Turboprop engine whole machine bird swallowing test device

Abstract

The invention discloses a turboprop engine whole machine bird swallowing test device, which comprises an air cannon launching assembly, a propeller phase sensing assembly, a muzzle vision measurement assembly and a control assembly, and is characterized in that the air cannon launching assembly comprises an air source part, a control valve connected with the air source part and the control assembly, and a launching part connected with the control valve; a time delay compensation cooperative triggering mechanism is utilized, the launching precision of the bird bombs is improved, it is ensured that the bird bombs can accurately penetrate through a high-speed rotating propeller plane, through the fusion design of a concentrated air source and a parallel gun barrel, N bird bombs at the set speed are launched within the set time, and it is ensured that the ballistic consistency of the bird bombs meets the requirement through real-time ballistic correction; compared with the prior art, extreme requirements of the high-power turboprop engine bird-swallowing test on launching density, speed, precision and consistency are met, the test risk is greatly reduced, the reliability, repeatability and safety are improved, the practicability is high, and the device is suitable for wide popularization and application.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of whole machine bird ingestion test, in particular, relates to a turbo-prop engine whole machine bird ingestion test device. BACKGROUND

[0002] Bird ingestion events are extremely common for turbo-prop engines during take-off and low altitude flight. Bird ingestion can cause propeller blade breakage, engine surge stall and even structural disintegration, which seriously threatens flight safety. Therefore, the airworthiness regulations require that the engine must pass the bird ingestion test to ensure its reliability under extreme conditions. The engine bird ingestion test uses specially designed "bird bullets" that simulate the weight and density of real birds. The bird bullets are shot into the running engine at high speed by air cannons or compressed gas devices.

[0003] In existing bird body launching tests, high-pressure gas in the air cannon propels the bird body-loaded shell carrier forward to accelerate, the shell carrier separates from the projectile at the cannon mouth separator, and the bird body moving in a straight line along the horizontal direction can be accurately launched to the designated position.

[0004] The bird ingestion test requirements for high-power turbo engines are as follows: 1. Extremely high launch frequency and quality: 5 small birds weighing 80g-100g are launched continuously within 1s; 2. Extremely high launch speed: the muzzle velocity of each small bird needs to reach 350km / h to simulate the take-off / approach speed of an airplane; 3. Extremely high timing accuracy: the "time window" between each propeller blade of the engine is extremely short, and the control system must ensure that each small bird is launched at an extremely accurate time to accurately pass through the plane of the high-speed rotating propeller and enter the engine inlet, rather than hitting the propeller blade, and a single error will cause the propeller and engine to be damaged, resulting in test failure; 4. Trajectory consistency: the trajectories of the 5 small birds must have high consistency to ensure that they all enter the inlet through the preset path.

[0005] However, existing bird ingestion test gas cannons mostly use single-cannon sequential triggering or simple multi-cannon parallel control methods. Single-cannon sequential triggering control refers to using a complex mechanical loading mechanism (such as a rotating shell magazine and a push rod system) to continuously load and launch multiple bird bullets into the same cannon tube within a very short time. This method has the following disadvantages when applied to bird ingestion tests for high-power turbo engines: 1. Mechanical limit: the movement speed of mechanical structures has a physical upper limit, and it is almost impossible to complete 5 high-reliability loading, sealing and launching within 1s, which is prone to jamming, impact or sealing failure; 2. Pressure fluctuation: the same gas tank continuously releases high-pressure gas in a short time, the pressure in the bore cannot be quickly stabilized, resulting in a significant decrease in the muzzle velocity of subsequent shells, which cannot guarantee the consistency of the speed of five bird shells; 3. Single 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; Multi-cannon parallel control refers to using multiple independent gas cannons, each cannon preloaded with a bird shell, triggered by a master control signal to fire simultaneously or with a fixed delay. In the application of bird swallowing test for high-power turboprop engines, the following shortcomings exist: 1. Synchronization error: factors such as response time of each quick-opening valve, slight pressure difference of each gas tank, and friction coefficient difference of each cannon, can cause milliseconds (ms) error in each cannon firing. This error is fatal to a 1020 RPM propeller, enough to make the bird hit the blade instead of entering the gap between the blades; 2. Wake interference: even if five cannons fire simultaneously, the first fired bird shell will form a shock wave at the muzzle, disturbing the trajectory of the subsequent muzzle bird shell ("wake" effect), causing trajectory divergence and subsequent bird shell deviation from the intended trajectory; 3. Heavy control system: five independent high-pressure gas sources and firing systems are very heavy, difficult to adjust and calibrate.

[0006] In summary, the existing technology cannot meet the extreme requirements of firing density, speed, accuracy, and consistency in bird swallowing tests for high-power turboprop engines, and cannot guarantee the reliability, repeatability, and safety of the test.

[0007] Note that the disclosure of the above background art is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present patent application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0008] The present application provides a turboprop engine whole machine bird swallowing test device to solve the technical problem that the existing bird swallowing test cannot meet the extreme requirements of firing density, speed, accuracy, and consistency in bird swallowing tests for high-power turboprop engines, and the test risk is high, the reliability, repeatability, and safety are low.

[0009] According to one aspect of the present application, there is provided a whole engine bird ingestion test device for a turboprop engine, comprising an air cannon launching assembly, a propeller phase sensing assembly, a muzzle visual measurement assembly and a control assembly, the air cannon launching assembly comprising an air source for providing a launching power source, N control valves connected to the air source and the control assembly respectively, and N launching mechanisms connected to the control valves respectively, N being an integer greater than 1, the launching mechanisms and the control valves being arranged in one-to-one correspondence, the propeller phase sensing assembly being connected to the control assembly for measuring the phase of the propeller and transmitting a phase signal to the control assembly, the control assembly being configured to calculate a theoretical launching time according to the phase signal and pre-store response deviation times of the N control valves, and further set a difference between the theoretical launching time and the response deviation times as an actual trigger time of the control valves, the muzzle visual measurement assembly being connected to the control assembly for calculating the muzzle velocity and launching angle of the bird bomb after launching and transmitting a signal to the control assembly, and the control assembly being configured to correct the launching pressure, launching time and launching angle of the subsequent bird bomb according to the muzzle velocity and launching angle of the first bird bomb after launching.

[0010] As a further improvement of the above technical solution: Further, the air source comprises an air compressor, a high-pressure gas cylinder for storing high-pressure gas connected to the air compressor, a pressure reducing valve connected to the high-pressure gas cylinder, an inflation valve connected to the pressure reducing valve, and a gas storage shell connected to the inflation valve and the control valve respectively.

[0011] Further, the gas storage shell comprises a gas storage chamber and a control gas chamber, the pressure of the control gas chamber being higher than that of the gas storage chamber.

[0012] Further, the control assembly comprises a controller connected to the propeller phase sensing assembly and the muzzle visual measurement assembly respectively, and a control box connected to the controller, the inflation valve and the control valve respectively.

[0013] Further, the control assembly further comprises a pressure sensor arranged on the gas storage shell and connected to the control box for monitoring the internal gas pressure of the gas storage shell.

[0014] Further, the control assembly further comprises a gas release valve connected to the control box and the gas storage shell respectively for adjusting the internal gas pressure of the gas storage shell in cooperation with the inflation valve.

[0015] Further, the test device further comprises a mounting base, a first height adjusting support arranged on the mounting base and connected to the gas storage shell for adjusting the height of the gas storage shell, and a second height adjusting support arranged on the mounting base and connected to the launching mechanism for adjusting the height of the launching mechanism.

[0016] Further, the propeller phase sensing assembly comprises a laser phase sensor arranged in front of the output shaft of the test engine.

[0017] Further, the muzzle visual measurement assembly comprises M measurement cameras arranged in front of the projectile component, the frame rate of the measurement camera is greater than or equal to 10000 fps, and M is a positive integer.

[0018] Further, the projectile component comprises a loading mechanism connected with the control valve, a barrel connected with the loading mechanism, and a cartridge support separator arranged on the launching end of the barrel.

[0019] The present application has the following beneficial effects: The turbo-propeller engine whole-machine bird swallowing test device has the following beneficial effects: the phase signal is transmitted to the control assembly by measuring the phase of the propeller through the propeller phase sensing assembly, the control assembly calculates the theoretical launching time according to the phase signal, and the response deviation time of N control valves is stored in advance, so that the difference between the theoretical launching time and the response deviation time is set as the actual triggering time of the control valve, the inherent error of the hardware is offset by actively introducing the compensation amount, and the launching accuracy of the N birds is improved; the air cannon launching assembly provides a launching power source through the air source, and then controls the working of the corresponding projectile component through the N control valves, so that the N birds are launched within a set time, the air source consistency and the high-speed shooting of multiple cannons are considered, and the test requirements of the launching density and the launching speed are met; after the reflection of the first bird, the muzzle visual measurement assembly calculates the muzzle velocity and the launching angle of the first bird after launching and transmits the signal to the control assembly, and the control assembly corrects the launching pressure, the launching time and the launching angle of the subsequent birds according to the muzzle velocity and the launching angle of the first bird after launching, so as to actively cope with uncertain influences such as pressure fluctuation, bird individual difference and tail flow disturbance, and the launching consistency of the N birds is improved; the launching accuracy of the birds is improved by using the time delay compensation cooperative triggering mechanism, the birds can accurately pass through the plane of the high-speed rotating propeller, the N birds of the set speed are launched within the set time by the fusion design of the centralized air source and the parallel barrel, the trajectory consistency of the birds meets the requirements by real-time trajectory correction; compared with the prior art, the extreme requirements of the launching density, the speed, the accuracy and the consistency of the high-power turbo-propeller engine bird swallowing test are met, the test risk is greatly reduced, the reliability, the repeatability and the safety are improved, the practicality is high, and the present application is suitable for wide promotion and application.

[0020] In addition to the objects, features, and advantages described above, the present application has other objects, features and advantages. The present application will be described in further detail below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0021] The accompanying drawings, which form a part of the present application, are included to provide a further understanding of the application, and are incorporated herein for purposes of explanation, but are not intended to limit the present application. In the drawings: Figure 1Fig. 1 is a structural schematic diagram of a whole engine bird ingestion test device of a turboprop engine according to a preferred embodiment of the present application.

[0022] Legend: 10, air cannon launching assembly; 11, high-pressure gas cylinder; 12, pressure reducing valve; 13, inflation valve; 14, gas storage shell; 15, control valve; 16, cartridge loading mechanism; 17, cannon barrel; 18, cartridge support separator; 21, measuring camera; 22, illuminating element; 30, control assembly; 31, controller; 32, control box; 33, pressure sensor; 34, gas release valve; 41, mounting base; 42, height adjustment support I; 43, height adjustment support II. DETAILED DESCRIPTION

[0023] The following description provides specific applications and requirements of the present specification, in order to enable a person skilled in the art to manufacture and use the contents of the present specification. Various partial modifications of the disclosed embodiments are obvious 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 the present specification. Therefore, the present specification is not limited to the embodiments shown, but is consistent with the widest scope of the claims.

[0024] The terms used herein are only for the purpose of describing specific example embodiments, and are not limiting. For example, unless the context clearly indicates otherwise, as used herein, the singular forms "a", "an", and "the" can also include the plural forms. When used in the present specification, the terms "comprise", "comprise" and / or "comprise" mean that the associated integers, steps, operations, elements and / or components exist, but do not exclude the presence of one or more other features, integers, steps, operations, elements, components and / or groups.

[0025] These features of the present specification and other features, as well as the operation and function of related elements of the structure, and the combination and economy of manufacture of components can be significantly improved in view of the following description. With reference to the drawings, all of which form part of the present specification. 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 the present specification. It should also be understood that the drawings are not drawn to scale.

[0026] As Figure 1As shown, the whole engine bird swallowing test device of the turboprop engine of the embodiment comprises an air cannon launching assembly 10, a propeller phase sensing assembly (not shown in the figure), a muzzle visual measurement assembly and a control assembly 30. The air cannon launching assembly 10 comprises an air source for providing a launching power source, control valves 15 connected with the air source and the control assembly 30 respectively, and launching elements for launching bird bullets connected with the control valves 15. The control valves 15 are provided with N, N is an integer greater than 1. The launching elements and the control valves 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 pre-storing the response deviation time of the N control valves 15. 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 launching angle after the bird bullet is launched and transmitting the signal to the control assembly 30. The control assembly 30 is used for correcting the launching pressure, the launching time and the launching angle of the subsequent bird bullets according to the muzzle velocity and the launching angle after the first bird bullet is launched.

[0027] As Figure 1As shown, specifically, the whole swallowing bird test device of the turbo-prop engine of the present application firstly measures the propeller phase through the propeller phase sensing assembly to transmit the phase signal to the control assembly 30, the control assembly 30 calculates the theoretical launch time according to the phase signal, and pre-stores the response deviation time of the N control valves 15, and then sets the difference between the theoretical launch time and the response deviation time as the actual trigger time of the control valve 15, and the inherent error of the hardware is offset by actively introducing the compensation amount, thereby improving the launch accuracy of the N bird bullets; the air cannon launch assembly 10 provides a launch power source through the air source, and then controls the corresponding launch components through the N control valves 15 respectively, so as to launch the N bird bullets within the set time, taking into account the air source consistency and the high-speed shooting of multiple cannons, and meeting the test requirements of launch density and launch speed; after the reflection of the first bird bullet, the muzzle visual measurement assembly calculates the muzzle velocity and launch angle of the first bird bullet after launch and transmits the signal to the control assembly 30, and the control assembly 30 corrects the launch pressure, launch time and launch angle of the subsequent bird bullets according to the muzzle velocity and launch angle of the first bird bullet after launch, actively coping with uncertain influences such as pressure fluctuation, bird bullet individual difference and wake disturbance, and improving the launch consistency of the N bird bullets; the present scheme improves the launch accuracy of the bird bullets through the use of the "time delay compensation" cooperative trigger mechanism, ensures that the bird bullets can accurately pass through the plane of the high-speed rotating propeller, realizes the launch of the N bird bullets at the set speed within the set time through the fusion design of "centralized air source + parallel cannon barrel 17", and ensures that the trajectory consistency of the bird bullets meets the requirements through real-time trajectory correction; compared with the prior art, the present scheme meets the extreme requirements of launch density, speed, accuracy and consistency of the high-power turbo-prop engine swallowing bird test, greatly reduces the test risk, improves the reliability, repeatability and safety, has strong practicality, and is suitable for wide promotion and application.

[0028] Optionally, the control valve 15 is an electromagnetic valve or a piezoelectric valve with a response time less than 1 ms.

[0029] It should be understood that the set time, the set speed and N can be adaptively set according to the test requirements, and in an embodiment, 5 bird bullets at 350 km / h are launched within 1S.

[0030] It should be understood that the launch density refers to the launch of a set number of bird bullets within a set time.

[0031] As Figure 1As shown, in the 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 works to fill the high-pressure gas cylinder 11 with compressed air at a set pressure, and after the pressure reducing valve 12 reduces and stabilizes the pressure, the compressed air is delivered to the gas storage shell 14 through the inflation valve 13, so that when the swallow bird test is performed, the control valve 15 is triggered to drive the bird bomb out by the compressed air, and the launch speed is positively correlated with the pressure of the compressed air. By ensuring the stability and accuracy of the pressure of the compressed air, the launch speed of the N bird bombs can be ensured to be stable and accurate.

[0032] As shown in the embodiment, the control assembly 30 includes a controller 31 connected to the propeller phase sensing assembly and the muzzle visual measurement assembly respectively, and a control box 32 connected to the controller 31, the inflation valve 13 and the control valve 15 respectively. Specifically, the controller 31 receives the phase signal transmitted by the propeller phase sensing assembly and the image signal transmitted by the muzzle visual measurement assembly, and controls the inflation valve 13 and the control valve 15 to work through the control box 32, so that when the inflation valve 13 is opened and reaches a set pressure, the control valve 15 starts the swallow bird test; after the first bird bomb is launched, and the muzzle velocity is lower than the set value, the trigger time of the subsequent valve is advanced to correct the launch time and improve the launch accuracy. Figure 1 As shown in the embodiment, the control assembly 30 further includes a pressure sensor 33 arranged on the gas storage shell 14 and connected to the control box 32 for monitoring the internal gas pressure of the gas storage shell 14. Specifically, the controller 31 ensures that the control valve 15 starts the swallow bird test only after reaching a set pressure by monitoring the internal gas pressure of the gas storage shell 14 through the pressure sensor 33, so as to ensure the accuracy of the launch speed.

[0033] Figure 1 As shown in the embodiment, the control assembly 30 further includes a pressure sensor 33 arranged on the gas storage shell 14 and connected to the control box 32 for monitoring the internal gas pressure of the gas storage shell 14. Specifically, the controller 31 ensures that the control valve 15 starts the swallow bird test only after reaching a set pressure by monitoring the internal gas pressure of the gas storage shell 14 through the pressure sensor 33, so as to ensure the accuracy of the launch speed.

[0034] Optionally, the controller 31 is a computer loaded with control software.

[0035] As shown in the embodiment, the control assembly 30 further includes a pressure sensor 33 arranged on the gas storage shell 14 and connected to the control box 32 for monitoring the internal gas pressure of the gas storage shell 14. Specifically, the controller 31 ensures that the control valve 15 starts the swallow bird test only after reaching a set pressure by monitoring the internal gas pressure of the gas storage shell 14 through the pressure sensor 33, so as to ensure the accuracy of the launch speed. Figure 1 As shown in the embodiment, the control assembly 30 further includes a pressure sensor 33 arranged on the gas storage shell 14 and connected to the control box 32 for monitoring the internal gas pressure of the gas storage shell 14. Specifically, the controller 31 ensures that the control valve 15 starts the swallow bird test only after reaching a set pressure by monitoring the internal gas pressure of the gas storage shell 14 through the pressure sensor 33, so as to ensure the accuracy of the launch speed.

[0036] Figure 1 ​​As shown, in the embodiment, 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 cooperating with the gas charging valve 13 to adjust the internal air pressure of the gas storage shell 14. Specifically, the compressed air in the gas storage shell 14 can be discharged through the gas release valve 34, and then cooperating with the gas charging valve 13 to adjust the internal air pressure of the gas storage shell 14, so as to realize the precise control of the launch speed; after the first bird bomb is launched, the internal air pressure of the gas storage shell 14 is adjusted through the gas release valve 34 and the gas charging valve 13, so as to realize the correction of the launch pressure, thereby ensuring that the launch speed meets the test requirements.

[0037] As shown in the figure, Figure 1 In the embodiment, 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, and a height adjusting support two 43 arranged on the mounting base 41 and connected with the launching component. Specifically, the angle correction includes pitch angle correction, and the pitch angle of the launching component can be adjusted through the cooperation of the height adjusting support one 42 and the height adjusting support two 43, so as to realize the correction of the pitch angle.

[0038] Optionally, the angle correction also includes yaw angle correction, and the launching component is connected with the control valve 15 through the flange, and the flange can be used to realize the fine adjustment of the yaw angle and realize the yaw angle correction.

[0039] In the embodiment, the propeller phase sensing assembly comprises a laser phase sensor for mounting in front of the output shaft of the test engine. Specifically, the rotation angle (phase) of the propeller is measured in real time by the laser phase sensor, and the 0-360° phase signal is sent to the control assembly 30 in the form of high-frequency pulse as the reference signal of the entire launch timing.

[0040] As shown in the figure, Figure 1 In the embodiment, the muzzle visual measurement assembly comprises M measurement cameras 21 arranged in front of the launching component, and the frame rate of the measurement camera 21 is ≥10000fps, and M is a positive integer. Specifically, the field of view of the M measurement cameras 21 covers the muzzle area. Once it is monitored that the bird bomb is shot out, the image is analyzed immediately, and the actual muzzle velocity and launch angle of the first bird bomb are calculated. Optionally, the muzzle visual measurement assembly further comprises an illuminating part 22 used in cooperation with the M measurement cameras 21. Optionally, the illuminating part 22 is a led lamp.

[0041] As shown in the figure, Figure 1As shown, in the present embodiment, the launching device comprises a loading mechanism 16 connected with the control valve 15, a barrel 17 connected with the loading mechanism 16, and a cartridge separator 18 arranged on the launching end of the barrel 17. Specifically, before the test, the bird projectile is loaded into the cartridge of the loading mechanism 16, so that after the set pressure is reached and the actual trigger is actually triggered, the control assembly 30 triggers the control valve 15, the cartridge and the bird projectile are ejected in the barrel 17 under the action of compressed air, and the cartridge is separated from the bird projectile under the action of the cartridge separator 18, so that the bird projectile impacts the test piece at a set speed.

[0042] The foregoing description of specific embodiments of the disclosure has been presented. Other embodiments are within the scope of the following claims. In some cases, the actions or steps recited in the claims can be performed in a different order and still achieve desirable results. In addition, the processes depicted in the accompanying figures do not necessarily require the particular order shown, or sequential order, to achieve the desired results. In certain implementations, multitasking and parallel processing can be advantageous.

[0043] In light of the forgoing disclosure, those skilled in the art will appreciate that the foregoing detailed description of the present disclosure is made in an illustrative, and that the present disclosure is not limited to the embodiments described herein. Although specific configurations have been described herein, it will be understood by those skilled in the art that changes can be made to the embodiments described herein without departing from the spirit and scope of the present disclosure. Such changes are intended to be within the scope of the present disclosure.

[0044] In addition, certain terminology has been used to describe embodiments of the disclosure. For example, the terms "one embodiment" or "an embodiment" or "some embodiments" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the disclosure. Therefore, it is emphasized and should be appreciated that a use of these phrases in various places in the specification is not necessarily referring to the same embodiment. Further, the particular features, structures, or characteristics can be combined in any suitable manner in one or more embodiments without limitation.

[0045] It should be understood that, in the foregoing description of embodiments of the present specification, for purposes of simplicity of explanation, the present specification has combined a plurality of features in a single embodiment, drawing, or description of an embodiment. It is intended that the features combined in this way are not necessarily limited to the particular embodiment. Rather, the present specification envisions that a person of ordinary skill in the art could take the individual arrangements of the various features, and combine or arrange the individual features in a different way than the way the features are combined or arranged in the specific embodiments disclosed in the present specification, without departing from the scope of the present specification. That is, the embodiments of the present specification can be understood to include a plurality of combinations of the various features disclosed in the present specification, and the various combinations of the features are specifically contemplated by the present specification. Further, the present specification envisions that a person of ordinary skill in the art could take the individual arrangements of the various features, and combine or arrange the individual features in a different way than the way the features are combined or arranged in the specific embodiments disclosed in the present specification, without departing from the scope of the present specification.

[0046] Each patent, patent application, publication, and other material cited in this document is incorporated herein by reference in its entirety for all purposes. Except to the extent necessary or required to be inconsistent with this document as it presently exists, the incorporated material also can be incorporated for all purposes as it exists on the date of incorporation. To the extent that any meaning or definition of a term in this document conflicts with the meaning or definition of the same term in any incorporated material, the meaning or definition in this document prevails. To the extent the incorporated material contradicts any stated term of this document, such stated term controls.

[0047] Finally, it should be understood that the embodiments of the application disclosed herein are illustrative of the principles of the present specification. Other modifications that fall within the scope of the present specification can also be made to embodiments of the present specification. Accordingly, the disclosure of embodiments of the present specification is intended to be illustrative, but not limiting, of the scope of the application. Thus, it is intended that the present specification cover any modifications and variations of the application were within the scope of the applicant's disclosure.

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 to 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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