Aero-engine fan blade foreign object impact detection device

Abstract

This invention discloses a foreign object impact detection device for aero-engine fan blades, relating to the field of aero-engine performance testing technology. The technical solution includes a detection unit, a foreign object launching unit, and a linkage unit. The detection unit includes an electric conductor connector, a camera connector, a high-speed detection camera, and a controller connector. The foreign object launching unit includes a feeding mechanism, a low-speed launching mechanism, a high-speed launching mechanism, and a cylinder. The linkage unit can switch the connection between any launching mechanism and the cylinder. The cylinder can store energy for the connected launching mechanism. After storing energy, the low-speed and high-speed launching mechanisms can launch the material from the feeding mechanism. The linkage unit can synchronously drive the controller connector to reciprocate. Through its overall structural design, this invention can not only detect the impact of different impact velocities on fan blades but also provide more accurate detection results.

Description

Technical Field

[0001] This invention relates to the field of aero-engine performance testing technology, and more specifically to an aero-engine fan blade foreign object impact detection device. Background Technology

[0002] During high-speed operation, aero-engine fan blades are often exposed to the risk of impact from foreign objects such as birds, hail, and runway debris. The different impact speeds of these foreign objects can cause varying degrees of structural damage to the blades. Therefore, accurately simulating the impact process of foreign objects at different speeds and detecting the damage status of the blades in real time is a key technical aspect of assessing engine reliability.

[0003] Existing detection devices generally suffer from the following shortcomings: First, they have a single detection mode. In low-speed foreign object impact scenarios, they rely on traditional sensors for detection, while in high-speed impact scenarios, insufficient data acquisition frequency leads to the omission of key damage details. Second, foreign object launching mechanisms are mostly fixed power outputs, making it difficult to flexibly switch between low-speed and high-speed launching modes. Furthermore, the lack of a linkage mechanism between launching speed and detection mode easily leads to mismatches between the detection equipment and the impact conditions. Third, the coordinated control precision between the detection unit and the launching unit is insufficient. In low-speed detection, the high-frequency data from the high-speed camera wastes computing resources, while in high-speed detection, the low-frequency sampling of traditional sensors cannot capture transient impact signals, resulting in deviations in the detection results. Summary of the Invention

[0004] To address the shortcomings of existing technologies, the present invention aims to provide a foreign object impact detection device for aero-engine fan blades. The foreign object launching unit is equipped with low-speed and high-speed dual launching mechanisms and cylinders. The linkage unit can switch between any mechanism and cylinder for energy storage. By storing energy through the high-speed mechanism, more speed-graded launching can be achieved, meeting the simulation requirements of foreign object impacts at different speeds and facilitating the study of the impact of speed on the blades.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a detection unit, a foreign object launching unit, and a linkage unit. The detection unit includes a current collector connector, a camera connector, a high-speed detection camera, and a controller connector. The current collector connector is connected to a low-speed detection unit. The camera connector is electrically connected to the high-speed detection camera. The controller connector is located between the current collector connector and the camera connector, and is electrically connected to a controller. The foreign object launching unit includes a feeding mechanism, a low-speed launching mechanism, a high-speed launching mechanism, and a cylinder. The linkage unit can switch the connection between any launching mechanism and the cylinder. The cylinder can store energy for the connected launching mechanism. After storing energy, the low-speed and high-speed launching mechanisms can launch the material from the feeding mechanism. The linkage unit can synchronously drive the controller connector to reciprocate.

[0006] As a further improvement of the present invention, the detection unit further includes a motor, a fan shaft, and fan blades. The fan shaft is fixedly connected to the output end of the motor, and the fan blades are fixedly installed on the fan shaft. The low-speed detection unit includes a triaxial strain gauge, a slip ring actuator, and a strain acquisition device. The triaxial strain gauge is fixedly installed on the fan blades, the slip ring actuator is sleeved on the fan shaft, the triaxial strain gauge is connected to the rotor end of the slip ring actuator, and the stator end cable of the slip ring actuator is connected to the strain acquisition device.

[0007] As a further improvement of the present invention, the feeding mechanism includes a material cylinder, a push rod, a fixed ring, and a spring. A hopper is fixedly installed at the upper end of the material cylinder. The push rod passes through one end of the material cylinder. A sliding ring is fixedly installed on the push rod. The fixed ring is fixedly installed at one end inside the material cylinder. The spring is disposed between the sliding ring and the fixed ring, and the spring is sleeved on one end of the push rod. A branch rod is fixedly installed at the other end of the push rod. Dampers are fixedly installed at both ends of the branch rod.

[0008] As a further improvement of the present invention, the low-speed launching mechanism includes a launching tube, a push rod, a sliding ring, a spring, a limiting ring, and a sliding plate. The push rod passes through the launching tube, and the sliding ring and spring are both disposed inside the launching tube. The sliding ring is fixedly installed on one end of the push rod, and the spring is sleeved on the push rod. The limiting ring is fixedly installed on the other end of the push rod, and the sliding plate is slidably installed on the other end of the push rod. One end of the push rod is in contact with the extension end of any one of the dampers.

[0009] As a further improvement of the present invention, the high-speed launching mechanism includes a second launching tube, a third push rod, a piston, a second limiting ring, and a second sliding plate. The third push rod passes through the second launching tube, the piston is placed inside the second launching tube, and the piston is fixedly installed at one end of the third push rod. The second limiting ring is fixedly installed at the other end of the third push rod, and the second sliding plate is slidably installed at the other end of the third push rod. The second sliding plate is in contact with the first sliding plate. A barometer and an air nozzle are fixedly installed at the upper end of the second launching tube, and one end of the third push rod is in contact with the telescopic end of another damper.

[0010] As a further improvement of the present invention, an electric telescopic rod is fixedly installed on the telescopic end of the cylinder, and the ends of the sliding plate one and the sliding plate two that are in contact with each other are provided with grooves, and the two grooves are connected. The telescopic end of the electric telescopic rod is inserted into either groove.

[0011] As a further improvement of the present invention, the linkage unit includes a housing, a connecting rod, a pusher, a rack and pinion, and a gear. The connecting rod and rack are slidably mounted on the housing. The pusher is fixedly connected to the connecting rod and rack. The pusher is U-shaped. The two side plates of the pusher are respectively attached to the outer side of sliding plate 1 and the outer side of sliding plate 2. The gear is rotatably mounted on the housing and meshes with rack.

[0012] As a further improvement of the present invention, the linkage unit further includes a support platform, a second gear, a second rack, and a shift fork. The second gear is rotatably mounted on the support platform, the second rack is slidably mounted on the support platform, and the second gear meshes with the second rack. One end of the shift fork is fixedly connected to the second rack, and the other end of the shift fork is engaged in an annular groove opened in the middle of the controller connector plug. A first pulley is fixedly mounted on the upper end of the first gear, and a second pulley is fixedly mounted on the upper end of the second gear. The first pulley and the second pulley are connected by a belt.

[0013] As a further improvement of the present invention, the detection unit is covered with a protective shell, the high-speed detection camera is disposed diagonally above the fan blades, and the high-speed detection camera is fixedly installed in the upper part of the protective shell.

[0014] The beneficial effects of this invention are:

[0015] 1. The foreign object launching unit is equipped with low-speed and high-speed dual launching mechanisms and cylinders. The linkage unit can switch between any mechanism and cylinder to store energy. By storing energy through the high-speed mechanism, more speed-graded launching can be achieved, which can meet the simulation requirements of foreign object impact at different speeds and facilitate the study of the impact of speed on the blades.

[0016] 2. The detection unit is equipped with an electric conductor connection socket, a camera connection socket, and a controller connection plug. It can switch between a low-speed detection unit and a high-speed detection camera according to the foreign object's emission speed. Low-speed impacts are detected by an electric conductor, while high-speed impacts are detected by a high-speed camera, which can capture the impact process at different speeds and improve detection accuracy.

[0017] 3. The linkage unit synchronously drives the switching of detection mode and launch speed, ensuring that low-speed launch matches low-speed detection and high-speed launch corresponds to high-speed imaging, avoiding detection deviation caused by mode mismatch, realizing precise linkage between detection and launch. The overall structure is compact and flexible, and can efficiently simulate foreign object impacts in multiple scenarios, providing reliable data support for optimizing the impact resistance performance of fan blades and improving the safety of aero engines. Attached Figure Description

[0018] Figure 1 This is a three-dimensional structural schematic diagram of the foreign object impact detection device for aero-engine fan blades according to the present invention;

[0019] Figure 2 This is a cross-sectional structural diagram of the foreign object impact detection device for aero-engine fan blades according to the present invention;

[0020] Figure 3 This is a three-dimensional structural schematic diagram of the detection unit of the present invention;

[0021] Figure 4 for Figure 3 Enlarged view of point A in the middle;

[0022] Figure 5 This is a three-dimensional structural schematic diagram of the external object emission unit of the present invention;

[0023] Figure 6 This is a cross-sectional structural diagram of the feeding mechanism of the present invention;

[0024] Figure 7 This is a cross-sectional structural diagram of the low-speed launching mechanism of the present invention;

[0025] Figure 8 This is a cross-sectional structural diagram of the high-speed launch mechanism of the present invention;

[0026] Figure 9 This is a three-dimensional structural diagram of the linkage unit of the present invention.

[0027] Explanation of reference numerals in the attached drawings: 1. Detection unit; 101. Motor; 102. Fan shaft; 103. Fan blade; 104. Electromagnetic connector socket; 105. Camera connector socket; 106. High-speed detection camera; 107. Controller connector plug; 2. External object emission unit; 202. Feeding mechanism; 2021. Material cylinder; 2022. Hopper; 2023. Push rod one; 2024. Fixing ring; 2025. Sliding ring one; 2026. Spring one; 2027. Branch rod; 2028. Damper; 2036. Sliding plate one; 203. Low-speed emission mechanism; 2031. Emission tube one; 2032. Push rod two; 203 3. Sliding ring II; 2034. Spring II; 2035. Limiting ring I; 2036. Sliding plate I; 204. High-speed launching mechanism; 2041. Launch tube II; 2042. Push rod III; 2043. Piston; 2044. Limiting ring II; 2045. Sliding plate II; 2046. Barometer; 2047. Air nozzle; 205. Cylinder; 3. Linkage unit; 301. Housing; 302. Connecting rod; 303. Pushing component; 304. Rack I; 305. Gear I; 306. Pulley I; 307. Support platform; 308. Gear II; 309. Pulley II; 310. Rack II; 311. Actuating fork; 4. Protective outer shell. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of the embodiments of this disclosure clearer, the technical solutions of the embodiments of this disclosure will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this disclosure, and not all of them. The components of the embodiments of this disclosure described and shown herein can generally be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of this disclosure is not intended to limit the scope of the claimed disclosure, but merely represents selected embodiments of this disclosure. All other embodiments obtained by those skilled in the art based on the embodiments of this disclosure without inventive effort are within the scope of protection of this disclosure.

[0029] refer to Figures 1 to 5The diagram illustrates a specific embodiment of a foreign object impact detection device for an aero-engine fan blade according to the present invention. It includes a detection unit 1, a foreign object launching unit 2, and a linkage unit 3. The detection unit 1 includes a current collector connector 104, a camera connector 105, a high-speed detection camera 106, and a controller connector 107. The current collector connector 104 is connected to a low-speed detection unit, and the camera connector 105 is electrically connected to the high-speed detection camera 106. A protective housing 4 is fitted over the detection unit 1 to prevent the impacting object from being ejected and causing danger to the surrounding experimental environment. The high-speed detection camera 106 is positioned diagonally above the fan blade 103 and is fixedly installed within the upper part of the protective housing 4, enabling the high-speed detection camera 106 to clearly record the foreign object impact image and ensure the impact detection effect. The controller connector 107 is located between the conductor connector socket 104 and the camera connector socket 105, and is electrically connected to the controller. When the controller connector 107 is connected to the conductor connector socket 104, the controller controls the low-speed detection unit to detect the foreign object impact process on the fan blades. When the controller connector 107 is connected to the camera connector socket 105, the controller controls the high-speed detection camera 106 to detect the foreign object impact process on the fan blades. Different detection modes are switched according to the different foreign object emission speeds to make the detection results more accurate. The foreign object launching unit 2 includes a feeding mechanism 202, a low-speed launching mechanism 203, a high-speed launching mechanism 204, and a cylinder 205. The linkage unit 3 can switch any launching mechanism to be connected to the cylinder 205. The cylinder 205 can store energy for the connected launching mechanism. After storing energy, the low-speed launching mechanism 203 and the high-speed launching mechanism 204 can launch the material in the feeding mechanism 202. The linkage unit 3 can switch either the low-speed launching mechanism 203 or the high-speed launching mechanism 204 as the power source for launching foreign objects. The high-speed launching mechanism 204 can store more energy than the low-speed launching mechanism 203. When the high-speed launching mechanism 204 is used as the power source, the foreign object launching speed is greater. In summary, the linkage unit 3 can switch the foreign object launching speed and can synchronously drive the controller connector 107 to move back and forth, that is, switch different detection modes. The low-speed detection mode is used to detect foreign objects launched at low speed, and the high-speed detection mode is used to detect foreign objects launched at high speed. This not only detects the impact of different impact speeds on the fan blades 103, but also makes the detection results more accurate.

[0030] The detection unit 1 further includes a motor 101, a fan shaft 102, and fan blades 103. The fan shaft 102 is fixedly connected to the output end of the motor 101, and the fan blades 103 are fixedly mounted on the fan shaft 102. The motor 101 drives the fan shaft 102 to rotate, causing the fan blades 103 to rotate at high speed, realistically replicating the actual operating conditions of the blades during flight. The low-speed detection unit includes a triaxial strain gauge, a slip ring actuator, and a strain acquisition device. The triaxial strain gauge is fixedly mounted on the fan blades 103, and the slip ring actuator is sleeved on the fan shaft 102. The triaxial strain gauge is connected to the rotor end of the slip ring actuator, and the stator cable of the slip ring actuator is connected to the strain acquisition device. The slip ring actuator adopts a low-friction conductive material and a sealed structure design, which can still stably transmit strain signals under high-speed rotation, avoiding the signal interruption or interference problems caused by rotation in traditional wired connections, ensuring the continuity and reliability of dynamic strain data, and improving the reliability of detection results.

[0031] In a further embodiment, such as Figure 6 As shown, the feeding mechanism 202 includes a material cylinder 2021, a push rod 2023, a fixing ring 2024, and a spring 2026. A hopper 2022 is fixedly installed at the upper end of the material cylinder 2021. The push rod 2023 passes through one end of the material cylinder 2021, and a sliding ring 2025 is fixedly installed on the push rod 2023. The fixing ring 2024 is fixedly installed at one end inside the material cylinder 2021. The spring 2026 is disposed between the sliding ring 2025 and the fixing ring 2026. Between 4, and the spring 2026 is sleeved on one end of the push rod 2023, and the other end of the push rod 2023 is fixedly installed with a branch rod 2027. Both ends of the branch rod 2027 are fixedly installed with dampers 2028. The material falls from the hopper 2022 into the cylinder 2021 and hits any one of the dampers 2028 to push the push rod 2023, causing the material to be launched. After the launch is completed, the push rod 2023 is reset under the action of the spring 2026, ready for the next launch.

[0032] In a further embodiment, such as Figure 7As shown, the low-speed launching mechanism 203 includes a launching tube 2031, a push rod 2032, a sliding ring 2033, a spring 2034, a limiting ring 2035, and a sliding plate 2036. The push rod 2032 passes through the launching tube 2031. The sliding ring 2033 and the spring 2034 are both disposed inside the launching tube 2031. The sliding ring 2033 is fixedly installed at one end of the push rod 2032, and the spring 2034 is sleeved on the push rod 2032. The limiting ring 2035 is fixedly installed at the other end of the push rod 2032. The sliding plate 2036... The other end of the push rod 2032 is slidably mounted. One end of the push rod 2032 is attached to the telescopic end of any one of the dampers 2028. When the push rod 2032 is pulled, the sliding ring 2033 acts on the spring 2034 and compresses it to complete the energy storage. When the push rod 2032 is released, the push rod 2032 resets under the action of the spring and hits the corresponding damper 2028, so that the push rod 2023 hits the material. Since the elastic potential energy that the spring can store is limited, the elastic potential energy of the spring is used as the material launch power. The launch speed that the material can reach is also limited. Therefore, the material is launched at a low speed here.

[0033] In a further embodiment, such as Figure 8 As shown, the high-speed launching mechanism 204 includes a second launching tube 2041, a third push rod 2042, a piston 2043, a second limiting ring 2044, and a second sliding plate 2045. The third push rod 2042 passes through the second launching tube 2041. The piston 2043 is placed inside the second launching tube 2041 and is fixedly installed at one end of the third push rod 2042. The second limiting ring 2044 is fixedly installed at the other end of the third push rod 2042. The second sliding plate 2045 is slidably installed at the other end of the third push rod 2042 and is in contact with a first sliding plate 2036. A barometer 2046 and an air nozzle 2047 are fixedly installed at the upper end of the second launching tube 2041. One end of the push rod 2042 is attached to the telescopic end of another damper 2028. Pulling the push rod 2042 causes the piston 2043 to move and compress the air in the launch tube 2041 to complete energy storage. When the push rod 2042 is released, it resets under air pressure and strikes the corresponding damper 2028, causing the push rod 2023 to strike the material. Compared with using a spring to store energy, the potential energy that compressed air can store is greatly increased, so the material launch speed can be greatly increased. The barometer 2046 is used to detect the air pressure in the launch tube 2041, and the air nozzle 2047 is used to adjust the air pressure in the launch tube 2041, thereby adjusting the material launch speed.

[0034] As a further improvement of the present invention, an electric telescopic rod is fixedly installed on the telescopic end of the cylinder 205. The sliding plate 2036 and the sliding plate 2045 are provided with grooves at their respective ends, and the two grooves are connected. The telescopic end of the electric telescopic rod is inserted into either groove. By synchronously pushing the sliding plate 2036 and the sliding plate 2045, the groove that matches the telescopic end of the electric telescopic rod is switched, thereby switching the launching mechanism connected to the telescopic end of the cylinder 205, thus completing the switching between high-speed launching and low-speed launching.

[0035] As a further improvement to the present invention, such as Figure 9 As shown, the linkage unit 3 includes a housing 301, a connecting rod 302, a pusher 303, a rack 304, and a gear 305. The connecting rod 302 and the rack 304 are slidably mounted on the housing 301. The pusher 303 is fixedly connected to the connecting rod 302 and the rack 304. The pusher 303 is U-shaped. The two side plates of the pusher 303 are respectively attached to the outer side of the sliding plate 2036 and the outer side of the sliding plate 2045. The gear 305 is rotatably mounted on the housing 301. The gear 305 meshes with the rack 304. By rotating the gear 305, the rack 304 can be moved, which can drive the pusher 303 to move, thereby pushing the sliding plate 2036 and the sliding plate 2045 to move synchronously, completing the switching between high-speed and low-speed launch.

[0036] The linkage unit 3 further includes a support platform 307, a second gear 308, a second rack 310, and a shift fork 311. The second gear 308 is rotatably mounted on the support platform 307, and the second rack 310 is slidably mounted on the support platform 307. The second gear 308 meshes with the second rack 310. One end of the shift fork 311 is fixedly connected to the second rack 310, and the other end of the shift fork 311 is engaged in an annular groove in the middle of the controller connector plug 107. A pulley 306 is fixedly mounted on the upper end of the first gear 305, and a pulley 309 is fixedly mounted on the upper end of the second gear 308. Wheel 1 306 and pulley 2 309 are connected by a belt. By rotating gear 2 308, rack 2 310 is driven to move. Rack 2 310 drives to move shift fork 311. Shift fork 311 drives controller connector 107 to move, so that controller connector 107 can switch from connecting to transmitter connector 104 to connecting to camera connector 105, that is, switch from low-speed detection mode to high-speed detection mode. Through the connection of pulley 1 306, pulley 2 309 and belt, gear 1 305 and gear 2 308 rotate synchronously, so that the switching of detection mode is synchronized with the switching of high and low speed transmission.

[0037] Finally, it should be noted that the above-described embodiments are merely specific implementations of this disclosure, used to illustrate the technical solutions of this disclosure, and not to limit it. The scope of protection of this disclosure is not limited thereto. Although this disclosure has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that any person skilled in the art can still modify or easily conceive of changes to the technical solutions described in the foregoing embodiments, or make equivalent substitutions for some of the technical features, within the scope of the technology disclosed in this disclosure; and these modifications, changes, or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this disclosure, and should all be covered within the scope of protection of this disclosure. Therefore, the scope of protection of this disclosure should be determined by the scope of the claims.

Claims

1. A foreign object impact detection device for aero-engine fan blades, comprising a detection unit (1), a foreign object launching unit (2), and a linkage unit (3), characterized in that: The detection unit (1) includes an electric conductor connector (104), a camera connector (105), a high-speed detection camera (106), and a controller connector (107). The electric conductor connector (104) is connected to a low-speed detection unit. The camera connector (105) is electrically connected to the high-speed detection camera (106). The controller connector (107) is located between the electric conductor connector (104) and the camera connector (105), and is electrically connected to a controller. The external object launching unit (2) includes a feeding mechanism (202), a low-speed launching mechanism (203), a high-speed launching mechanism (204), and a cylinder (205). The linkage unit (3) can switch any launching mechanism to be connected to the cylinder (205). The cylinder (205) can store energy for the connected launching mechanism. After the low-speed launching mechanism (203) and the high-speed launching mechanism (204) store energy, they can launch the material in the feeding mechanism (202). The linkage unit (3) can synchronously drive the controller connector plug (107) to move back and forth.

2. The foreign object impact detection device for aero-engine fan blades according to claim 1, characterized in that: The detection unit (1) also includes a motor (101), a fan shaft (102), and fan blades (103). The fan shaft (102) is fixedly connected to the output end of the motor (101), and the fan blades (103) are fixedly installed on the fan shaft (102). The low-speed detection unit includes a triaxial strain gauge, a slip ring actuator, and a strain acquisition device. The triaxial strain gauge is fixedly installed on the fan blades (103), and the slip ring actuator is sleeved on the fan shaft (102). The triaxial strain gauge is connected to the rotor end of the slip ring actuator, and the stator end cable of the slip ring actuator is connected to the strain acquisition device.

3. The foreign object impact detection device for aero-engine fan blades according to claim 1, characterized in that: The feeding mechanism (202) includes a material cylinder (2021), a push rod (2023), a fixing ring (2024), and a spring (2026). A hopper (2022) is fixedly installed at the upper end of the material cylinder (2021). The push rod (2023) passes through one end of the material cylinder (2021). A sliding ring (2025) is fixedly installed on the push rod (2023). The fixing ring (2024) is fixedly installed at one end inside the material cylinder (2021). The spring (2026) is located between the sliding ring (2025) and the fixing ring (2024), and the spring (2026) is sleeved on one end of the push rod (2023). A branch rod (2027) is fixedly installed at the other end of the push rod (2023). A damper (2028) is fixedly installed at both ends of the branch rod (2027).

4. The foreign object impact detection device for aero-engine fan blades according to claim 3, characterized in that: The low-speed launching mechanism (203) includes a launching tube (2031), a push rod (2032), a sliding ring (2033), a spring (2034), a limiting ring (2035), and a sliding plate (2036). The push rod (2032) passes through the launching tube (2031). The sliding ring (2033) and the spring (2034) are both located inside the launching tube (2031). (2033) is fixedly installed on one end of push rod two (2032), spring two (2034) is sleeved on push rod two (2032), limit ring one (2035) is fixedly installed on the other end of push rod two (2032), sliding plate one (2036) is slidably installed on the other end of push rod two (2032), and one end of push rod two (2032) is in contact with the telescopic end of any one of the dampers (2028).

5. The foreign object impact detection device for aero-engine fan blades according to claim 4, characterized in that: The high-speed launching mechanism (204) includes a second launching tube (2041), a third push rod (2042), a piston (2043), a second limiting ring (2044), and a second sliding plate (2045). The third push rod (2042) passes through the second launching tube (2041), the piston (2043) is placed inside the second launching tube (2041), and the piston (2043) is fixedly installed at one end of the third push rod (2042). The second limiting ring (2044) is... 44) The sliding plate 2 (2045) is fixedly installed at the other end of the push rod 3 (2042), and the sliding plate 2 (2045) is slidably installed at the other end of the push rod 3 (2042). The sliding plate 2 (2045) is in contact with the sliding plate 1 (2036). The upper end of the launching tube 2 (2041) is fixedly installed with a barometer (2046) and an air nozzle (2047). One end of the push rod 3 (2042) is in contact with the telescopic end of another damper (2028).

6. The foreign object impact detection device for aero-engine fan blades according to claim 5, characterized in that: An electric telescopic rod is fixedly installed on the telescopic end of the cylinder (205). The sliding plate one (2036) and the sliding plate two (2045) are both provided with grooves at their respective ends, and the two grooves are connected. The telescopic end of the electric telescopic rod is inserted into either groove.

7. The foreign object impact detection device for aero-engine fan blades according to claim 5, characterized in that: The linkage unit (3) includes a housing (301), a connecting rod (302), a pusher (303), a rack (304), and a gear (305). The connecting rod (302) and the rack (304) are slidably mounted on the housing (301). The pusher (303) is fixedly connected to the connecting rod (302) and the rack (304). The pusher (303) is U-shaped. The two side plates of the pusher (303) are respectively attached to the outer side of the sliding plate (2036) and the outer side of the sliding plate (2045). The gear (305) is rotatably mounted on the housing (301) and meshes with the rack (304).

8. The foreign object impact detection device for aero-engine fan blades according to claim 7, characterized in that: The linkage unit (3) further includes a support platform (307), a second gear (308), a second rack (310), and a shift fork (311). The second gear (308) is rotatably mounted on the support platform (307), and the second rack (310) is slidably mounted on the support platform (307). The second gear (308) meshes with the second rack (310). One end of the shift fork (311) is fixedly connected to the second rack (310), and the other end of the shift fork (311) is engaged in the annular groove opened in the middle of the controller connector plug (107). The upper end of the first gear (305) is fixedly mounted with a first pulley (306), and the upper end of the second gear (308) is fixedly mounted with a second pulley (309). The first pulley (306) and the second pulley (309) are connected by a belt.

9. The foreign object impact detection device for aero-engine fan blades according to claim 2, characterized in that: The detection unit (1) is covered with a protective shell (4), the high-speed detection camera (106) is located diagonally above the fan blade (103), and the high-speed detection camera (106) is fixedly installed in the upper part of the protective shell (4).

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