Turboprop engine bird swallowing test device

Abstract

This invention discloses a bird-swallowing test device for a turboprop engine, comprising an air-gun launching assembly, a propeller phase sensing assembly, a muzzle vision measurement assembly, and a control assembly. The air-gun launching assembly includes an air source component, control valves connected to the air source component and the control assembly respectively, and a launching component connected to the control valve. By utilizing a "time delay compensation" collaborative triggering mechanism, the launching accuracy of the bird projectiles is improved, ensuring that the bird projectiles can accurately pass through the plane of the high-speed rotating propeller. Through the integrated design of "centralized air source + parallel gun barrel", N bird projectiles at a set speed are launched within a set time. Through real-time trajectory correction, the trajectory consistency of the bird projectiles is ensured to meet the requirements. Compared with the prior art, this device meets the extreme requirements of high-power turboprop engine bird-swallowing tests for launching density, speed, accuracy, and consistency, greatly reduces test risks, and improves reliability, repeatability, and safety. It is highly practical and suitable for widespread promotion and application.

Description

Technical Field

[0001] This invention relates to the field of whole-engine bird swallowing test technology, and in particular, to a whole-engine bird swallowing test device for turboprop engines. Background Technology

[0002] Turboprop engines are highly susceptible to ingesting birds during takeoff and low-altitude flight. Bird strikes can cause propeller blade breakage, engine surge and stall, or even structural disintegration, seriously threatening flight safety. Therefore, airworthiness regulations mandate that engines undergo bird strike testing to ensure their reliability under extreme conditions. The bird strike test uses a specially designed "bird projectile" simulating the weight and density of a real bird, propelled at high speed into the running engine via an air cannon or compressed gas device.

[0003] In existing bird launch tests, since there is no propeller to obstruct the air, the high-pressure gas in the air gun pushes the sabot containing the bird forward at an accelerated speed. The sabot separates from the projectile at the muzzle separator, and the projectile moves forward at a calibrated speed. The bird, moving in a straight line in the horizontal direction, can be accurately launched to the designated position.

[0004] The requirements for bird-swallowing tests of high-power turbine engines are as follows:

[0005] 1. Extremely high launch frequency and quality: It can launch five small birds weighing between 80g and 100g in succession within 1 second;

[0006] 2. Extremely high launch speed: Each bird needs to launch at a speed of 350 km / h to simulate the takeoff / approach speed of an aircraft;

[0007] 3. Extremely high timing accuracy: The "time window" between each blade of the engine propeller is extremely short. The control system must ensure that each bird is launched at an extremely precise moment to accurately pass through the high-speed rotating propeller plane and enter the engine air intake, rather than hitting the blade. A single incorrect impact will damage the propeller and engine, and the test will fail.

[0008] 4. Ballistic Consistency: The trajectories of the five birds must be highly consistent to ensure that they all enter the air intake through the preset path.

[0009] However, existing bird-swallowing gas cannons mostly employ single-gun sequential triggering or simple multi-gun parallel control methods. Single-gun sequential triggering control refers to using a complex mechanical loading mechanism (such as a rotating magazine and push rod system) to continuously load and fire multiple bird projectiles into the same barrel in a very short time. This has the following drawbacks when applied to bird-swallowing tests of high-power turbine engines:

[0010] 1. Mechanical Limits: There is a physical limit to the speed of movement of mechanical structures. It is almost impossible to complete 5 high-reliability loading, sealing and launching operations within 1 second. Jamming, impact or sealing failure are very likely to occur.

[0011] 2. Pressure fluctuation: When the same gas tank releases high-pressure gas continuously in a short period of time, the pressure inside the gun barrel cannot be stabilized quickly, resulting in a significant decrease in the muzzle velocity of subsequent shells and making it impossible to guarantee the consistency of the velocity of the five bird shells.

[0012] 3. Limited timing control: Once the first shot is fired, the timing of subsequent shots is fixed by the mechanical process and cannot be dynamically adjusted according to the real-time phase of the propeller.

[0013] Parallel control of multiple guns refers to the use of multiple independent gas guns, each pre-loaded with a bird projectile. Multiple quick-opening valves are triggered simultaneously or after a fixed delay by a main control signal to fire the projectiles. However, this method has the following drawbacks when applied to bird-swallowing tests of high-power turbine engines:

[0014] 1. Synchronization Error: Factors such as the response time of each quick-opening valve, slight pressure differences in each gas tank, and differences in the friction coefficient of each gun barrel can cause millisecond (ms) errors in the firing of each gun. This error is fatal for a 1020 RPM propeller, enough to cause a bird to strike the blade instead of entering the blade disk gap;

[0015] 2. Wake interference: Even if all five cannons fire at the same time, the first bird shell fired will create a shock wave at the muzzle, which will disturb the trajectory of the subsequent bird shells leaving the barrel ("wake effect"), causing the trajectory to diverge and the subsequent bird shells to deviate from the intended trajectory.

[0016] 3. The control system is bulky: the five independent high-pressure gas sources and the launching system are very bulky and difficult to adjust and calibrate.

[0017] In summary, existing technologies are insufficient to meet the extreme requirements for launch density, speed, accuracy, and consistency during bird-swallowing tests of high-power turboprop engines, and cannot guarantee the reliability, repeatability, and safety of the tests.

[0018] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this invention, the above background information should not be used to evaluate the novelty and inventiveness of this invention. Summary of the Invention

[0019] This invention provides a whole-engine bird swallowing test device for turboprop engines, which solves the technical problems of existing bird swallowing tests being unable to meet the extreme requirements of launch density, speed, accuracy and consistency for bird swallowing tests of high-power turboprop engines, and having high test risks, low reliability, repeatability and safety.

[0020] According to one aspect of the present invention, a turboprop engine bird-swallowing test device is provided, comprising an air gun launching assembly, a propeller phase sensing assembly, a muzzle vision measurement assembly, and a control assembly. The air gun launching assembly includes an air source component for providing a power source for launching, control valves connected to the air source component and the control assembly respectively, and a launching component for launching bird projectiles connected to the control valves. There are N control valves, where N is an integer greater than 1. The launching component and the control valves are arranged in a one-to-one correspondence. The propeller phase sensing assembly is connected to the control assembly and is used to measure the propeller phase to transmit a phase signal to the control assembly. The control assembly is used to calculate the theoretical launch time based on the phase signal and pre-store the response deviation times of the N control valves. The difference between the theoretical launch time and the response deviation time is then set as the actual trigger time of the control valve. The muzzle vision measurement assembly is connected to the control assembly and is used to calculate the muzzle velocity and launch angle of the bird projectile after launch and transmit the signal to the control assembly. The control assembly is used to correct the launch pressure, launch time, and launch angle of subsequent bird projectiles based on the muzzle velocity and launch angle of the first bird projectile after launch.

[0021] As a further improvement to the above technical solution:

[0022] Furthermore, the gas source components include an air compressor, a high-pressure gas cylinder connected to the air compressor for storing high-pressure gas, a pressure reducing valve connected to the high-pressure gas cylinder, an inflation valve connected to the pressure reducing valve, and a gas storage housing connected to the inflation valve and the control valve respectively.

[0023] Furthermore, the gas storage shell includes a gas storage chamber and a control gas chamber, with the pressure in the control gas chamber being higher than the pressure in the gas storage chamber.

[0024] Furthermore, the control assembly includes a controller connected to the propeller phase sensing assembly and the muzzle vision measurement assembly, respectively, and a control box connected to the controller, the inflation valve, and the control valve, respectively.

[0025] Furthermore, the control components also include pressure sensors installed on the gas storage housing and connected to the control box for monitoring the internal gas pressure of the gas storage housing.

[0026] Furthermore, the control assembly also includes a venting valve connected to the control box and the gas storage housing respectively, for adjusting the internal air pressure of the gas storage housing in conjunction with the inflation valve.

[0027] Furthermore, the test apparatus also includes a mounting base, a height adjustment bracket 1 disposed on the mounting base and connected to the gas storage shell for adjusting the height of the gas storage shell, and a height adjustment bracket 2 disposed on the mounting base and connected to the launcher for adjusting the height of the launcher.

[0028] Furthermore, the propeller phase sensing assembly includes a laser phase sensor for mounting in front of the output shaft of the test engine.

[0029] Furthermore, the muzzle vision measurement component includes M measurement cameras deployed in front of the firing element, with a frame rate of ≥10000fps, where M is a positive integer.

[0030] Furthermore, the launching component includes a loading mechanism connected to a control valve, a gun barrel connected to the loading mechanism, and a sabot separator disposed on the launching end of the gun barrel.

[0031] The present invention has the following beneficial effects:

[0032] The turboprop engine bird-swallowing test device of the present invention first measures the propeller phase using a propeller phase sensing component to transmit the phase signal to a control component. The control component then calculates the theoretical launch time based on the phase signal and pre-stores the response deviation times of N control valves. The difference between the theoretical launch time and the response deviation time is then set as the actual trigger time of the control valves. By actively introducing compensation, inherent hardware errors are offset, improving the launch accuracy of the N bird projectiles. The air gun launching component provides the launch power source through an air source component and controls the corresponding launching components through N control valves, thereby launching N bird projectiles within a set time. This balances air source consistency and high-speed multi-gun firing, meeting the test requirements for launch density and launch speed. After the first bird projectile is deflected, the muzzle vision measurement component calculates the muzzle velocity and launch angle of the first bird projectile and transmits the signal to the control component. The control components then adjust the launch pressure, launch time, and launch angle of subsequent bird projectiles based on the muzzle velocity and launch angle of the first bird projectile, proactively addressing uncertainties such as pressure fluctuations, individual bird projectile differences, and wake disturbances, thus improving the launch consistency of N bird projectiles. This scheme improves the launch accuracy of bird projectiles by utilizing a "time delay compensation" collaborative triggering mechanism, ensuring that the bird projectiles accurately pass through the plane of the high-speed rotating propeller. Through the integrated design of "centralized air source + parallel gun barrel," it achieves the launch of N bird projectiles at a set velocity within a set time. Real-time ballistic correction ensures that the ballistic consistency of the bird projectiles meets the requirements. Compared with existing technologies, this scheme meets the extreme requirements of high-power turboprop engine bird ingestion tests for launch density, velocity, accuracy, and consistency, greatly reducing test risks and improving reliability, repeatability, and safety. It is highly practical and suitable for widespread promotion and application.

[0033] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0034] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0035] Figure 1 This is a schematic diagram of the structure of the turboprop engine bird-swallowing test device according to a preferred embodiment of the present invention.

[0036] Legend:

[0037] 10. Air cannon firing assembly; 11. High-pressure gas cylinder; 12. Pressure reducing valve; 13. Inflation valve; 14. Gas storage shell; 15. Control valve; 16. Loading mechanism; 17. Gun barrel; 18. Spawn separator; 21. Measuring camera; 22. Illumination components; 30. Control assembly; 31. Controller; 32. Control box; 33. Pressure sensor; 34. Vent valve; 41. Mounting base; 42. Height adjustment bracket one; 43. Height adjustment bracket two. Detailed Implementation

[0038] The following description provides specific application scenarios and requirements for this specification, intended to enable those skilled in the art to make and use the contents of this specification. Various partial modifications to the disclosed embodiments will be apparent to those skilled in the art, and the general principles defined herein can be applied to other embodiments and applications without departing from the spirit and scope of this specification. Therefore, this specification is not limited to the embodiments shown, but rather to the widest scope consistent with the claims.

[0039] The terminology used herein is for the purpose of describing particular exemplary embodiments only and is not restrictive. For example, unless the context clearly indicates otherwise, the singular forms “a,” “an,” and “the” as used herein may also include the plural forms. When used in this specification, the terms “comprising,” “including,” and / or “containing” mean that the associated integers, steps, operations, elements, and / or components are present, but do not preclude the presence of one or more other features, integers, steps, operations, elements, components, and / or groups, or that other features, integers, steps, operations, elements, components, and / or groups may be added to the system / method.

[0040] Considering the following description, these and other features of this specification, as well as the operation and function of the related components of the structure, and the economy of assembly and manufacture of the parts, can be significantly improved. All of these form part of this specification with reference to the accompanying drawings. However, it should be clearly understood that the drawings are for illustrative and descriptive purposes only and are not intended to limit the scope of this specification. It should also be understood that the drawings are not drawn to scale.

[0041] like Figure 1 As shown, the turboprop engine bird-swallowing test device of this embodiment includes an air gun launching assembly 10, a propeller phase sensing assembly (not shown), a muzzle vision measurement assembly, and a control assembly 30. The air gun launching assembly 10 includes an air source component for providing a power source for launching, control valves 15 connected to the air source component and the control assembly 30 respectively, and a launching component for launching bird projectiles connected to the control valves 15. There are N control valves 15, where N is an integer greater than 1. The launching components and control valves 15 are arranged in a one-to-one correspondence. The propeller phase sensing assembly is connected to the control assembly 30 and is used to measure the propeller phase. The phase signal is transmitted to the control component 30. The control component 30 is used to calculate the theoretical firing time based on the phase signal and to pre-store the response deviation time of N control valves 15. Then, the difference between the theoretical firing time and the response deviation time is set as the actual triggering time of the control valve 15. The muzzle vision measurement component is connected to the control component 30 and is used to calculate the muzzle velocity and firing angle of the bird projectile after firing and transmit the signal to the control component 30. The control component 30 is used to correct the firing pressure, firing time and firing angle of subsequent bird projectiles based on the muzzle velocity and firing angle of the first bird projectile after firing.

[0042] like Figure 1As shown, specifically, the turboprop engine bird-swallowing test device of the present invention first measures the propeller phase through the propeller phase sensing component to transmit the phase signal to the control component 30. The control component 30 then calculates the theoretical launch time based on the phase signal and pre-stores the response deviation time of N control valves 15. The difference between the theoretical launch time and the response deviation time is then set as the actual trigger time of the control valve 15. By actively introducing compensation, the inherent hardware error is offset, improving the launch accuracy of the N bird projectiles. The air gun launching component 10 provides the launch power source through the air source component, and then controls the corresponding launching components through N control valves 15 respectively, thereby launching N bird projectiles within a set time. This balances air source consistency and high-speed firing of multiple guns, meeting the test requirements for launch density and launch speed. After the first bird projectile is deflected, the muzzle vision measurement component calculates the muzzle velocity and launch angle of the first bird projectile and transmits the signal. The first bird projectile is sent to the control component 30, which then adjusts the launch pressure, launch time, and launch angle of subsequent bird projectiles based on the muzzle velocity and launch angle of the first projectile. This proactively addresses uncertainties such as pressure fluctuations, individual differences in bird projectiles, and wake disturbances, improving the launch consistency of N bird projectiles. This scheme improves the launch accuracy of bird projectiles by utilizing a "time delay compensation" collaborative triggering mechanism, ensuring that the bird projectiles accurately pass through the plane of the high-speed rotating propeller. Through the integrated design of "centralized air source + parallel gun barrel 17," N bird projectiles at a set velocity are launched within a set time. Real-time ballistic correction ensures that the ballistic consistency of the bird projectiles meets the requirements. Compared to existing technologies, this scheme meets the extreme requirements of high-power turboprop engine bird-swallowing tests for launch density, velocity, accuracy, and consistency, significantly reducing test risks and improving reliability, repeatability, and safety. It is highly practical and suitable for widespread promotion and application.

[0043] Optionally, the control valve 15 is a solenoid valve or a piezoelectric valve with a response time of less than 1ms.

[0044] It should be understood that the set time, set speed, and N can be adaptively set according to the test requirements. In one embodiment, five bird missiles at 350 km / h are launched within 1 second.

[0045] It should be understood that firing density refers to firing a set number of bird shots within a set time period.

[0046] like Figure 1As shown, in this embodiment, the air source includes an air compressor, a high-pressure gas cylinder 11 connected to the air compressor for storing high-pressure gas, a pressure reducing valve 12 connected to the high-pressure gas cylinder 11, an inflation valve 13 connected to the pressure reducing valve 12, and a gas storage shell 14 connected to the inflation valve 13 and the control valve 15 respectively. Specifically, the air compressor operates to fill the high-pressure gas cylinder 11 with compressed air at a set pressure. After pressure reduction and stabilization by the pressure reducing valve 12, the pressure of the compressed air output from the high-pressure gas cylinder 11 is ensured to be stable. The compressed air is then delivered to the gas storage shell 14 via the inflation valve 13. During a bird-swallowing test, triggering the control valve 15 will cause the bird to be launched by the compressed air. The launch speed is positively correlated with the pressure of the compressed air. By ensuring the stability and accuracy of the compressed air pressure, the launch speed of N bird projectiles can be ensured to be stable and accurate.

[0047] like Figure 1 As shown, in this embodiment, the gas storage housing 14 includes a gas storage chamber and a control gas chamber, with the pressure in the control gas chamber being higher than that in the gas storage chamber. Specifically, compressed air is stored in the gas storage chamber to ensure a continuous supply of compressed air, and the firing speed is controlled by the control gas chamber. Furthermore, by ensuring that the pressure in the control gas chamber is higher than that in the gas storage chamber, the impact of pressure attenuation during compressed air transmission is buffered, thereby ensuring that the firing speed of N bird projectiles is stable and accurate.

[0048] like Figure 1 As shown, in this embodiment, the control component 30 includes a controller 31 connected to the propeller phase sensing component and the muzzle vision measurement component, and a control box 32 connected to the controller 31, the inflation valve 13, and the control valve 15. Specifically, the controller 31 receives the phase signal transmitted by the propeller phase sensing component and the image signal transmitted by the muzzle vision measurement component, and controls the inflation valve 13 and the control valve 15 to operate through the control box 32. After the inflation valve 13 opens and reaches the set pressure, the control valve 15 can be triggered to start the bird-swallowing test. After the first bird projectile is fired and the muzzle velocity is lower than the set value, the triggering time of subsequent valves can be advanced to correct the firing time and improve firing accuracy.

[0049] Optionally, the controller 31 is a computer loaded with control software.

[0050] like Figure 1 As shown, in this embodiment, the control component 30 further includes a pressure sensor 33 disposed on the gas storage housing 14 and connected to the control box 32 for monitoring the internal air pressure of the gas storage housing 14. Specifically, by monitoring the internal air pressure of the gas storage housing 14 through the pressure sensor 33, the controller 31 ensures that the control valve 15 is triggered to start the bird-swallowing test only after the set pressure is reached, so as to ensure accurate launch speed.

[0051] like Figure 1As shown, in this embodiment, the control component 30 further includes a venting valve 34 connected to the control box 32 and the gas storage housing 14, respectively, for cooperating with the inflation valve 13 to adjust the internal air pressure of the gas storage housing 14. Specifically, the venting valve 34 can discharge compressed air from the gas storage housing 14, thereby cooperating with the inflation valve 13 to adjust the internal air pressure of the gas storage housing 14, thus achieving precise control of the firing speed; after the first bird shot is fired, the venting valve 34, in cooperation with the inflation valve 13, adjusts the internal air pressure of the gas storage housing 14 to correct the firing pressure, thereby ensuring that the firing speed meets the test requirements.

[0052] like Figure 1 As shown, in this embodiment, the test apparatus further includes a mounting base 41, a height adjustment bracket 42 disposed on the mounting base 41 and connected to the gas storage housing 14 for adjusting the height of the gas storage housing 14, and a height adjustment bracket 43 disposed on the mounting base 41 and connected to the launcher for adjusting the height of the launcher. Specifically, the angle correction includes pitch angle correction, and by cooperating with the height adjustment bracket 42 and the height adjustment bracket 43, the pitch angle of the launcher can be adjusted to achieve pitch angle correction.

[0053] Optionally, the angle correction also includes yaw angle correction. The launcher is connected to the control valve 15 via a flange, and the flange can be used to make fine adjustments to the yaw angle, thereby achieving yaw angle correction.

[0054] In this embodiment, the propeller phase sensing component includes a laser phase sensor for mounting in front of the output shaft of the test engine. Specifically, the laser phase sensor measures the propeller rotation angle (phase) in real time and sends the 0-360° phase signal as a high-frequency pulse to the control component 30 as a reference signal for the entire launch timing.

[0055] like Figure 1 As shown, in this embodiment, the muzzle vision measurement component includes M measuring cameras 21 positioned in front of the firing component. The frame rate of the measuring cameras 21 is ≥10000fps, and M is a positive integer. Specifically, the field of view of the M measuring cameras 21 covers the muzzle area. Once a bird projectile is detected, its image is immediately analyzed to calculate the actual muzzle velocity and firing angle of the first bird projectile. Optionally, the muzzle vision measurement component also includes an illumination element 22 used in conjunction with the M measuring cameras 21. Optionally, the illumination element 22 is an LED light.

[0056] like Figure 1As shown, in this embodiment, the launching component includes a loading mechanism 16 connected to the control valve 15, a gun barrel 17 connected to the loading mechanism 16, and a sabot separator 18 disposed on the launching end of the gun barrel 17. Specifically, before the test, the bird projectile is loaded into the sabot of the loading mechanism 16. After reaching the set pressure and the actual triggering condition, the control component 30 triggers the control valve 15. The sabot and the bird projectile are fired out of the gun barrel 17 under the action of compressed air, and the sabot is separated from the bird projectile by the action of the sabot separator 18, so that the bird projectile impacts the test piece at a set speed.

[0057] The foregoing has described specific embodiments of this specification. Other embodiments are within the scope of the appended claims. In some cases, the actions or steps recited in the claims may be performed in a different order than that shown in the embodiments and may still achieve the desired result. Furthermore, the processes depicted in the drawings do not necessarily require a specific or sequential order to achieve the desired result. In some embodiments, multitasking and parallel processing are possible or may be advantageous.

[0058] In summary, after reading the detailed disclosure of this specification, those skilled in the art will understand that the foregoing detailed disclosure is presented by way of example only and is not restrictive. Although not explicitly stated herein, those skilled in the art will understand that this specification requires various reasonable changes, improvements, and modifications to the embodiments. These changes, improvements, and modifications are intended to be made by this specification and are within the spirit and scope of the exemplary embodiments described herein.

[0059] Furthermore, certain terms in this specification have been used to describe embodiments of this specification. For example, "an embodiment," "an embodiment," and / or "some embodiments" mean that a particular feature, structure, or characteristic described in connection with that embodiment may be included in at least one embodiment of this specification. Therefore, it is to be emphasized and understood that two or more references to "an embodiment" or "an embodiment" or "alternative embodiment" in various parts of this specification do not necessarily refer to the same embodiment. Moreover, specific features, structures, or characteristics may be suitably combined in one or more embodiments of this specification.

[0060] It should be understood that in the foregoing description of the embodiments in this specification, various features are combined in a single embodiment, drawing, or description for the purpose of simplifying the description and aiding in the understanding of a feature. However, this does not mean that the combination of these features is necessary, and those skilled in the art may readily identify some of the devices as separate embodiments when reading this specification. That is, the embodiments in this specification can also be understood as an integration of multiple secondary embodiments. It is also valid when each secondary embodiment contains fewer than all the features of a single foregoing disclosed embodiment.

[0061] Each patent, patent application, publication of the patent application, and other materials such as articles, books, specifications, publications, documents, articles, etc., cited herein may be incorporated by reference. The entire contents used for all purposes, except for any history of prosecution documents associated with it, that may be inconsistent with or conflict with this document, or that may have a limiting effect on the widest extent of the claims, are now or hereafter associated with this document. For example, in the event of any inconsistency or conflict between the description, definition, and / or use of terms associated with any of the included materials and the terms, description, definition, and / or used in connection with this document, the terms used herein shall prevail.

[0062] Finally, it should be understood that the embodiments disclosed herein are illustrative of the principles of the embodiments described in this specification. Other modified embodiments are also within the scope of this specification. Therefore, the embodiments disclosed in this specification are merely examples and not limitations. Those skilled in the art can implement the applications described in this specification using alternative configurations based on the embodiments in this specification. Therefore, the embodiments in this specification are not limited to the embodiments precisely described in the applications.

Claims

1. An apparatus for swallowing bird test of a turboprop engine as a whole, characterized in that, The air cannon launching assembly (10) comprises an air source member for providing a launching power source, a control valve (15) connected with the air source member and the control assembly (30) respectively, and a launching member for launching the bird bomb connected with the control valve (15), the control valve (15) is provided with N, N is an integer greater than 1, the launching member and the control valve (15) are one-to-one corresponding, the propeller phase sensing assembly is connected with the control assembly (30), for measuring the propeller phase to transmit the phase signal to the control assembly (30), the control assembly (30) is used for calculating the theoretical launching time according to the phase signal, and the response deviation time of the N control valves (15) is stored in advance, and then the difference between the theoretical launching time and the response deviation time is set as the actual trigger time of the control valve (15), the muzzle visual measurement assembly is connected with the control assembly (30), for calculating the muzzle velocity and the launch angle after the bird bomb is launched and transmitting the signal to the control assembly (30), and the control assembly (30) is used for correcting the launch pressure, launch time and launch angle of the subsequent bird bomb according to the muzzle velocity and the launch angle after the first bird bomb is launched.

2. The nacelle bird ingestion test device of claim 1, wherein, The air source member comprises an air compressor, a high-pressure gas cylinder (11) for storing high-pressure gas connected with the air compressor, a pressure reducing valve (12) connected with the high-pressure gas cylinder (11), an inflation valve (13) connected with the pressure reducing valve (12), and a gas storage shell (14) connected with the inflation valve (13) and the control valve (15) respectively.

3. The nacelle bird ingestion test device of claim 2, wherein, The gas storage shell (14) comprises a gas storage chamber and a control gas chamber, and the pressure of the control gas chamber is higher than that of the gas storage chamber.

4. The nacelle bird ingestion test device of claim 2, wherein, The control assembly (30) comprises a controller (31) connected with the propeller phase sensing assembly and the muzzle visual measurement assembly respectively, and a control box (32) connected with the controller (31), the inflation valve (13) and the control valve (15) respectively.

5. The nacelle bird ingestion test device of claim 4, wherein, The control assembly (30) further comprises a pressure sensor (33) arranged on the gas storage shell (14) and connected with the control box (32), for monitoring the internal gas pressure of the gas storage shell (14).

6. The nacelle bird ingestion test device of claim 4, wherein, The control assembly (30) further comprises a gas release valve (34) connected with the control box (32) and the gas storage shell (14) respectively, for adjusting the internal gas pressure of the gas storage shell (14) in cooperation with the inflation valve (13).

7. The nacelle bird ingestion test device of claim 2, wherein, The test device further comprises a mounting base (41), a height adjusting support one (42) arranged on the mounting base (41) and connected with the gas storage shell (14) for adjusting the height of the gas storage shell (14), and a height adjusting support two (43) arranged on the mounting base (41) and connected with the launching member for adjusting the height of the launching member.

8. The nacelle bird ingestion test device of any of claims 1-7, wherein, The propeller phase sensing assembly comprises a laser phase sensor for being installed in front of the output shaft of the test engine.

9. The nacelle bird ingestion test device of any of claims 1-7, wherein, The muzzle visual measurement assembly comprises M measurement cameras (21) arranged in front of the launching member, the frame rate of the measurement camera (21) is greater than or equal to 10000 fps, and M is a positive integer.

10. The whole engine bird ingestion test device according to any one of claims 1-7, characterized in that, The launching mechanism comprises a charging mechanism (16) connected with the control valve (15), a barrel (17) connected with the charging mechanism (16), and a cartridge support separator (18) arranged on the launching end of the barrel (17).

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