al, and Ti exceed the standards. Check the flow path components of the aircraft engine, including the air intake, fan stator, compressor stator, combustion chamber, high-pressure turbine stator, low-pressure turbine stator, and afterburner, to ensure they are normal. If all of the above are normal, the aircraft engine is considered to be operating normally, and the aircraft attitude test in the shadow area is completed.

[0087] The above embodiments disclose a method for testing the attitude of an aero-engine in the shaded area under open-air conditions. By setting the roll and pitch angle test points (X1, Y1) in the blank area of ​​the aero-engine attitude test and the roll and pitch angle test points (X2, Y2) in the shaded area, and adjusting the attitude angles and states of the aero-engine, the method highly simulates the flight conditions of the aero-engine, ensuring the safe and efficient completion of the aero-engine attitude test in the shaded area under open-air conditions, effectively testing the working ability of the aero-engine under extreme conditions, and promoting the development of aero-engines.

[0088] 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 testing the attitude of an aircraft engine in an open-air, shaded area, characterized in that, include: Attitude test stand angle calibration steps: Calibrate the pitch and roll angles of the attitude test stand; The attitude test stand includes a pitch platform and a roll platform mounted on the pitch platform. The roll platform is used to mount the aircraft engine, and the pitch platform and roll platform are used to adjust the pitch and roll angles of the aircraft. Aircraft engine installation steps: Install the aircraft engine onto the open-air attitude test stand; Aircraft engine attitude test procedures: Attitude tests for aircraft engines include: S21. Set the roll and pitch angle test points (X1, Y1) in the blank area of ​​the aircraft engine attitude test and the roll and pitch angle test points (X2, Y2) in the shaded area. S22. Start the aircraft engine to idle position, warm up the aircraft engine, and push the aircraft engine to the intermediate thrust position. S23. Control the roll platform angle to rotate to X1, brake and lock; Control the pitch platform angle to rotate to Y1, then brake and lock; S24. Control the roll platform angle to rotate to X2, then brake and lock; Control the pitch platform angle to rotate to Y2, then brake and lock; The aircraft engine was operated at intermediate thrust for 30 seconds. Within 30 seconds, the lubrication system was allowed to interrupt the oil supply, and the time of interruption of the oil supply within 30 seconds was recorded. S25. Control the pitch platform angle to rotate to a horizontal position, then brake and lock. Control the roll platform to rotate to a horizontal position, then brake and lock. S26. Pull the aircraft engine from the intermediate thrust state to a low thrust state to perform a cold engine shutdown. Change the roll and pitch angle test points (X1, Y1) in the blank area of ​​the aero-engine attitude test and the roll and pitch angle test points (X2, Y2) in the shaded area, repeating S22 to S26. Among them, the roll and pitch angle test points (X1, Y1) in the blank area of ​​the aero-engine attitude test should include at least six blank area attitude angle test boundary points: (-20°, 0°), (-10°, -90°), (10°, -90°), (20°, 0°), (10°, 90°), and (-10°, 90°). The roll and pitch angle test points (X2, Y2) in the shaded area should include at least two shaded area attitude angle test boundary points: (-45°, 0°) and (45°, 0°).

2. The method for testing the attitude of an aircraft engine in an open-air shaded area according to claim 1, characterized in that, The specific steps for calibrating the attitude test bench angle are as follows: S11. Use an angle sensor to measure whether the angles of the pitch platform and roll platform are 0°. If not, apply an initial torque to level the pitch platform and roll platform. S12. Given the pitch angle adjustment speed, control the pitch platform to operate between α1 and α2, and record the operating speed and pitch angle control accuracy of the attitude test stand. Here, α1 is the pitch limit angle of the aero-engine attitude envelope, and α2 is the pitch limit angle of the aero-engine attitude envelope. S12. Control the pitch platform to move from 0° to α1, or from 0° to α2. After stabilization, return to 0° and record the time of the attitude test stand moving forward or returning. S13. Given the roll angle adjustment speed, control the roll platform to operate between β1 and β2, and record the operating speed and roll angle control accuracy of the attitude test stand. Here, β1 is the pitch limit angle of the aero-engine attitude envelope, and β2 is the pitch limit angle of the aero-engine attitude envelope. S14. Control the roll platform to move forward from 0° to β1, or from 0° to β2. After stabilization, return to 0° and record the time of the attitude test stand moving forward or returning.

3. The method for testing the attitude of an aircraft engine in an open-air shaded area according to claim 2, characterized in that, The pitching limit angle α1 of the aero-engine attitude envelope is taken as 105°, and the pitching limit angle α2 of the aero-engine attitude envelope is taken as -90°. The pitching limit angle β1 of the aero-engine attitude envelope is taken as 45°, and the pitching limit angle β2 of the aero-engine attitude envelope is taken as -45°.

4. The method for testing the attitude of an aircraft engine in an open-air shaded area according to claim 3, characterized in that, The specific steps for installing an aircraft engine are as follows: According to the relevant installation and disassembly requirements of the model, the aero engine, flight attachment casing, process air intake and other components are fixedly installed on the pre-installation frame. Then the pre-installation frame is installed on the roll platform. The roll platform is then transported as a whole to the attitude test stand area and lifted and fixedly installed on the pitch platform using a lifting device.

5. The method for testing the attitude of an aircraft engine in an open-air shaded area according to claim 4, characterized in that, In the aero-engine installation process, after the aero-engine is installed on the open-air attitude test stand, the aero-engine is accepted. After the acceptance is passed, the aero-engine process equipment, accessory equipment, electrical system and test system are installed, and the parameters of the aero-engine electrical system, fuel system and health management system are calibrated. The aero-engine is also filled with oil, bleeded, unsealed and dummy started.

6. The method for testing the attitude of an aircraft engine in an open-air shaded area according to claim 5, characterized in that, During the aircraft engine installation process, the technical documents, testing equipment, testing instruments, organization, support, and safety aspects of the aircraft engine attitude test are reviewed.

7. The method for testing the attitude of an aircraft engine in an open-air shaded area according to claim 6, characterized in that, During the attitude test of aero-engines, it is necessary to strengthen the monitoring of aero-engine vibration and pulsation, as well as the parameters of key components of the high-pressure air system, low-pressure air system, and lubricating oil system. If any abnormalities are found, they should be eliminated in time or the aero-engine should be stopped.

8. The method for testing the attitude of an aircraft engine in an open-air shaded area according to claim 7, characterized in that, In the aero-engine attitude test procedure, after the aero-engine is shut down, check for external leaks, confirm the validity of the test data, and calculate the lubricating oil consumption to determine if it exceeds the limit. Lubricating oil is collected from the oil tank, accessory housing, and rear bearing cavity for spectral analysis to determine if the spectra of major elements such as Fe, Cu, Ag, Al, and Ti exceed the standards. The aero-engine's air intake, fan stator, compressor stator, combustion chamber, high-pressure turbine stator, low-pressure turbine stator, and afterburner are checked for normal operation.

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