Movable cylinder used for ground static strength test based on aircraft structure

Abstract

The utility model provides an aircraft structure ground static strength test-based actuating cylinder, which comprises an actuating cylinder body, a base and a limit adjusting mechanism, the base is fixedly provided with fixing plates which are arranged in a bilateral symmetry manner, a rotating shaft is fixed at the bottom of the actuating cylinder body and is rotatably connected between the two fixing plates, and the limit adjusting mechanism is fixedly connected with the actuating cylinder body. The limiting adjusting mechanism comprises an outer shell, a worm gear and a worm, the worm gear is connected with one end of the rotating shaft and arranged in the outer shell, the worm is in meshed connection with the worm gear and arranged in the outer shell, and the two ends of the worm extend out of the outer shell; by the adoption of the technical scheme, the worm is rotated to drive the worm gear to rotate, the worm gear drives the rotating shaft to rotate, the deflection angle of the actuator cylinder body is adjusted, then the load applying direction of the actuator cylinder is adjusted, in the connection mode of the worm gear and the worm, the worm can drive the worm gear to rotate, and the worm gear cannot drive the worm to rotate; therefore, the angle-adjusted actuator cylinder body is prevented from toppling under the action of gravity.

Description

Technical Field

[0001] The utility model relates to the field of actuating cylinders, in particular to an actuating cylinder for aircraft structure ground static strength tests. Background Art

[0002] During aircraft structure ground static strength tests, loads are applied through an actuating loading device, which includes an actuating cylinder and an actuating cylinder base. The cylinder body of the actuating cylinder is connected to the actuating cylinder base through a spherical plain bearing. When applying loads to the test piece through the above actuating loading device, the actuating cylinder base is fixed, and the piston rod of the actuating cylinder is connected to the test piece.

[0003] During a certain aircraft structure ground static strength test, it is necessary to fix the actuating cylinder base of the actuating loading device to the ground and keep the cylinder body of the actuating cylinder of the actuating loading device perpendicular to the ground. However, since the cylinder body of the actuating cylinder is connected to the actuating cylinder base through a spherical plain bearing and can rotate arbitrarily relative to the actuating cylinder base, when the test personnel install it, the actuating cylinder is prone to tipping due to its own weight, causing the cylinder body of the actuating cylinder to deviate from the perpendicular to the ground, ultimately affecting the magnitude and direction of the applied load. In severe cases, it will damage the test piece and even threaten the safety of the test personnel.

[0004] The Chinese invention patent with the publication number CN110294144B discloses an actuating cylinder bracket and an actuating loading device having the same. The bracket can support the actuating cylinder to keep the actuating cylinder in a vertical state. However, during aircraft structure ground static strength tests, sometimes it is necessary to adjust the load application direction of the actuating cylinder, and the above invention cannot achieve load application at different angles to the test piece. Summary of the Utility Model

[0005] (I) Technical Problems to be Solved

[0006] In order to solve the above problems of the prior art, the utility model provides an actuating cylinder for aircraft structure ground static strength tests.

[0007] (II) Technical Solutions

[0008] To achieve the above object, the main technical solutions adopted by the utility model include:

[0009] An actuating cylinder for aircraft structure ground static strength tests includes an actuating cylinder body, a base, and a limit adjusting mechanism;

[0010] Fixed plates arranged symmetrically left and right are fixedly installed on the base,

[0011] The rotating shaft is fixed at the bottom of the actuating cylinder body and is rotatably connected between the two fixed plates;

[0012] The position-limiting and adjusting mechanism includes a housing, a worm gear, and a worm.

[0013] The worm gear is connected to one end of the rotating shaft and is arranged inside the housing.

[0014] The worm meshes with the worm gear. The worm is arranged inside the housing, and both ends of the worm extend out of the housing.

[0015] Preferably, the body of the worm is connected to the inner wall of the housing through bearings near both ends, and one end of the worm is provided with an internal hexagonal socket head cap groove.

[0016] Preferably, a spirit level is installed on the barrel of the actuating cylinder body.

[0017] Preferably, the connection between the rotating shaft and the fixing plate is connected by a bearing.

[0018] Preferably, the worm gear is connected to the rotating shaft through a planetary reduction gear set.

[0019] (III) Beneficial effects

[0020] The beneficial effects of the present utility model are as follows: By adopting the above technical solution, rotating the worm drives the worm gear to rotate, and the worm gear drives the rotating shaft to rotate, which is used to adjust the deflection angle of the actuating cylinder body, and further adjust the load application direction of the actuating cylinder. Moreover, in the connection mode of the worm gear and the worm, the worm can drive the worm gear to rotate, while the worm gear cannot drive the worm to rotate. This makes the actuating cylinder body after adjusting the angle not tilt under the action of gravity. Description of the drawings

[0021] Figure 1 It is a schematic structural diagram of an actuating cylinder used in the ground static strength test of an aircraft structure.

[0022] Figure 2 It is a schematic structural diagram of the position-limiting and adjusting mechanism.

[0023]

Description of the reference numerals

[0024] 1. Actuating cylinder body;

[0025] 2. Base;

[0026] 3. Fixing plate;

[0027] 4. Position-limiting and adjusting mechanism;

[0028] 41. Worm gear; 42. Worm. Detailed implementation manners

[0029] In order to better explain the present utility model for easy understanding, the present utility model will be described in detail below with reference to the drawings through specific implementation manners.

[0030] Please refer to Figures 1 to 2 , this utility model provides a hydraulic cylinder used for the ground static strength test of an aircraft structure, which includes a hydraulic cylinder body 1, a base 2 and a limit adjustment mechanism 4;

[0031] On the base 2, fixed plates 3 arranged symmetrically left and right are fixedly installed.

[0032] The rotating shaft is fixed at the bottom of the hydraulic cylinder body 1 and is rotatably connected between the two fixed plates 3;

[0033] The limit adjustment mechanism 4 includes a housing, a worm gear 41 and a worm 42;

[0034] One end of the worm gear 41 is connected to the rotating shaft and is arranged inside the housing;

[0035] The worm 42 is meshed with the worm gear 41. The worm 42 is arranged inside the housing, and both ends of the worm 42 extend out of the housing;

[0036] During use, rotate the worm 42 to drive the worm gear 41 to rotate. The worm gear 41 drives the rotating shaft to rotate, so as to adjust the deflection angle of the hydraulic cylinder body 1, and further adjust the load application direction of the hydraulic cylinder. Moreover, in the connection mode of the worm gear 41 and the worm 42, the worm 42 can drive the worm gear 41 to rotate, while the worm gear 41 cannot drive the worm 42 to rotate. This makes the adjusted hydraulic cylinder body 1 not tilt under the action of gravity.

[0037] In this embodiment, the body of the worm 42 is connected to the inner wall of the housing through bearings near both ends. One end of the worm 42 is provided with an internal hexagon socket head cap. Select a corresponding internal hexagon wrench to rotate the worm 42, so as to control the rotation of the worm 42.

[0038] In this embodiment, a spirit level is installed on the cylinder body of the hydraulic cylinder body 1, and the levelness of the hydraulic cylinder body 1 is obtained through the spirit level.

[0039] In this embodiment, the connection between the rotating shaft and the fixed plate 3 adopts a bearing connection.

[0040] In this embodiment, the worm gear 41 is connected to the rotating shaft through a planetary reduction gear set. The setting of the planetary reduction gear set is beneficial to accurately adjust the deflection angle of the hydraulic cylinder body 1.

[0041] The working principle of this utility model is as follows:

[0042] Rotating the worm 42 drives the worm wheel 41 to rotate. The worm wheel 41 drives the rotating shaft to rotate, which is used to adjust the deflection angle of the actuator body 1, and further adjust the load application direction of the actuator. Moreover, in the connection mode of the worm wheel 41 and the worm 42, the worm 42 can drive the worm wheel 41 to rotate, while the worm wheel 41 cannot drive the worm 42 to rotate. This prevents the actuator body 1 from tilting under the action of gravity after the angle is adjusted.

[0043] The circuits, electronic components, and modules involved are all prior arts and can be fully realized by those skilled in the art without further elaboration. The content protected by the present utility model does not involve improvements to software and methods either.

[0044] The above are only embodiments of the present utility model, and do not limit the patent scope of the present utility model accordingly. Any equivalent transformation made by using the content of the specification and drawings of the present utility model, directly or indirectly applied in related technical fields, shall be equally included in the patent protection scope of the present utility model.

[0045] In addition, it should be understood that although this specification is described according to embodiments, not every embodiment only contains an independent technical solution. This narrative way of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. An actuator used in the ground static strength test of an aircraft structure, characterized in that, It includes an actuator body, a base, and a limit adjustment mechanism; On the base, fixed plates arranged symmetrically left and right are fixedly installed, The rotating shaft is fixed at the bottom of the actuator body and rotatably connected between the two fixed plates; The limit adjustment mechanism includes an outer shell, a worm gear, and a worm; One end of the rotating shaft is connected to the worm gear and is arranged inside the outer shell; The worm is meshed with the worm gear, the worm is arranged inside the outer shell, and both ends of the worm extend inside and outside the outer shell.

2. The actuator used in the ground static strength test based on the aircraft structure according to claim 1, characterized in that, The body of the worm is connected to the inner wall of the outer shell through bearings near both ends, and one end of the worm is provided with an internal hexagonal socket head slot.

3. The actuator used in the ground static strength test based on the aircraft structure according to claim 1, characterized in that, A spirit level is installed on the barrel of the actuator body.

4. An actuator used in the ground static strength test based on the aircraft structure according to claim 1, characterized in that The connection between the rotating shaft and the fixed plate is connected by a bearing.

5. An actuator used for the ground static strength test of an aircraft structure according to claim 1, characterized in that, The worm gear is connected to the rotating shaft through a planetary reduction gear set.

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