Device suitable for automatic detection of airplane control surface loading

Abstract

The utility model provides a device suitable for automatic detection of airplane control surface loading, which comprises a base, a cavity is arranged in the base, a lifting device is mounted at the top end of the base, a support frame is mounted at the top end of the lifting device, and a clamp assembly is mounted at the top of the support frame. The arranged lifting device is matched with the clamp assembly to conveniently carry out control surface loading detection on airplanes with different control surface heights, so that the applicability of the device is effectively improved, and the clamp assembly can rotate along with the control surfaces, so that the control surfaces with different inclination angles can be effectively clamped, the control surface loading test is conveniently carried out, and the test efficiency is improved. And the load applied to the control surface can be conveniently detected through the arranged force transducer.

Description

Technical Field

[0001] This utility model belongs to the field of testing device technology, specifically relating to a device suitable for automatic detection of aircraft control surface loading. Background Technology

[0002] Aircraft control surfaces are crucial components for aircraft control, primarily used to ensure longitudinal and lateral flight balance and maneuverability. Aircraft control surface loading tests are used to detect the dynamic and static characteristics of the flight control system under load, as well as the operation of the control surface control mechanism and control surfaces. Traditional control surface loading test devices are usually fixed, dedicated test benches. Although this test method can basically test and verify the functional performance of the flight control system, control surfaces, and their control systems, this test device also has disadvantages such as high specialization and high cost per unit. Based on this, we propose a control surface recording and testing device with strong applicability. Utility Model Content

[0003] The purpose of this invention is to provide a device for automatic detection of aircraft control surface loading, aiming to solve the problems mentioned in the background art.

[0004] To achieve the above objectives, the present invention provides the following technical solution: a device for automatic detection of aircraft control surface loading, comprising a base, the base having an internal cavity, a lifting device mounted on the top of the base, a support frame mounted on the top of the lifting device, and a clamping assembly mounted on the top of the support frame.

[0005] The support frame includes a base plate installed on the top of the lifting device. Side plates are installed on both sides of the top of the base plate. The top of the side plates is provided with an installation groove. A pressure cap is installed on the top of the side plates by bolts.

[0006] The clamp assembly includes a mounting frame, with connecting rods fixedly connected to both sides of the mounting frame. A bearing is installed at one end of each connecting rod, and the bearing is installed in a mounting groove and fixed by a pressure cap. A servo electric cylinder is installed on the front of the mounting frame, and a force sensor is installed at the telescopic end of the servo electric cylinder. A U-shaped clamp is installed at the top of the force sensor, and an adjusting bolt is threaded to the top of the U-shaped clamp. A first clamping block is installed at one end of the adjusting bolt inside the U-shaped clamp, and a second clamping block is installed at the other end inside the U-shaped clamp.

[0007] As a preferred technical solution of this utility model, the lifting device is a worm gear lifter. One end of the lifting screw in the lifting device extends into the cavity. Four guide sleeves are also installed at the top of the base. A guide rod is inserted into each guide sleeve. One end of the guide rod extends into the cavity and the other end is connected to the bottom end of the base plate.

[0008] In a preferred embodiment of this invention, the two ends of the worm gear in the lifting device are connected to a handwheel and a drive motor, respectively.

[0009] As a preferred technical solution of this utility model, a protective cover is installed on the top of the base, the drive motor is set inside the protective cover, the top of the protective cover has a first opening and four second openings, the lifting screw of the lifting device passes through the first opening, the four guide rods pass through the corresponding second openings respectively, and a control panel is provided on the front of the protective cover.

[0010] As a preferred technical solution of this utility model, an inspection door is installed on one side of the base, and casters with foot cups are installed at the bottom of the base.

[0011] As a preferred technical solution of this utility model, the top of the base is provided with a through cavity mounting hole, and the top of the base is provided with positioning grooves on both sides of the mounting hole. The surface of the connecting rod is provided with positioning blocks, the size of the positioning blocks matches the size of the positioning grooves, and the size of the mounting hole is larger than the size of the mounting bracket.

[0012] In a preferred embodiment of this invention, the drive motor and the servo cylinder are both electrically connected to the control panel, and the force sensor is electrically connected to an external controller.

[0013] Compared with the prior art, the beneficial effects of this utility model are: the casters make the device easy to move, and the lifting device and clamping assembly facilitate the control surface loading test of aircraft at different control surface heights, thereby effectively improving the applicability of the device. Moreover, the clamping assembly can rotate with the control surface, so that control surfaces at different tilt angles can be effectively clamped, thus facilitating control surface loading tests. Attached Figure Description

[0014] The accompanying drawings are provided to further illustrate the present invention and form part of the specification. They are used together with the embodiments of the present invention to explain the present invention, but do not constitute a limitation thereof. In the drawings:

[0015] Figure 1 This is a schematic diagram of the structure of the present invention in use.

[0016] Figure 2 This is a schematic diagram of the structure of Embodiment 1 of this utility model;

[0017] Figure 3 This is a schematic diagram of the base and lifting device in this utility model;

[0018] Figure 4 This is a schematic diagram of the support frame in this utility model;

[0019] Figure 5 This is a schematic diagram of the clamp assembly in this utility model;

[0020] Figure 6 This is a schematic diagram of the structure of the protective cover in this utility model;

[0021] Figure 7 This is a schematic diagram of the structure of Embodiment 2 of this utility model.

[0022] In the diagram: 1. Base; 2. Lifting device; 3. Support frame; 31. Base plate; 32. Side plate; 33. Mounting slot; 34. Pressure cover; 4. Clamp assembly; 41. Mounting bracket; 42. Connecting rod; 43. Bearing; 44. Servo cylinder; 45. Force sensor; 46. U-shaped clamp; 47. Adjusting bolt; 48. First clamping block; 49. Second clamping block; 410. Positioning block; 5. Guide sleeve; 6. Guide rod; 7. Handwheel; 8. Drive motor; 9. Protective cover; 10. First opening; 11. Second opening; 12. Control panel; 13. Inspection door; 14. Caster; 15. Mounting hole; 16. Positioning slot. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0024] Example 1

[0025] Please see Figures 1-6 The present invention provides the following technical solution: a device for automatic detection of aircraft control surface loading, including a base 1, the base 1 having a cavity inside, a lifting device 2 installed at the top of the base 1, a support frame 3 installed at the top of the lifting device 2, and a clamping assembly 4 installed at the top of the support frame 3.

[0026] In this embodiment, the support frame 3 includes a base plate 31 installed on the top of the lifting device 2. Side plates 32 are installed on both sides of the top of the base plate 31. The top of the side plates 32 is provided with a mounting groove 33. A pressure cap 34 is installed on the top of the side plates 32 by bolts. The clamp assembly 4 includes a mounting frame 41. Connecting rods 42 are fixedly connected to both sides of the mounting frame 41. A bearing 43 is installed at one end of the connecting rod 42. The bearing 43 is installed in the mounting groove 33 and fixed by the pressure cap 34. A servo electric cylinder 44 is installed on the front of the mounting frame 41. A force sensor 45 is installed at the telescopic end of the servo electric cylinder 44. A U-shaped clamp 46 is installed at the top of the force sensor 45. An adjusting bolt 47 is threadedly connected to the top of the U-shaped clamp 46. A first clamping block 48 is installed at one end of the adjusting bolt 47 inside the U-shaped clamp 46. A second clamping block 49 is installed at one end inside the U-shaped clamp 46.

[0027] Specifically, since the bearing 43 is installed in the mounting groove 33 and fixed by the pressure cap 34, the clamp assembly 4 can be disassembled and moved to the control surface of the aircraft. The lifting device 2 lifts the clamp assembly 4 so that the control surface of the aircraft is placed in the U-shaped clamp 46. The bearing 43 allows the angle of the U-shaped clamp 46 to be adjusted. The servo cylinder 44 drives the U-shaped clamp 46 to rise so that the second clamp 49 fits against the bottom of the control surface. Then, by rotating the adjusting bolt 47, the first clamp 48 fits against the top of the control surface. The first clamp 48 and the second clamp 49 clamp the control surface of the aircraft. The force sensor 45 can detect the load applied to the control surface. After the lifting device 2 is raised to the highest position and the extension end of the servo cylinder 44 is extended, the highest measuring position of the entire device is reached. The lifting device 2 allows the device to perform control surface loading tests on control surfaces at different heights.

[0028] In this embodiment, the lifting device 2 is a worm gear lifter. One end of the lifting screw in the lifting device 2 extends into the cavity. Four guide sleeves 5 are also installed at the top of the base 1. Each guide sleeve 5 is connected with a guide rod 6. One end of the guide rod 6 extends into the cavity and the other end is connected to the bottom end of the base plate 31.

[0029] Specifically, since the lifting device 2 is a worm gear lifter, and the worm gear lifter has many advantages such as compact structure, small size, light weight, wide range of power sources, no noise, convenient installation, flexible use, multiple functions, multiple matching forms, high reliability, and long service life, the guide sleeve 5 and guide rod 6 can improve the stability of the lifting of the support frame 3.

[0030] In this embodiment, the two ends of the worm gear in the lifting device 2 are connected to the handwheel 7 and the drive motor 8, respectively.

[0031] Specifically, the power source of the lifting device 2 can be manual or electric. The operator can drive the lifting device 2 to lift the clamp assembly 4 by turning the handwheel 7 or by driving the lifting device 2 to lift the clamp assembly 4 by driving the motor 8.

[0032] In this embodiment, a protective cover 9 is installed on the top of the base 1, and the drive motor 8 is located inside the protective cover 9. The top of the protective cover 9 has a first opening 10 and four second openings 11. The lifting screw in the lifting device 2 passes through the first opening 10, and the four guide rods 6 pass through the corresponding second openings 11 respectively. A control panel 12 is provided on the front of the protective cover 9.

[0033] Specifically, the protective cover 9 can protect the worm gear structure and drive motor 8 in the lifting device 2, while the first opening 10 and the second opening 11 can prevent the movement of the lifting screw and the lifting of the guide rod 6 in the lifting device 2 from being affected.

[0034] In this embodiment, an inspection door 13 is installed on one side of the base 1, and a caster 14 with a foot cup is installed at the bottom of the base 1.

[0035] Specifically, the access door 13 facilitates the maintenance of instruments inside the cavity, while the casters 14 facilitate the movement of the device. Moreover, the casters 14 are equipped with feet, which can improve the stability of the device during use and prevent the device from shifting its position.

[0036] In this embodiment, the drive motor 8 and the servo cylinder 44 are both electrically connected to the control panel 12, and the force sensor 45 is electrically connected to the external controller.

[0037] Specifically, the control panel 12 facilitates the control of the drive motor 8 and the servo cylinder 44, while the external controller detects the data from the force sensor 45, thus facilitating the transmission of the data to the operator's terminal for analysis.

[0038] Example 2

[0039] Please see Figure 3 and Figure 7 In this embodiment, the top of the base 1 is provided with a through cavity mounting hole 15, and the top of the base 1 is provided with positioning grooves 16 on both sides of the mounting hole 15. The surface of the connecting rod 42 is provided with a positioning block 410, the size of the positioning block 410 matches the size of the positioning groove 16, and the size of the mounting hole 15 is larger than the size of the mounting bracket 41.

[0040] Specifically: After the staff removes the pressure cap 34, the clamp assembly 4 can be easily removed from the support frame 3. Then, the bottom plate 31 of the support frame 3 is lowered to the top of the protective cover 9 by the lifting device 2. Then, the staff can insert the mounting bracket 41 into the cavity through the mounting hole 15. During this process, the positioning block 410 is aligned with the positioning groove 16, so that the positioning block 410 is placed in the positioning groove 16. In this way, the device reaches the lowest measuring position of the whole machine.

[0041] Finally, it should be noted that the above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Although the utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A device for automatic detection of aircraft control surface load, comprising a base (1), characterized in that: The base (1) has a cavity inside, a lifting device (2) is installed at the top of the base (1), a support frame (3) is installed at the top of the lifting device (2), and a clamp assembly (4) is installed at the top of the support frame (3). The support frame (3) includes a base plate (31) installed on the top of the lifting device (2). Side plates (32) are installed on both sides of the top of the base plate (31). The top of the side plate (32) is provided with an installation groove (33). The top of the side plate (32) is fitted with a pressure cap (34) by bolts. The clamp assembly (4) includes a mounting frame (41), with connecting rods (42) fixedly connected to both sides of the mounting frame (41). A bearing (43) is installed at one end of the connecting rod (42), and the bearing (43) is installed in the mounting groove (33) and fixed by a pressure cap (34). A servo electric cylinder (44) is installed on the front of the mounting frame (41), and a force sensor (45) is installed at the telescopic end of the servo electric cylinder (44). A U-shaped clamp (46) is installed at the top of the force sensor (45), and an adjusting bolt (47) is threadedly connected to the top of the U-shaped clamp (46). A first clamping block (48) is installed at one end of the adjusting bolt (47) inside the U-shaped clamp (46), and a second clamping block (49) is installed at one end inside the U-shaped clamp (46).

2. The device for automatic detection of aircraft control surface load according to claim 1, characterized in that: The lifting device (2) is a worm gear lifter. One end of the lifting screw in the lifting device (2) extends into the cavity. The top of the base (1) is also equipped with four guide sleeves (5). Each guide sleeve (5) is connected with a guide rod (6). One end of the guide rod (6) extends into the cavity and the other end is connected to the bottom end of the base plate (31).

3. The device for automatic detection of aircraft control surface load according to claim 2, characterized in that: The two ends of the worm gear in the lifting device (2) are connected to the handwheel (7) and the drive motor (8) respectively.

4. The device for automatic detection of aircraft control surface load according to claim 3, characterized in that: The top of the base (1) is equipped with a protective cover (9), the drive motor (8) is located inside the protective cover (9), the top of the protective cover (9) has a first opening (10) and four second openings (11), the lifting screw of the lifting device (2) passes through the first opening (10), and the four guide rods (6) pass through the corresponding second openings (11) respectively. The front of the protective cover (9) is equipped with a control panel (12).

5. The device for automatic detection of aircraft control surface load according to claim 1, characterized in that: An inspection door (13) is installed on one side of the base (1), and a caster (14) with a foot cup is installed at the bottom of the base (1).

6. The device for automatic detection of aircraft control surface load according to claim 1, characterized in that: The top of the base (1) has a through-cavity mounting hole (15), and the top of the base (1) has positioning grooves (16) on both sides of the mounting hole (15). The surface of the connecting rod (42) is equipped with a positioning block (410), the size of the positioning block (410) matches the size of the positioning groove (16), and the size of the mounting hole (15) is larger than the size of the mounting bracket (41).

7. The device for automatic detection of aircraft control surface load according to claim 4, characterized in that: The drive motor (8) and the servo electric cylinder (44) are both electrically connected to the control panel (12), and the force sensor (45) is electrically connected to the external controller.

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