Aero-engine exhaust nozzle infrared radiation characteristic measurement test method and test device

Abstract

The invention discloses an aero-engine exhaust nozzle infrared radiation characteristic measurement test method. The method comprises the following steps: S1, test arrangement; s2, test debugging: starting the accompanying test piece, collecting pneumatic parameters of the test piece through a pneumatic measurement assembly, performing joint debugging on working states of the accompanying test piece and the test piece, and when the pneumatic parameters of the test piece reach a set value, marking the working state of the accompanying test piece at the moment as a test state, the set value being the pneumatic parameters of the test piece under a specified working condition; and S3, data acquisition. According to the scheme, the infrared radiation data of the real exhaust nozzle under the specified working condition in the real environment can be obtained, compared with the prior art, the suppression capability of the exhaust nozzle on infrared radiation can be accurately evaluated, the method is suitable for testing infrared suppressors in the field of helicopters, the development cycle of aero-engines is shortened, practicability is high, and the method is suitable for popularization and application. The method is suitable for wide popularization and application. In addition, the invention also discloses an aero-engine exhaust nozzle infrared radiation characteristic measurement test device.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft infrared radiation measurement, and in particular, to a method for measuring the infrared radiation characteristics of an aeroengine tail nozzle. In addition, the present invention also relates to an experimental device for measuring the infrared radiation characteristics of an aeroengine tail nozzle by using the above method for measuring the infrared radiation characteristics of an aeroengine tail nozzle. Background Art

[0002] Stealth technology can greatly improve the survivability of military aircraft (such as armed helicopters). Among them, infrared stealth is an important aspect in the field of stealth technology research and is crucial in countering the threat of infrared-guided missiles. An aeroengine is the largest infrared radiation source of an aircraft and thus becomes the main tracking target of infrared missiles. In order to improve the survivability of the aircraft, currently, an infrared suppressor (mainly a tail nozzle) is usually installed at the exhaust port of the aeroengine. By means of the infrared suppressor, the temperature of the hot components of the aeroengine and the temperature of the exhaust heat flow are significantly reduced, thereby reducing the infrared radiation signal and the probability of being detected and tracked by an infrared missile.

[0003] The design of the suppression ability of an infrared suppressor (a tail nozzle without an infrared suppression feature design can be regarded as a reference infrared suppressor) for infrared radiation is an important research field of aircraft infrared stealth. In order to evaluate the suppression ability of the infrared suppressor, an infrared radiation characteristic test needs to be carried out to obtain the infrared radiation data of the infrared suppressor, and then the infrared radiation data is compared with the infrared radiation data of the reference infrared suppressor.

[0004] However, at present, the research methods for evaluating the suppression ability of infrared suppressors mainly rely on simulation calculations. There are differences between the simulation data and the actual test data, and the accuracy of the suppression ability evaluation based on the simulation data is relatively low. The research objects of other physical tests are usually fixed-wing military aircraft equipped with turbo-fan / turbo-jet engines that can generate tail flames at the tail nozzle. The exhaust gas processed by the infrared suppressors in the helicopter field usually has relatively low operating conditions (compared with turbo-jet / turbo-fan engines), which is usually provided by a mature gas generator, and the exhaust gas after processing will not form an obvious tail flame at the outlet of the suppressor, that is, there is no directivity of the radiation intensity distribution of the tail flame generated. Therefore, it is not applicable to the test of infrared suppressors in the helicopter field. In addition, if the infrared suppressor is tested after the aeroengine is developed, if the test result is not ideal and it is necessary to optimize the design of the infrared suppressor or the aeroengine, it will greatly delay the development cycle, slow down the R & D progress, and waste manpower and material resources. Summary of the Invention

[0005] The present invention provides a method and an experimental device for measuring the infrared radiation characteristics of an aeroengine tail nozzle, so as to solve the technical problems that the existing experimental methods cannot accurately evaluate the suppression ability of an infrared suppressor, or are not applicable to the test of the infrared suppressor in the helicopter field, or may delay the development cycle of the aeroengine.

[0006] According to one aspect of the present invention, there is provided a method for measuring the infrared radiation characteristics of an aeroengine tail nozzle, including the following steps: S1, experimental arrangement: First, install the companion test piece, the test piece and the pneumatic measurement component, then set up a light-shielding background wall to form a test area to isolate the test piece from the environment, and finally set a test arc in the test area with the test piece as the geometric center. Select a plurality of measuring points arranged at equal intervals on the test arc, and set an infrared measurement component that can be transferred between multiple measuring points, where the companion test piece is a gas generator and the test piece is a tail nozzle; S2, experimental debugging: Start the companion test piece and collect the pneumatic parameters of the test piece through the pneumatic measurement component, and jointly debug the working states of the companion test piece and the test piece. When the pneumatic parameters of the test piece reach the set value, mark the working state of the companion test piece at this moment as the test state, where the set value is the pneumatic parameter of the test piece under the specified working condition; S3, data acquisition: First, make the companion test piece and the test piece in a non-working state, and complete the infrared radiation data acquisition of multiple measuring points in sequence through the infrared measurement component, and repeat the acquisition at least once. Then start the companion test piece and adjust it to the test state, collect the pneumatic parameters of the test piece through the pneumatic measurement component, and finally complete the infrared radiation data acquisition of multiple measuring points in sequence through the infrared measurement component, and repeat the acquisition at least once.

[0007] As a further improvement of the above technical solution:

[0008] Further, in step S1, the calculation formula for the radius of the test arc is:

[0009]

[0010] where R is the radius of the test arc, ω is the field of view angle of the infrared measurement component, and r is the field of view diameter corresponding to the maximum contour of the test piece among all test azimuth angles.

[0011] Further, after step S3, there is also a step: S4, data processing: Set the infrared radiation data collected by the infrared measurement component when the test piece is in the non-working state as L0, then set the infrared radiation data collected by the infrared measurement component when the companion test piece is in the test state as L1, and finally calculate L1 - L0 to obtain the infrared radiation data L of the test piece.

[0012] Further, between step S3 and step S4, there is also a step of checking whether the pneumatic parameters collected in step S2 and the pneumatic parameters collected in step S3 meet the repeatability requirements, and at the same time checking whether the infrared radiation data collected in step S3 meets the repeatability requirements. If both checks meet the requirements, then step S4 is carried out. If any one of the checks does not meet the requirements, then step S3 is repeated.

[0013] Further, in step S1, the number of measurement points is 8 to 12, and the included angle between the connecting lines of the first and last measurement points and the test piece is 90°.

[0014] Further, the pneumatic parameters include inlet total pressure, inlet static pressure, inlet air velocity, outlet temperature, outlet total pressure, and outlet air velocity.

[0015] Further, before step S2, there is also a step of completing the inspection work before the start of the companion test piece, checking the installation reliability of the test piece, and confirming that the pneumatic measurement component operates normally.

[0016] Further, before step S3, there is also a step of confirming that the test area is in a light-shielded environment, checking and confirming that the companion test piece and the test piece are in good condition, calibrating the infrared measurement component with a black box to confirm that it can completely cover the test piece, and confirming that the pneumatic measurement component and the infrared measurement component operate well.

[0017] According to another aspect of the present invention, there is also provided a test device for measuring the infrared radiation characteristics of an aero-engine tail nozzle, which adopts the above-mentioned test method for measuring the infrared radiation characteristics of an aero-engine tail nozzle. The test device includes a test stand, a gas generator installed on the test stand, an exhaust pipe connected to the gas generator, a tail nozzle connected to the exhaust pipe, a pneumatic measurement component arranged on the tail nozzle, a light-shielding background wall arranged on both sides of the tail nozzle at a preset angle for forming a test area, and an infrared measurement component for collecting infrared radiation data in the test area. The tail nozzle and the infrared measurement component are arranged at the same height.

[0018] As a further improvement of the above technical solution:

[0019] Further, the test device also includes a moving component for supporting the infrared measurement component and driving the infrared measurement component to move between multiple measurement points, and a remote controller wirelessly connected to the moving component.

[0020] The present invention has the following beneficial effects:

[0021] The test method for measuring the infrared radiation characteristics of the aero-engine tail nozzle of the present invention, when arranging the test, uses a gas generator as a companion test piece and the tail nozzle as the test piece for physical tests. And by setting up a light-shielding background wall to form a test area to isolate the test piece from the environment, that is, taking the test piece as an independent test object, the test data is reliable and can accurately evaluate the suppression ability of the test piece; taking the test piece as the geometric center, a test arc is set in the test area, and multiple measurement points are selected in the test arc and arranged evenly at intervals. An infrared measurement component that can be transferred between multiple measurement points is used to collect infrared radiation data, thus meeting the requirement of non-directionality in the horizontal plane for the infrared suppressor in the helicopter field and being applicable to the test of the infrared suppressor in the helicopter field; when conducting the test debugging, by collecting the aerodynamic parameters of the test piece, the working states of the companion test piece and the test piece are jointly debugged. When the aerodynamic parameters of the test piece reach the set value, mark the working state of the companion test piece at this moment as the test state, and realize that by adjusting and marking the working state of the companion test piece, the test piece can be in the specified working condition. This specified working condition can be the working state of the infrared suppressor on the aero-engine under research. Therefore, during the development process of the aero-engine, the infrared suppressor can be tested, thereby accelerating the development speed and shortening the development cycle; when collecting data, first collect the infrared radiation data of multiple measurement points of the test piece in the non-working state multiple times, and then collect the infrared radiation data of multiple measurement points of the companion test piece in the test state multiple times. By comparing the two sets of data, the infrared radiation data of the test piece can be obtained. Then, by comparing the infrared radiation data of the test piece with the infrared radiation data of the reference infrared suppressor, the consistent ability of the test piece to infrared radiation can be accurately evaluated. During the data collection process, the reliability of the test data can be improved by collecting multiple times to ensure the accuracy of the test data; this solution can obtain the infrared radiation data of the physical tail nozzle in the specified working condition in the real environment. Compared with the prior art, it can accurately evaluate the suppression ability of the tail nozzle to infrared radiation, is applicable to the test of the infrared suppressor in the helicopter field, and is beneficial to shortening the development cycle of the aero-engine, with strong practicability and being suitable for wide promotion and application.

[0022] In addition to the purposes, features and advantages described above, the present invention has other purposes, features and advantages. The following will refer to the drawings for a further detailed description of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The drawings forming a part of this application are used to provide a further understanding of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0024] Figure 1 is the step block diagram of the test method for measuring the infrared radiation characteristics of the aero-engine tail nozzle of the preferred embodiment of the present invention;

[0025] Figure 2 It is a schematic structural diagram of an experimental device for measuring the infrared radiation characteristics of an aero-engine tail nozzle according to a preferred embodiment of the present invention.

[0026] Legend:

[0027] 100, gas generator; 200, exhaust pipe; 300, tail nozzle; 400, light-shielding background wall; 500, test arc; 600, infrared measurement component. Specific implementation mode

[0028] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways defined and covered by the following.

[0029] It should be noted that the terms "include" and "have" and any variations thereof are intended to cover non-exclusive inclusion. For example, a process, method, system, product or device that includes a series of steps or units does not necessarily have to be limited to those steps or units clearly listed, but may include other steps or units not clearly listed or inherent to these processes, methods, products or devices.

[0030] As Figure 1 and Figure 2 shown, the method for measuring the infrared radiation characteristics of the aero-engine tail nozzle in this embodiment includes the following steps: S1, test arrangement: First, install the companion specimen, exhaust pipe 200, test specimen and pneumatic measurement component, then set up the light-shielding background wall 400 to form a test area to isolate the test specimen from the environment, and finally set up a test arc 500 in the test area with the test specimen as the geometric center, select multiple measurement points evenly spaced in the test arc 500, and set an infrared measurement component 600 that can be transferred between multiple measurement points. Among them, the companion specimen is the gas generator 100, and the test specimen is the tail nozzle 300; S2, test debugging: Start the companion specimen and collect the pneumatic parameters of the test specimen through the pneumatic measurement component, jointly debug the working states of the companion specimen and the test specimen, and when the pneumatic parameters of the test specimen reach the set value, mark the current working state of the companion specimen as the test state. Among them, the set value is the pneumatic parameter of the test specimen under the specified working condition; S3, data collection: First, make the companion specimen and the test specimen in a non-working state, complete the infrared radiation data collection of multiple measurement points in sequence through the infrared measurement component 600, and repeat the collection at least once. Then start the companion specimen and adjust it to the test state, collect the pneumatic parameters of the test specimen through the pneumatic measurement component, and finally complete the infrared radiation data collection of multiple measurement points in sequence through the infrared measurement component 600, and repeat the collection at least once.

[0031] Specifically, in the test method for measuring the infrared radiation characteristics of the aero-engine exhaust nozzle of the present invention, when arranging the test, the gas generator 100 is used as the companion test piece, and the exhaust nozzle 300 is used as the test piece for physical tests. Moreover, by setting up a light-shielding background wall 400 to form a test area to isolate the test piece from the environment, that is, taking the test piece as an independent test object, the test data is reliable and can accurately evaluate the suppression ability of the test piece; a test arc 500 is set in the test area with the test piece as the geometric center, and multiple measuring points are selected in the test arc 500 and arranged at uniform intervals, so as to collect infrared radiation data through an infrared measurement component 600 that can be transferred between multiple measuring points, thereby meeting the requirement of the infrared suppressor in the helicopter field being non-directional in the horizontal plane and being applicable to the test of the infrared suppressor in the helicopter field; when conducting the test commissioning, by collecting the aerodynamic parameters of the test piece, the working states of the companion test piece and the test piece are jointly debugged. When the aerodynamic parameters of the test piece reach the set value, mark the working state of the companion test piece at this moment as the test state, so as to realize that by adjusting and marking the working state of the companion test piece, the test piece can be in the specified working condition. This specified working condition can be the working condition of the infrared suppressor on the aero-engine under development. Therefore, during the development process of the aero-engine, the infrared suppressor can be tested, thus accelerating the development speed and shortening the development cycle; when collecting data, first collect the infrared radiation data of multiple measuring points in the non-working state of the test piece multiple times, and then collect the infrared radiation data of multiple measuring points in the test state of the companion test piece multiple times. By comparing the two sets of data, the infrared radiation data of the test piece can be obtained, and then by comparing the infrared radiation data of the test piece with the infrared radiation data of the reference infrared suppressor, the consistent ability of the test piece to infrared radiation can be accurately evaluated. During the data collection process, the reliability of the test data can be improved through multiple collections to ensure the accuracy of the test data; this solution can obtain the infrared radiation data of the physical exhaust nozzle 300 under the specified working condition in the real environment. Compared with the prior art, it can accurately evaluate the suppression ability of the exhaust nozzle 300 to infrared radiation, is applicable to the test of the infrared suppressor in the helicopter field, and is beneficial to shortening the development cycle of the aero-engine, with strong practicability and being suitable for wide promotion and application.

[0032] Optionally, the infrared measurement component 600 is one of an infrared thermal imager and a spectrometer. Optionally, the pneumatic measurement component includes a temperature sensor, a pressure sensor, and an air flow velocity sensor.

[0033] It should be understood that since it is different from the horizontal exhaust of turbojet and turbofan engines, the infrared suppressor of the turboshaft engine used by helicopters usually exhausts upward or downward, and the infrared radiation sources are only the infrared suppressor housing and the vertical exhaust. The imaging differences of the radiation sources observed at multiple measuring points are not significant, so equidistant testing is adopted.

[0034] It should be understood that the infrared radiation data of the reference infrared suppressor are known values. Therefore, only the infrared radiation data of the test piece can be measured. By comparing the two sets of data, the infrared radiation suppression ability of the test piece can be judged.

[0035] It should be understood that the main influencing factor for the infrared radiation data of the infrared suppressor during operation is the aerodynamic parameter. Thus, by ensuring that the aerodynamic parameter of the infrared suppressor is consistent with the aerodynamic parameter under the specified working condition, the infrared radiation data of the infrared suppressor collected during the test can be made consistent with the infrared radiation data of the infrared suppressor under the specified working condition.

[0036] In this embodiment, in step S1, the calculation formula for the radius of the test arc 500 is:

[0037]

[0038] where R is the radius of the test arc 500, ω is the field of view angle of the infrared measurement component 600, and r is the field of view diameter corresponding to the maximum contour of the test piece among all test azimuth angles.

[0039] Specifically, the radius of the test arc 500 is estimated through the above calculation formula to set the test arc 500, and then measurement points are set based on the test arc 500 to be applicable to the test of the infrared suppressor in the helicopter field.

[0040] It should be understood that the radius of the test arc 500 can be estimated according to the above formula, and during the actual test, the distance from the measurement point to the geometric center of the test piece also needs to be finely adjusted according to the field of view situation.

[0041] In this embodiment, after step S3, there is also step: S4, data processing: Set the infrared radiation data collected by the infrared measurement component 600 when the test piece is in the non-operating state as L0, then set the infrared radiation data collected by the infrared measurement component 600 when the companion test piece is in the test state as L1, and finally calculate L1 - L0 to obtain the infrared radiation data L of the test piece.

[0042] It should be understood that the infrared radiation data collected by the infrared measurement component 600 when the test piece is in the non-operating state are the infrared radiation data of the background environment within the test area; the infrared radiation data collected by the infrared measurement component 600 when the companion test piece is in the test state include the infrared radiation data of the background environment within the test area.

[0043] Specifically, through the above data processing, the influence of the background environment on the test piece can be excluded, ensuring the accuracy and reliability of the test data.

[0044] In this embodiment, between step S3 and step S4, there is also a step of checking whether the pneumatic parameters collected in step S2 and the pneumatic parameters collected in step S3 meet the repeatability requirements, and at the same time checking whether the infrared radiation data collected in step S3 meets the repeatability requirements. If both checks meet the requirements, step S4 is carried out. If any one of the checks does not meet the requirements, step S3 is repeated. Specifically, by checking whether the pneumatic parameters collected in step S2 and the pneumatic parameters collected in step S3 meet the repeatability requirements, it is used to assess whether the test piece has reached the specified working conditions, and to check whether the accompanying test piece, the test piece and the measurement components are operating well during the data collection process; by checking whether the infrared radiation data collected in step S3 meets the repeatability requirements, it is used to judge whether the data repeatedly collected under the same state (that is, the non-working state of the test piece and the test state of the accompanying test piece) is accurate, so as to improve the accuracy of the infrared radiation data.

[0045] In this embodiment, in step S1, the number of measuring points is 8 to 12, and the included angle between the connecting lines of the first and last measuring points and the test piece is 90°. Specifically, when the number of measuring points is between 8 and 12, the test cost is reasonable, the test time is short, and the test results are accurate; when the number of measuring points is less than 8, the accuracy of the test results is low; when the number of measuring points exceeds 12, the test cost is high and the test time is long; by controlling the included angle between the connecting lines of the first and last measuring points and the test piece to be 90°, the geometric symmetry of the test piece on the helicopter is fully utilized, saving test resources.

[0046] It should be understood that the helicopter exhaust ports are usually arranged on both sides of the fuselage. For the infrared suppressor installed on one side of the exhaust port, the infrared radiation relative to the other side is usually blocked by the fuselage. Therefore, during the actual test, only the infrared radiation in the range of one side, that is, 0° - 90°, needs to be studied.

[0047] In this embodiment, the pneumatic parameters include the inlet total pressure, the inlet static pressure, the inlet air flow velocity, the outlet temperature, the outlet total pressure and the outlet air flow velocity. Specifically, by collecting the above pneumatic parameters, it is used to judge whether the test piece reaches the specified working conditions during the test.

[0048] Optionally, during the actual test process, the atmospheric temperature, the atmospheric pressure and the humidity also need to be collected to reduce the influence of the environment on the test results.

[0049] In this embodiment, before step S2, there is also a step of completing the inspection work before the start of the accompanying test piece, checking the installation reliability of the test piece, and confirming that the pneumatic measurement component is operating normally. Specifically, by checking and confirming the accompanying test piece, the test piece and the pneumatic measurement component, it is used to ensure the stable and reliable collection of the pneumatic parameters, so as to ensure that the calibrated test state during the test commissioning meets the subsequent test requirements, and finally improve the accuracy of the test results.

[0050] In this embodiment, before step S3, the following steps are further included: confirming that the test area is in a light-shielded environment, checking and confirming that the companion specimen and the test specimen are in good condition, calibrating the infrared measurement component 600 using a black box, confirming that it can completely cover the test specimen, and confirming that the pneumatic measurement component and the infrared measurement component 600 are operating well. Specifically, by checking and confirming the test environment, the companion specimen, the test specimen, the pneumatic measurement component, and the infrared measurement component 600, the accuracy of data collection is improved, thereby improving the accuracy of the test results.

[0051] It should be understood that the test area can be in a light-shielded environment during a night test.

[0052] As Figure 2 shown, the test device for measuring the infrared radiation characteristics of an aero-engine tail nozzle in this embodiment adopts the above-mentioned test method for measuring the infrared radiation characteristics of an aero-engine tail nozzle. The test device includes a test stand (not shown in the figure), a gas generator 100 installed on the test stand, an exhaust pipe 200 connected to the gas generator 100, a tail nozzle 300 connected to the exhaust pipe 200, a pneumatic measurement component (not shown in the figure) arranged on the tail nozzle 300, a light-shielding background wall 400 arranged on both sides of the tail nozzle 300 at a preset angle for forming a test area, and an infrared measurement component 600 for collecting infrared radiation data in the test area. The tail nozzle 300 and the infrared measurement component 600 are arranged at the same height. Specifically, the gas generator 100 is installed through the test stand so that the gas generator 100 is at a preset height from the ground (the preset height is not less than 3 meters). The high-temperature gas generated by starting the gas generator 100 is transported to the tail nozzle 300 through the exhaust pipe 200. All radiation sources outside the tail nozzle 300 are blocked by the light-shielding background wall 400, and the test field background is ensured to be uniform. The pneumatic parameters of the tail nozzle 300 are collected through the pneumatic measurement component to determine whether the tail nozzle 300 reaches the specified working condition through the pneumatic parameters. The infrared radiation data of the tail nozzle 300 are collected through the infrared measurement component 600 to provide data support for evaluating the infrared radiation suppression ability of the tail nozzle 300. Moreover, the tail nozzle 300 and the infrared measurement component 600 are arranged at the same height to ensure the stability and reliability of data collection.

[0053] Optionally, multiple infrared measurement components 600 are arranged to simultaneously collect data at multiple measurement points through the multiple infrared measurement components 600, thereby improving the collection efficiency.

[0054] Optionally, the length of the light-shielding background wall 400 is 10 meters.

[0055] In this embodiment, the test device further includes a moving component for supporting the infrared measurement component 600 and driving the infrared measurement component 600 to move between multiple measurement points, and a remote controller wirelessly connected to the moving component. Specifically, after the measurement component completes the measurement at a measurement point, the moving component is remotely controlled by the remote controller to transfer to the next measurement point, so as to drive the infrared measurement component 600 to move to the next measurement point at the same time, thereby realizing continuous measurement without stopping the operation of the gas generator 100, saving test time and reducing test costs.

[0056] The foregoing is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A test method for measuring infrared radiation characteristics of an aircraft engine tail nozzle, characterized in that: The following steps are involved: S1, test arrangement: firstly, a test piece, a test piece and a pneumatic measurement assembly are installed, then a light-shielding background wall (400) is set to form a test area to isolate the test piece from the environment, and finally a test arc (500) is set in the test area with the test piece as the geometric center, a plurality of measurement points evenly spaced are selected on the test arc (500), and an infrared measurement assembly (600) that can be transferred between the plurality of measurement points is set, wherein the test piece is a gas generator (100) and the test piece is a tail nozzle (300); S2, test debugging: start the accompanying test piece and collect the pneumatic parameters of the test piece through the pneumatic measurement component, jointly debug the working status of the accompanying test piece and the test piece, and when the pneumatic parameters of the test piece reach the set value, mark the working status of the accompanying test piece at this moment as the test status, wherein the set value is the pneumatic parameter of the test piece under the specified working condition; S3, data collection: firstly, the accompanying test piece and the test piece are placed in a non-operating state, and infrared radiation data collection of a plurality of measuring points is sequentially completed through the infrared measurement component (600), and the collection is repeated at least once, then the accompanying test piece is started and adjusted to a test state, and the pneumatic parameters of the test piece are collected through the pneumatic measurement component, and finally, infrared radiation data collection of a plurality of measuring points is sequentially completed through the infrared measurement component (600), and the collection is repeated at least once.

2. The infrared radiation characteristic measurement test method of an aircraft engine tail nozzle according to claim 1 is characterized in that: In step S1, the radius calculation formula of the test arc (500) is: Wherein, R is the radius of the test arc (500), ω is the field of view angle of the infrared measurement component (600), and r is the field of view diameter corresponding to the maximum contour of the test piece in all test azimuth angles.

3. The infrared radiation characteristic measurement test method of an aircraft engine tail nozzle according to claim 1 is characterized in that: Step S3 further includes the following steps: S4, data processing: setting the infrared radiation data collected by the infrared measurement component (600) when the test piece is not in operation to L0, then setting the infrared radiation data collected by the infrared measurement component (600) when the test piece is in testing state to L1, and finally subtracting L1 from L0 to obtain the infrared radiation data L of the test piece.

4. The infrared radiation characteristic measurement test method of an aircraft engine tail nozzle according to claim 3 is characterized in that: The steps between step S3 and step S4 include: Check whether the aerodynamic parameters collected in step S2 and the aerodynamic parameters collected in step S3 meet the repeatability requirements, and check whether the infrared radiation data collected in step S3 meets the repeatability requirements. If both checks meet the requirements, proceed to step S4. If any check does not meet the requirements, repeat step S3.

5. The infrared radiation characteristic measurement test method of an aircraft engine tail nozzle according to any one of claims 1 to 4, characterized in that: In step S1, the number of measuring points is 8-12, and the angle between the first and last measuring points and the line connecting the test piece is 90°.

6. The infrared radiation characteristic measurement test method of an aircraft engine tail nozzle according to any one of claims 1 to 4, characterized in that: Aerodynamic parameters include inlet total pressure, inlet static pressure, inlet air flow velocity, outlet temperature, outlet total pressure and outlet air flow velocity.

7. The infrared radiation characteristic measurement test method of an aircraft engine tail nozzle according to any one of claims 1 to 4, characterized in that: Before step S2, the method further includes the following steps: Complete the inspection work before starting the test piece, check the installation reliability of the test piece, and confirm that the pneumatic measurement components are operating normally.

8. The infrared radiation characteristic measurement test method of an aircraft engine tail nozzle according to any one of claims 1 to 4, characterized in that: Before step S3, the method further includes the following steps: Confirm that the test area is in a light-proof environment, check and confirm that the test piece and the test piece are in good condition, use a black box to calibrate the infrared measurement component (600) to confirm that it can completely cover the test piece, and confirm that the pneumatic measurement component and the infrared measurement component (600) are operating well.

9. An aircraft engine tail nozzle infrared radiation characteristic measurement test device, characterized in that: The infrared radiation characteristic measurement test method of an aircraft engine tail nozzle as claimed in any one of claims 1 to 8 is adopted, and the test device comprises a test bench, a gas generator (100) installed on the test bench, an exhaust pipe (200) connected to the gas generator (100), a tail nozzle (300) connected to the exhaust pipe (200), an aerodynamic measurement component arranged on the tail nozzle (300), a light-shielding background wall (400) arranged at a preset angle on both sides of the tail nozzle (300) for forming a test area, and an infrared measurement component (600) for collecting infrared radiation data in the test area, wherein the tail nozzle (300) and the infrared measurement component (600) are arranged at the same height.

10. The infrared radiation characteristic measurement test device for the tail nozzle of an aircraft engine according to claim 9, characterized in that: The test device also includes a moving component for supporting the infrared measurement component (600) and driving the infrared measurement component (600) to move between multiple measurement points, and a remote controller wirelessly connected to the moving component.

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