An aircraft engine thrust detection device

Abstract

The present invention relates to the technical field of aero-engines, and specifically discloses a thrust detection device for an aero-engine, including: a fixed bracket, both sides of the bottom of the fixed bracket are fixedly connected with socket rods, and one side of the surfaces of the two socket rods is slidably connected with mounting plates, and both sides of the surfaces of the two mounting plates are fixedly connected with mounting sleeves; through the settings of the mounting plates, the first electric telescopic rods, the assembly brackets, the first electric sliding rails and the arc-shaped clamping plates, the first electric telescopic rods drive the front-end assembly brackets to adjust, and the two groups of assembly brackets clamp the aero-engine from both sides. The first electric sliding rails drive the arc-shaped clamping plates on the surfaces to adjust, so as to clamp the aero-engine in a semi-circular shape by the cooperation of the assembly brackets and the arc-shaped clamping plates, and there are two groups of clamping mechanisms that are symmetrically arranged in pairs to stably clamp the aero-engine, thereby achieving the effect of clamping and limiting both sides of the aero-engine in a semi-circular shape.

Description

Technical Field

[0001] The present invention belongs to the technical field of aero-engines, and particularly relates to a thrust detection device for an aero-engine. Background Art

[0002] Aero-engine thrust detection devices are used to test and evaluate the thrust performance of aero-engines. These devices can simulate the working conditions of the engine under real flight conditions and measure parameters such as the magnitude of the generated thrust and thrust changes, which are of great significance for improving engine performance, optimizing engine design, and ensuring flight safety.

[0003] In the Chinese patent with the publication number CN109916635B, a thrust detection device for an aero-engine is mentioned, which relates to the technical field of aero-engines. It includes a base, a power mechanism is installed above the base, adjustment mechanisms are installed on both the left and right sides of the power mechanism, and a clamping mechanism is installed below the power mechanism. This aero-engine thrust detection device has the function of driving the threaded rod to rotate, can provide power conditions for adjustment, improves the overall practicability, has the advantage of automatic adjustment, achieves the effect of moving the fixing plate up and down, has the function of driving the up and down position adjustment of the engine, is more convenient for detecting the engine, has the advantage of easy adjustment, achieves the effect of moving the clamping plate left and right, has the function of clamping the engine by the clamping plate, has the advantage of good stability, and achieves the effect of driving the top plate to move up and down by the first electric push rod, and has the function of clamping the engine up and down.

[0004] However, the above technical solution clamps the aero-engine for convenient testing of the thrust of the aero-engine. During the use of this clamping device, although the aero-engine can be adjusted, the overall clamping device is relatively simple for testing the aero-engine. The aero-engine has a large volume, and single-position clamping is likely to cause shaking, affecting the thrust detection of the aero-engine. Therefore, it needs to be improved by the staff. Summary of the Invention

[0005] The purpose of the present invention is to provide a thrust detection device for an aero-engine to solve the problems raised in the above background art.

[0006] To achieve the above purpose, the present invention provides the following technical solutions:

[0007] A thrust detection device for an aero-engine, comprising:

[0008] A fixed bracket;

[0009] Both sides of the bottom of the fixed bracket are fixedly connected with socket rods. One side of the surfaces of the two socket rods is slidably connected with mounting plates, and both sides of the surfaces of the two mounting plates are fixedly connected with mounting sleeves;

[0010] One side of the inner wall of the mounting sleeve is fixedly connected with a first electric telescopic rod. The front end of the first electric telescopic rod is fixedly connected with an assembly bracket. Both the upper and lower sides of the surface of the assembly bracket are fixedly connected with first electric slide rails. The output ends of the first electric slide rails are slidably connected with arc-shaped clamping plates. The middle part of the back surface of the mounting sleeve is fixedly connected with a positioning plate. Both the upper and lower sides of the surface of the positioning plate are fixedly connected with telescopic brackets, and the front ends of the telescopic brackets are fixedly connected to the back surface of the assembly bracket.

[0011] Preferably, one side of the surface of one of the mounting plates is fixedly connected with a first servo motor. The output end of the first servo motor is equipped with a driving rod. The front end of the driving rod is fixedly connected with an arc-shaped lapping plate, and both ends of the arc-shaped lapping plate are respectively rotatably connected to the inner walls of the two mounting plates. One side of the inner walls of the two mounting plates is fixedly connected with a fifth electric telescopic rod. The front end of the fifth electric telescopic rod is fixedly connected with a sixth electric telescopic rod. The bottom end of the sixth electric telescopic rod is fixedly connected with a U-shaped bracket.

[0012] Preferably, both sides of the back surfaces of the two mounting plates are fixedly connected with socket frames. The inner walls of the socket frames are slidably connected with sliding steel pipes, and the top ends of the sliding steel pipes are fixedly connected to the bottom of the fixed bracket. One side of the top of the socket rod is fixedly connected with a connecting bracket. The middle part of the top of the connecting bracket is fixedly connected with a motor box. One side of the inner wall of the motor box is fixedly connected with a second servo motor. The output end of the second servo motor is equipped with a transmission rod. Both sides of the surface of the transmission rod are rotatably connected with transmission belts. One side of the inner walls of the two transmission belts is rotatably connected with a rotating wheel, and the surfaces of the transmission belts and the rotating wheels are both arranged on the inner wall of the connecting bracket.

[0013] Preferably, one side of the bottom of each of the two rotating wheels is fixedly connected with an adapter rod. The bottom end of the adapter rod is fixedly connected with a threaded rod. One side of the surface of the threaded rod is threadedly connected with a threaded collar, and one side of the threaded collar is fixedly connected to the surface of the mounting plate.

[0014] Preferably, one side of the bottom of the fixed bracket is fixedly connected with a mounting platform. The four peripheral parts of the bottom of the mounting platform are fixedly connected with support rods. The bottom ends of the support rods are fixedly connected with a fixed base. The middle part of the top of the fixed base is fixedly connected with an assembly frame. One side of the inner wall of the assembly frame is fixedly connected with a second electric slide rail. One side of the inner wall of the second electric slide rail is slidably connected with a sliding frame.

[0015] Preferably, one side of the top of the sliding frame is fixedly connected with an arc-shaped placing plate, and the bottom of the arc-shaped placing plate is arranged on the top of the installation platform. Both sides of the surface of the arc-shaped placing plate are fixedly connected with reinforcing rods, and the bottom ends of the two reinforcing rods are fixedly connected with rollers.

[0016] Preferably, connection sleeves are fixedly connected to the four peripheral parts of the top of the fixed base. On one side of the inner wall of each of the four connection sleeves, a second electric telescopic rod is fixedly connected. The bottom end of the second electric telescopic rod is fixedly connected with an anti-slip bottom plate, and the top of the anti-slip bottom plate is arranged at the bottom of the fixed base. Universal wheels are fixedly connected to the four peripheral parts of the bottom of the fixed base, and a control panel body is fixedly connected to one side of the top of the installation platform.

[0017] Preferably, a conical bracket is fixedly connected to one side of the top of the fixed bracket. One side of the bottom of the conical bracket is fixedly connected with a connection frame. On one side of the inner wall of the connection frame, a third electric telescopic rod is fixedly connected. The front end of the third electric telescopic rod is fixedly connected with a mounting frame. On one side of the inner wall of the mounting frame, a fourth electric telescopic rod is fixedly connected. The bottom end of the fourth electric telescopic rod is fixedly connected with a thrust meter.

[0018] Preferably, a lapping bracket is fixedly connected to one side of the top of the fixed bracket. A fuel supply pipe is fixedly connected to one side of the top of the lapping bracket. An ignition control line is fixedly connected to the middle of the top of the lapping bracket. A speed regulation line is fixedly connected to the other side of the top of the lapping bracket.

[0019] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0020] (1) Through the settings of the mounting plate, the first electric telescopic rod, the assembly bracket, the first electric slide rail and the arc-shaped clamping plate, the first electric telescopic rod drives the adjustment of the front-end assembly bracket. The two groups of assembly brackets clamp the aero-engine from both sides. The first electric slide rail drives the adjustment of the arc-shaped clamping plate on its surface. Thus, the aero-engine is clamped in a semi-circular shape by the cooperation of the assembly bracket and the arc-shaped clamping plate. And there are two groups of symmetric clamping mechanisms to stably clamp the aero-engine, so as to achieve the effect of semi-circular clamping and limiting on both sides of the aero-engine.

[0021] (2) Through the settings of the first servo motor, drive rod, arc-shaped lapping plate, fifth electric telescopic rod, sixth electric telescopic rod and U-shaped bracket, the output end of the first servo motor drives the drive rod to rotate, and the drive rod drives the arc-shaped lapping plate at the front end to rotate. The arc-shaped lapping plate is sleeved on the bottom or tail end of the clamped aero-engine to provide stable thrust detection for the aero-engine. The front end of the fifth electric telescopic rod drives the sixth electric telescopic rod to adjust, and the sixth electric telescopic rod drives the U-shaped bracket at the bottom to adjust the height. By adjusting the position of the U-shaped bracket, the bottom of the clamped aero-engine is supported to facilitate maintaining the stability of the aero-engine, thus achieving the effect of supporting the bottom and tail end clamping position of the clamped aero-engine.

[0022] (3) Through the settings of the socket rod, second servo motor, transmission belt, rotating wheel, threaded rod, threaded sleeve ring and mounting plate, the output end of the second servo motor drives the transmission rod to rotate, the transmission rod drives the two transmission belts on the surface to rotate, both transmission belts drive the rotating wheels on one side of the inner wall to rotate, both rotating wheels drive the connecting rod at the bottom to rotate, the connecting rod drives the threaded rod at the bottom to rotate, the threaded rod drives the threaded sleeve ring connected to its surface to adjust the height, and the threaded sleeve ring drives the mounting plate on its surface to adjust the height, thereby finely adjusting the clamped aero-engine, thus achieving the effect of finely adjusting the height of the aero-engine.

[0023] (4) Through the settings of the second electric slide rail, arc-shaped placement plate, second electric telescopic rod and anti-slip bottom plate, the second electric slide rail drives the sliding frame slidingly connected to the inner wall to move, the sliding frame drives the arc-shaped placement plate at the top to move, and rollers are provided on one side of the arc-shaped placement plate through two reinforcing rods, thereby maintaining the stability of the arc-shaped placement plate. The staff places the space engine on the arc-shaped placement plate, and the arc-shaped placement plate moves horizontally to move the space engine to the detection position to facilitate the rapid clamping of the space engine by the clamping device. After the detection is completed, the space engine can be moved out, which is convenient for the staff to take out and convey later. And the second electric telescopic rod drives the anti-slip bottom plate at the bottom to adjust the height. Thus, when detecting the space engine, the anti-slip bottom plate contacts the ground, thereby improving the stability of the overall fixing device and ensuring the stability of the space engine thrust detection, thus achieving the effect of convenient conveying and maintaining stability of the space engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is a three-dimensional view of the present invention;

[0025] Figure 2 is a three-dimensional view of the threaded rod of the present invention;

[0026] Figure 3 is a three-dimensional view of the thrust gauge of the present invention;

[0027] Figure 4 is a three-dimensional view of the arc-shaped clamping plate of the present invention;

[0028] Figure 5 is a perspective view of the anti-slip bottom plate of the present invention;

[0029] Figure 6 is a perspective view of the second electric slide rail of the present invention;

[0030] Figure 7 is a perspective view of the lapping bracket of the present invention;

[0031] In the figure: 1, fixed bracket; 2, socket rod; 3, mounting plate; 4, mounting sleeve; 5, first electric telescopic rod; 6, assembly bracket; 7, first electric slide rail; 8, arc-shaped clamping plate; 9, first servo motor; 10, driving rod; 11, arc-shaped lapping plate; 12, connecting bracket; 13, motor box; 14, second servo motor; 15, transmission rod; 16, transmission belt; 17, rotating wheel; 18, connecting rod; 19, threaded rod; 20, threaded collar; 21, mounting platform; 22, support rod; 23, fixed base; 24, assembly frame; 25, second electric slide rail; 26, sliding frame; 27, arc-shaped placing plate; 28, reinforcing rod; 29, roller; 30, connecting sleeve; 31, second electric telescopic rod; 32, anti-slip bottom plate; 33, universal wheel; 34, control panel body; 35, conical bracket; 36, connecting frame; 37, third electric telescopic rod; 38, mounting frame; 39, fourth electric telescopic rod; 40, thrust gauge; 41, lapping bracket; 42, fuel supply pipe; 43, ignition control line; 44, speed regulation line; 45, fifth electric telescopic rod; 46, sixth electric telescopic rod; 47, U-shaped bracket; 48, positioning plate; 49, telescopic bracket; 50, socket frame; 51, sliding steel pipe. Detailed implementation manners

[0032] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0033] Embodiment 1:

[0034] Please refer to Figures 1 to 7 as shown, an aircraft engine thrust detection device includes:

[0035] fixed bracket 1;

[0036] Both sides of the bottom of the fixed bracket 1 are fixedly connected with socket rods 2. One side of the surfaces of the two socket rods 2 is slidably connected with mounting plates 3. Both sides of the surfaces of the two mounting plates 3 are fixedly connected with mounting sleeves 4. One side of the inner wall of the mounting sleeve 4 is fixedly connected with a first electric telescopic rod 5. The front end of the first electric telescopic rod 5 is fixedly connected with an assembly bracket 6. Both the upper and lower sides of the surface of the assembly bracket 6 are fixedly connected with first electric slide rails 7. The output end of the first electric slide rail 7 is slidably connected with an arc-shaped clamping plate 8. The middle of the back of the mounting sleeve 4 is fixedly connected with a positioning plate 48. Both the upper and lower sides of the surface of the positioning plate 48 are fixedly connected with telescopic brackets 49, and the front ends of the telescopic brackets 49 are fixedly connected to the back of the assembly bracket 6.

[0037] During use, mounting plates 3 are arranged on both sides of the bottom of the fixed bracket 1 through socket rods 2. Two mounting sleeves 4 are arranged on one side of each of the two mounting plates 3. The inner walls of the four mounting sleeves 4 are all provided with first electric telescopic rods 5. The staff connects the first electric telescopic rods 5 to the power supply. The first electric telescopic rods 5 drive the assembly brackets 6 at the front ends to adjust. The aero-engine is clamped from both sides by the two groups of assembly brackets 6. First electric slide rails 7 are arranged on both the upper and lower sides of the inner wall of the assembly bracket 6. The staff connects the first electric slide rails 7 to the power supply. The first electric slide rails 7 drive the arc-shaped clamping plates 8 on the surfaces to adjust. Thus, the aero-engine is clamped in a semi-circular shape by the cooperation of the assembly bracket 6 and the arc-shaped clamping plate 8. And two groups of symmetric clamping mechanisms are provided to stably clamp the aero-engine, so that the two clamping devices clamp and limit the left and right sides and the upper and lower sides of the aero-engine. Two telescopic brackets 49 are arranged on the back of the mounting sleeve 4 through a positioning plate 48. The front ends of the telescopic brackets 49 are arranged on the back of the assembly bracket 6. Thus, the stable movement of the assembly bracket 6 is ensured.

[0038] Embodiment 2:

[0039] Please refer to Figures 1 to 7 As shown, a first servo motor 9 is fixedly connected to one side of the surface of one of the mounting plates 3. A driving rod 10 is installed at the output end of the first servo motor 9. The front end of the driving rod 10 is fixedly connected with an arc-shaped overlapping plate 11. The two ends of the arc-shaped overlapping plate 11 are respectively rotatably connected to the inner walls of the two mounting plates 3. A fifth electric telescopic rod 45 is fixedly connected to one side of the inner walls of the two mounting plates 3. The front end of the fifth electric telescopic rod 45 is fixedly connected with a sixth electric telescopic rod 46. The bottom end of the sixth electric telescopic rod 46 is fixedly connected with a U-shaped bracket 47.

[0040] On one side of one of the mounting plates 3, a first servo motor 9 is provided. The staff connects the first servo motor 9 to the power supply. The output end of the first servo motor 9 drives the driving rod 10 to rotate. The driving rod 10 drives the arc-shaped lapping plate 11 at the front end to rotate. The arc-shaped lapping plate 11 sleeves the bottom or the tail end of the clamped aeroengine to provide stable thrust detection for the aeroengine. And on the inner walls of the two mounting plates 3, fifth electric telescopic rods 45 are provided. The staff connects the fifth electric telescopic rods 45 to the power supply. The front ends of the fifth electric telescopic rods 45 drive the sixth electric telescopic rods 46 to adjust. The staff connects the sixth electric telescopic rods 46 to the power supply. The sixth electric telescopic rods 46 drive the U-shaped brackets 47 at the bottom ends to adjust the height. By adjusting the positions of the U-shaped brackets 47, the bottom of the clamped aeroengine is supported to facilitate maintaining the stability of the aeroengine.

[0041] Embodiment 3:

[0042] Please refer to Figures 1 to 7 As shown in the figure, on both sides of the back surfaces of the two mounting plates 3, socket frames 50 are fixedly connected. A sliding steel pipe 51 is slidably connected to the inner wall of the socket frame 50. And the top end of the sliding steel pipe 51 is fixedly connected to the bottom of the fixed bracket 1. On one side of the top of the socket rod 2, a connecting bracket 12 is fixedly connected. In the middle of the top of the connecting bracket 12, a motor box 13 is fixedly connected. On one side of the inner wall of the motor box 13, a second servo motor 14 is fixedly connected. A transmission rod 15 is installed at the output end of the second servo motor 14. On both sides of the surface of the transmission rod 15, transmission belts 16 are rotatably connected. On one side of the inner walls of the two transmission belts 16, rotating wheels 17 are rotatably connected. And the surfaces of the transmission belts 16 and the rotating wheels 17 are arranged on the inner wall of the connecting bracket 12. On one side of the bottom of the two rotating wheels 17, connecting rods 18 are fixedly connected. The bottom end of the connecting rod 18 is fixedly connected to a threaded rod 19. A threaded sleeve ring 20 is threadedly connected to one side of the surface of the threaded rod 19. And one side of the threaded sleeve ring 20 is fixedly connected to the surface of the mounting plate 3.

[0043] During use, at the top ends of the two socket rods 2, a connecting bracket 12 is provided. At the top of the connecting bracket 12, a second servo motor 14 is provided through the motor box 13. The staff connects the second servo motor 14 to the power supply. The output end of the second servo motor 14 drives the transmission rod 15 to rotate. The transmission rod 15 drives the two transmission belts 16 on the surface to rotate. The two transmission belts 16 both drive the rotating wheels 17 on one side of the inner walls to rotate. The two rotating wheels 17 both drive the connecting rods 18 at the bottom to rotate. The connecting rods 18 drive the threaded rods 19 at the bottom ends to rotate. The threaded rods 19 drive the threaded sleeve rings 20 threadedly connected to the surfaces to adjust the height. The threaded sleeve rings 20 drive the mounting plates 3 on the surfaces to adjust the height, thereby finely adjusting the clamped aeroengine. And on both sides of the back surface of the mounting plate 3, socket frames 50 are provided. In the inner walls of the socket frames 50, sliding steel pipes 51 are slidably connected, thereby facilitating ensuring the stable adjustment of the height of the mounting plate 3.

[0044] Example 4:

[0045] Please refer to Figures 1 to 7 As shown, on one side of the bottom of the fixed bracket 1, there is a fixedly connected mounting platform 21. At the four surrounding locations of the bottom of the mounting platform 21, there are fixedly connected support rods 22. The bottom ends of the support rods 22 are fixedly connected with a fixed base 23. In the middle of the top of the fixed base 23, there is a fixedly connected assembly frame 24. On one side of the inner wall of the assembly frame 24, there is a fixedly connected second electric slide rail 25. On one side of the inner wall of the second electric slide rail 25, there is a slidably connected sliding frame 26. On one side of the top of the sliding frame 26, there is a fixedly connected arc-shaped placement plate 27, and the bottom of the arc-shaped placement plate 27 is arranged on the top of the mounting platform 21. On both sides of the surface of the arc-shaped placement plate 27, there are fixedly connected reinforcement rods 28. The bottom ends of the two reinforcement rods 28 are both fixedly connected with rollers 29. At the four surrounding locations of the top of the fixed base 23, there are fixedly connected connecting sleeves 30. On one side of the inner wall of each of the four connecting sleeves 30, there is a fixedly connected second electric telescopic rod 31. The bottom end of the second electric telescopic rod 31 is fixedly connected with an anti-slip bottom plate 32, and the top of the anti-slip bottom plate 32 is arranged at the bottom of the fixed base 23. At the four surrounding locations of the bottom of the fixed base 23, there are fixedly connected universal wheels 33. On one side of the top of the mounting platform 21, there is a fixedly connected control panel body 34.

[0046] During use, on the top of the fixed base 23, there is a second electric slide rail 25 arranged through the assembly frame 24. The staff connects the second electric slide rail 25 to the power supply. The second electric slide rail 25 drives the sliding frame 26 slidably connected to its inner wall to move. The sliding frame 26 drives the arc-shaped placement plate 27 at the top to move. And on one side of the arc-shaped placement plate 27, there are rollers 29 arranged through two reinforcement rods 28, thereby maintaining the stability of the arc-shaped placement plate 27. The staff places the aerospace engine on the arc-shaped placement plate 27. The arc-shaped placement plate 27 moves horizontally to move the aerospace engine to the detection position, so as to quickly clamp the aerospace engine through the clamping device. And after the detection is completed, the aerospace engine can be moved out, which is convenient for the staff to take it out and convey it later. And at the four surrounding locations of the top of the fixed base 23, there are second electric telescopic rods 31 arranged through the connecting sleeves 30. The staff connects the second electric telescopic rods 31 to the power supply. The second electric telescopic rods 31 drive the anti-slip bottom plates 32 at the bottom ends to adjust the height. Thus, when detecting the aerospace engine, the anti-slip bottom plates 32 are in contact with the ground, thereby improving the stability of the overall fixing device and ensuring the stability of the aerospace engine thrust detection.

[0047] Example 5:

[0048] Please refer to Figures 1 to 7As shown in the figure, one side of the top of the fixed bracket 1 is fixedly connected with a conical bracket 35. One side of the bottom of the conical bracket 35 is fixedly connected with a connecting frame 36. One side of the inner wall of the connecting frame 36 is fixedly connected with a third electric telescopic rod 37. The front end of the third electric telescopic rod 37 is fixedly connected with a mounting frame 38. One side of the inner wall of the mounting frame 38 is fixedly connected with a fourth electric telescopic rod 39. The bottom end of the fourth electric telescopic rod 39 is fixedly connected with a thrust gauge 40. One side of the top of the fixed bracket 1 is fixedly connected with a lapping bracket 41. One side of the top of the lapping bracket 41 is fixedly connected with a fuel supply pipe 42. The middle of the top of the lapping bracket 41 is fixedly connected with an ignition control line 43. The other side of the top of the lapping bracket 41 is fixedly connected with a speed regulation line 44.

[0049] During use, a connecting frame 36 is arranged on the top of the fixed bracket 1 through the conical bracket 35. A third electric telescopic rod 37 is arranged on the inner wall of the connecting frame 36. The staff connects the third electric telescopic rod 37 to the power supply, and the third electric telescopic rod 37 drives the front-end mounting frame 38 to adjust. A fourth electric telescopic rod 39 is arranged on the inner wall of the mounting frame 38. The staff connects the fourth electric telescopic rod 39 to the power supply, and the fourth electric telescopic rod 39 drives the bottom-end thrust gauge 40 to adjust the height. The thrust gauge 40 is used to measure the magnitude of the thrust generated by the engine.

[0050] Working principle: When in use, the staff connects the first electric telescopic rod 5 to the power supply. The first electric telescopic rod 5 drives the assembly bracket 6 at the front end to adjust. The two sets of assembly brackets 6 clamp the aero-engine from both sides. The staff connects the first electric slide rail 7 to the power supply, and the first electric slide rail 7 drives the arc-shaped clamping plate 8 on the surface to adjust. Thus, the aero-engine is clamped semi-circularly by the cooperation of the assembly bracket 6 and the arc-shaped clamping plate 8, and there are two sets of symmetrically arranged clamping mechanisms to stably clamp the aero-engine. The staff connects the first servo motor 9 to the power supply, and the output end of the first servo motor 9 drives the driving rod 10 to rotate. The driving rod 10 drives the arc-shaped overlapping plate 11 at the front end to rotate. The aero-engine is sleeved at the bottom by the arc-shaped overlapping plate 11 to provide a stable thrust test for the aero-engine. The staff connects the fifth electric telescopic rod 45 to the power supply, and the front end of the fifth electric telescopic rod 45 drives the sixth electric telescopic rod 46 to adjust. The staff connects the sixth electric telescopic rod 46 to the power supply, and the sixth electric telescopic rod 46 drives the U-shaped bracket 47 at the bottom to adjust the height. By adjusting the position of the U-shaped bracket 47, the bottom of the clamped aero-engine is supported to facilitate maintaining the stability of the aero-engine. The staff connects the second servo motor 14 to the power supply, and the output end of the second servo motor 14 drives the transmission rod 15 to rotate. The transmission rod 15 drives the two transmission belts 16 on the surface to rotate. The two transmission belts 16 both drive the rotating wheels 17 on one side of the inner wall to rotate. The two rotating wheels 17 both drive the connecting rod 18 at the bottom to rotate. The connecting rod 18 drives the threaded rod 19 at the bottom to rotate. The threaded rod 19 drives the threaded sleeve ring 20 connected by threads on the surface to adjust the height. The threaded sleeve ring 20 drives the mounting plate 3 on the surface to adjust the height, thereby finely adjusting the clamped aero-engine. The staff connects the second electric slide rail 25 to the power supply, and the second electric slide rail 25 drives the sliding frame 26 slidably connected to the inner wall to move. The sliding frame 26 drives the arc-shaped placement plate 27 at the top to move, and there are rollers 29 on one side of the arc-shaped placement plate 27 through two reinforcing rods 28, thus maintaining the stability of the arc-shaped placement plate 27. The staff places the aerospace engine on the arc-shaped placement plate 27, and the arc-shaped placement plate 27 moves horizontally to move the aerospace engine to the detection position, so as to quickly clamp the aerospace engine through the clamping device, and after the detection is completed, the aerospace engine can be removed, which is convenient for the staff to take out and convey later. The staff connects the second electric telescopic rod 31 to the power supply, and the second electric telescopic rod 31 drives the anti-slip bottom plate 32 at the bottom to adjust the height. Thus, when the aerospace engine is detected, the anti-slip bottom plate 32 contacts the ground, thereby improving the stability of the overall fixing device and ensuring the stability of the aerospace engine thrust test. The staff connects the third electric telescopic rod 37 to the power supply, and the third electric telescopic rod 37 drives the mounting frame 38 at the front end to adjust. The staff connects the fourth electric telescopic rod 39 to the power supply, and the fourth electric telescopic rod 39 drives the thrust meter 40 at the bottom to adjust the height. The thrust meter 40 is used to measure the magnitude of the thrust generated by the engine.

[0051] Although embodiments of the present invention have been shown and described, those of ordinary skill in the art will appreciate that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft engine thrust detection device, characterized in that: include: A fixing bracket (1); Both sides of the bottom of the fixed bracket (1) are fixedly connected to sleeve rods (2), one side of the surface of the two sleeve rods (2) is slidably connected to a mounting plate (3), and both sides of the surface of the two mounting plates (3) are fixedly connected to mounting sleeves (4); A first electric telescopic rod (5) is fixedly connected to one side of the inner wall of the installation sleeve (4), a front end of the first electric telescopic rod (5) is fixedly connected to an assembly bracket (6), upper and lower sides of the surface of the assembly bracket (6) are fixedly connected to first electric slide rails (7), an output end of the first electric slide rail (7) is slidably connected to an arc-shaped clamping plate (8), a positioning plate (48) is fixedly connected to the middle of the back side of the installation sleeve (4), upper and lower sides of the surface of the positioning plate (48) are fixedly connected to a telescopic bracket (49), and a front end of the telescopic bracket (49) is fixedly connected to the back side of the assembly bracket (6); A conical bracket (35) is fixedly connected to one side of the top of the fixed bracket (1), a connecting frame (36) is fixedly connected to one side of the bottom of the conical bracket (35), a third electric telescopic rod (37) is fixedly connected to one side of the inner wall of the connecting frame (36), a front end of the third electric telescopic rod (37) is fixedly connected to a mounting frame (38), a fourth electric telescopic rod (39) is fixedly connected to one side of the inner wall of the mounting frame (38), and a thrust meter (40) is fixedly connected to the bottom end of the fourth electric telescopic rod (39).

2. The aircraft engine thrust detection device according to claim 1, characterized in that: A first servo motor (9) is fixedly connected to one side of the surface of one of the mounting plates (3); a driving rod (10) is installed at the output end of the first servo motor (9); a front end of the driving rod (10) is fixedly connected to an arc-shaped lap plate (11); and the two ends of the arc-shaped lap plate (11) are respectively rotatably connected to the inner walls of the two mounting plates (3); a fifth electric telescopic rod (45) is fixedly connected to one side of the inner walls of the two mounting plates (3); a front end of the fifth electric telescopic rod (45) is fixedly connected to a sixth electric telescopic rod (46); and a bottom end of the sixth electric telescopic rod (46) is fixedly connected to a U-shaped bracket (47).

3. The aircraft engine thrust detection device according to claim 1, characterized in that: Both sides of the back of the two mounting plates (3) are fixedly connected with a sleeve frame (50), the inner wall of the sleeve frame (50) is slidably connected with a sliding steel pipe (51), and the top of the sliding steel pipe (51) is fixedly connected to the bottom of the fixed bracket (1), one side of the top of the sleeve rod (2) is fixedly connected with a connecting bracket (12), the middle of the top of the connecting bracket (12) is fixedly connected with a motor box (13), one side of the inner wall of the motor box (13) is fixedly connected with a second servo motor (14), the output end of the second servo motor (14) is installed with a transmission rod (15), both sides of the surface of the transmission rod (15) are rotatably connected with a transmission belt (16), one side of the inner wall of the two transmission belts (16) are rotatably connected with a rotating wheel (17), and the surfaces of the transmission belt (16) and the rotating wheel (17) are both arranged on the inner wall of the connecting bracket (12).

4. The aircraft engine thrust detection device according to claim 3, characterized in that: One side of the bottom of the two rotating wheels (17) is fixedly connected to a connecting rod (18), the bottom end of the connecting rod (18) is fixedly connected to a threaded rod (19), one side of the surface of the threaded rod (19) is threadedly connected to a threaded collar (20), and one side of the threaded collar (20) is fixedly connected to the surface of the mounting plate (3).

5. The aircraft engine thrust detection device according to claim 1, characterized in that: A mounting platform (21) is fixedly connected to one side of the bottom of the fixed bracket (1), support rods (22) are fixedly connected to the four sides of the bottom of the mounting platform (21), a fixed base (23) is fixedly connected to the bottom end of the support rod (22), an assembly frame (24) is fixedly connected to the middle of the top of the fixed base (23), a second electric slide rail (25) is fixedly connected to one side of the inner wall of the assembly frame (24), and a sliding frame (26) is slidably connected to one side of the inner wall of the second electric slide rail (25).

6. The aircraft engine thrust detection device according to claim 5, characterized in that: An arc-shaped placement plate (27) is fixedly connected to one side of the top of the sliding frame (26), and the bottom of the arc-shaped placement plate (27) is arranged on the top of the mounting platform (21). Reinforcement rods (28) are fixedly connected to both sides of the surface of the arc-shaped placement plate (27), and the bottom ends of the two reinforcement rods (28) are fixedly connected to rollers (29).

7. The aircraft engine thrust detection device according to claim 5, characterized in that: The top of the fixed base (23) is fixedly connected with connecting sleeves (30) at four locations around the top, one side of the inner wall of the four connecting sleeves (30) is fixedly connected with a second electric telescopic rod (31), the bottom end of the second electric telescopic rod (31) is fixedly connected with an anti-skid bottom plate (32), and the top of the anti-skid bottom plate (32) is arranged at the bottom of the fixed base (23), the bottom of the fixed base (23) is fixedly connected with universal wheels (33) at four locations around the bottom, and one side of the top of the mounting platform (21) is fixedly connected with a control panel body (34).

8. The aircraft engine thrust detection device according to claim 1, characterized in that: A lap bracket (41) is fixedly connected to one side of the top of the fixed bracket (1), a fuel supply pipe (42) is fixedly connected to one side of the top of the lap bracket (41), an ignition control line (43) is fixedly connected to the middle of the top of the lap bracket (41), and a speed adjustment line (44) is fixedly connected to the other side of the top of the lap bracket (41).

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