CN218156829U

CN218156829U - Unmanned aerial vehicle makes and uses wing intensity detection device

Info

Publication number: CN218156829U
Application number: CN202222556103.9U
Authority: CN
Inventors: 张依然
Original assignee: Qinyang Yangpu Industrial Co ltd
Current assignee: Qinyang Yangpu Industrial Co ltd
Priority date: 2022-09-26
Filing date: 2022-09-26
Publication date: 2022-12-27
Anticipated expiration: 2032-09-26

Abstract

The utility model discloses an unmanned aerial vehicle makes and uses wing intensity detection device, including the diaphragm, two backup pads of the up end symmetry fixedly connected with of diaphragm, two the common fixedly connected with roof of up end of backup pad, two hydraulic telescoping rod of the lower terminal surface symmetry fixedly connected with of roof, every hydraulic telescoping rod's the equal fixedly connected with connecting plate of flexible end. The utility model discloses, through gear motor, the cooperation setting of worm and worm wheel, can drive the dwang and rotate, the dwang sets up through the cooperation of a gear and No. two gears, can drive two-way threaded rod and rotate, two-way threaded rod passes through the thread bush, pull rod and electric telescopic handle's cooperation setting, can drive two clamping relative movement and carry out the centre gripping spacing to the unmanned aerial vehicle wing, and can finely tune two clamping moreover, make the centre gripping more stable, prevent that the unmanned aerial vehicle wing from taking place to rock, and then improved the effect of centre gripping.

Description

Unmanned aerial vehicle makes and uses wing intensity detection device

Technical Field

The utility model relates to an unmanned aerial vehicle wing detects technical field, especially relates to an unmanned aerial vehicle makes and uses wing intensity detection device.

Background

One of the contents of the structural test is to observe and research the distribution conditions of the strength, the rigidity, the stress and the deformation of the aircraft structure or component under the action of the static load, and the method is an important means for verifying the structural strength and the static analysis correctness of the aircraft, and a loading system of the full-size structural static test is complex. Static testing arrangement of aircraft wing intensity on the existing market, it is inconvenient generally to install, the installation department does not have unified support frame, generally be every check point fixed alone, the installation department needs to measure operations such as punch, this mode adaptation model scope is less, be unfavorable for the static test to the aircraft wing intensity of different models, the position of regulation check point that can not convenient and fast, can not guarantee mostly that its check point is located same water flat line, lead to detecting the deviation appearing, be unfavorable for the accurate nature of detection.

To above-mentioned problem, the current patent of publication No. CN212829145U discloses a static test device for aircraft wing intensity, including the installing support, the outward appearance slidable mounting of installing support has the test component, the last surface mounting of installing support has the inflation screw rod, the outer surface welding of one side of installing support has first fixed plate, the opposite side upper surface welding of installing support has the second fixed plate, the upper end of test component is provided with the balladeur train, the lower surface of balladeur train articulates there is the hydraulic stem, the articulated pressure sensor that draws of installing of lower extreme of hydraulic stem, the lower fixed surface that draws pressure sensor has the pulling cardboard. The utility model discloses static testing arrangement of aircraft wing intensity is provided with the installing support, reduces the deviation in detecting, and detects that the component is located and can adjust as required on the installing support, and the model that the adaptation is on a large scale detects.

Carry out the centre gripping through two extrusion clamps to the wing in the above-mentioned technique to carry out spacing fixed to the extrusion clamp through set screw, but can not finely tune the extrusion clamp among the above-mentioned technique, the unstable condition of centre gripping can appear, and the wing takes place to rock easily in the testing process, and then has reduced the effect of centre gripping.

To the problem, the wing strength detection device for manufacturing the unmanned aerial vehicle is provided.

SUMMERY OF THE UTILITY MODEL

The utility model aims at solving among the prior art "carry out the centre gripping through two extrusion clamping to the wing in the above-mentioned technique to carry out spacing fixed through set screw to the extrusion clamping, but can not finely tune the extrusion clamping among the above-mentioned technique, the unstable condition of centre gripping can appear, the wing takes place easily in the testing process and rocks, and then has reduced the defect of the effect of centre gripping", thereby provides an unmanned aerial vehicle and has made wing intensity detection device.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

the utility model provides an unmanned aerial vehicle makes and uses wing intensity detection device, includes the diaphragm, two backup pads of up end symmetry fixedly connected with of diaphragm, two the common fixedly connected with roof of up end of backup pad, two hydraulic telescoping rod of the lower terminal surface symmetry fixedly connected with of roof, every the equal fixedly connected with connecting plate in hydraulic telescoping rod's flexible end, every the lower terminal surface of connecting plate all rotates and is connected with and draws pressure sensor, two draw pressure sensor's the common fixedly connected with headstock of lower extreme, the up end fixedly connected with gear motor of headstock, gear motor's output runs through the up end and the fixedly connected with worm of headstock, the meshing is connected with the worm wheel on the worm, the horizontal fixed interlude of center department of worm wheel has the dwang, the fixed cup joint has No. one gear on the dwang, the meshing is connected with No. two gears on No. one gear, the horizontal fixed interlude of center department of No. two gears has two threaded sleeves, every the equal fixedly connected with pull rod in one side of threaded sleeve, two slide holes have been seted up to the lower terminal surface symmetry of headstock, every the lower extreme of pull rod all runs through slide hole and fixedly connected with the electric telescopic rod.

Preferably, two risers of symmetry fixedly connected with on the inner wall of fixed case, the both ends of dwang are rotated respectively and are connected two on the lateral wall of riser.

Preferably, two opposite threads are arranged on the bidirectional threaded rod, and two ends of the bidirectional threaded rod are rotatably connected to the inner wall of the fixed box.

Preferably, both the pull rods are slidably connected in the inner wall of the sliding hole, and the diameter ratio between the first gear and the second gear is 1.

Preferably, the lower terminal surface symmetry fixedly connected with four supporting legs of diaphragm, every the equal fixedly connected with skid resistant base of lower extreme of supporting leg.

Compared with the prior art, the beneficial effects of the utility model are that:

the rotating rod can be driven to rotate through the matching arrangement of the speed reducing motor, the worm and the worm wheel, the rotating rod can drive the bidirectional threaded rod to rotate through the matching arrangement of the first gear and the second gear, the bidirectional threaded rod can drive the two clamps to relatively move and clamp and limit the wings of the unmanned aerial vehicle through the matching arrangement of the threaded sleeve, the pull rod and the electric telescopic rod, and the two clamps can be finely adjusted, so that the clamping is more stable, the wings of the unmanned aerial vehicle are prevented from shaking, and the clamping effect is further improved; and because the diameter of a gear is far less than the diameter of No. two gears, consequently the rotation of No. two gears can be less than the rotation of a gear to can make two-way threaded rod slowly rotate, the threaded rod can drive the clamping through thread bush and pull rod slowly and remove, prevents that the clamping from removing to lead to inconveniently controlling the device too fast.

Drawings

Fig. 1 is a schematic front cross-sectional structural view of a wing strength detection device for manufacturing an unmanned aerial vehicle according to the present invention;

fig. 2 is an enlarged schematic structural view of a point a in fig. 1 according to the present invention;

fig. 3 is an enlarged schematic structural diagram of B in fig. 1 according to the present invention.

In the figure: the device comprises a transverse plate 1, a supporting plate 2, a top plate 3, a hydraulic telescopic rod 4, a connecting plate 5, a pulling pressure sensor 6, a fixing box 7, a speed reducing motor 8, a worm 9, a worm wheel 10, a rotating rod 11, a first gear 12, a second gear 13, a bidirectional threaded rod 14, a threaded sleeve 15, a pull rod 16, an electric telescopic rod 17 and a clamp 18.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention.

Referring to fig. 1-3, a wing strength detection device for unmanned aerial vehicle manufacturing comprises a transverse plate 1, two support plates 2 are symmetrically and fixedly connected to the upper end surface of the transverse plate 1, a top plate 3 is fixedly connected to the upper end surfaces of the two support plates 2, two hydraulic telescopic rods 4 are symmetrically and fixedly connected to the lower end surface of the top plate 3, a connecting plate 5 is fixedly connected to the telescopic end of each hydraulic telescopic rod 4, a tension pressure sensor 6 is rotatably connected to the lower end surface of each connecting plate 5, a fixing box 7 is fixedly connected to the lower ends of the two tension pressure sensors 6, a reduction motor 8 is fixedly connected to the upper end surface of the fixing box 7, the output end of the reduction motor 8 penetrates through the upper end surface of the fixing box 7 and is fixedly connected with a worm 9, a worm wheel 10 is engaged and connected to the worm 9, a rotating rod 11 is horizontally and fixedly inserted in the center of the worm wheel 10, a first gear 12 is fixedly sleeved on the rotating rod 11, and a second gear 13 is engaged and connected to the first gear 12, a bidirectional threaded rod 14 is horizontally and fixedly inserted in the center of the second gear 13, two threaded sleeves 15 are symmetrically meshed and connected to the bidirectional threaded rod 14, a pull rod 16 is fixedly connected to one side of each threaded sleeve 15, two sliding holes are symmetrically formed in the lower end face of the fixed box 7, the lower end of each pull rod 16 penetrates through the sliding hole and is fixedly connected with an electric telescopic rod 17, a clamp 18 is fixedly connected to the telescopic end of each electric telescopic rod 17, the rotating rod 11 can be driven to rotate through the matching arrangement of the speed reducing motor 8, the worm 9 and the worm wheel 10, the rotating rod 11 can drive the bidirectional threaded rod 14 to rotate through the matching arrangement of the first gear 12 and the second gear 13, the bidirectional threaded rod 14 can drive the two clamps 18 to relatively move and clamp and limit the wings of the unmanned aerial vehicle through the matching arrangement of the threaded sleeves 15, the pull rods 16 and the electric telescopic rods 17, the two clamps 18 can be finely adjusted, so that clamping is more stable, wings of the unmanned aerial vehicle are prevented from shaking, and the clamping effect is improved; and because the diameter of the first gear 12 is far smaller than that of the second gear 13, the rotation of the second gear 13 is smaller than that of the first gear 12, so that the bidirectional threaded rod 14 can rotate slowly, the bidirectional threaded rod 14 can drive the clamp 18 to move slowly through the threaded sleeve 15 and the pull rod 16, and the condition that the clamp 18 moves too fast to control the device is prevented.

Wherein, two risers of symmetry fixedly connected with on the inner wall of fixed box 7, the both ends of dwang 11 are rotated respectively and are connected on the lateral wall of two risers, and the riser can play the effect of support to dwang 11.

Wherein, two sections of opposite screw threads are arranged on the bidirectional threaded rod 14, both ends of the bidirectional threaded rod 14 are rotatably connected on the inner wall of the fixed box 7, and the bidirectional threaded rod 14 can drive the threaded sleeve 15 to move.

Wherein, two pull rods 16 are all connected in the inner wall of slide opening in a sliding manner, the diameter ratio between first gear 12 and second gear 13 is 1.

Wherein, four supporting legs of the lower terminal surface symmetry fixedly connected with of diaphragm 1, the equal fixedly connected with skid proof base of lower extreme of every supporting leg, the supporting leg can play the effect of support to the device.

In the utility model, when in work, the wing of the unmanned aerial vehicle is placed between two clamping clips 18, then the gear motor 8 is started, the output end of the gear motor can drive the worm 9 to rotate, the worm 9 can drive the worm wheel 10 to rotate, the worm wheel 10 can drive the rotating rod 11 to rotate, the rotating rod 11 can drive the first gear 12 to rotate, the first gear 12 can drive the second gear 13 to rotate, the second gear 13 can drive the two-way threaded rod 14 to rotate, the two-way threaded rod 14 can drive the two threaded sleeves 15 to move relatively, the threaded sleeves 15 can drive the pull rod 16 to move, the pull rod 16 can drive the clamping clips 18 to move relatively through the electric telescopic rod 17, thereby the wing of the unmanned aerial vehicle with different sizes can be clamped and limited, and the two clamping clips 18 can be finely adjusted, so that the clamping is more stable, prevent that the unmanned aerial vehicle wing from taking place to rock, and then improved the effect of centre gripping, then start electric telescopic handle 17 and can drive clamping 18 and upwards move, it is tight to unmanned aerial vehicle wing memorability clamp, then can upwards stimulate the unmanned aerial vehicle wing through hydraulic telescopic rod 4 and pull pressure sensor 6, pull pressure sensor 6 operation detection hydraulic telescopic rod 4 pulling force, the intensity of reacing the wing after the calculation of computer, because the diameter of a gear 12 is far less than the diameter of No. two gears 13, consequently, the rotation of No. two gears 13 can be less than the rotation of a gear 12, thereby can make two-way threaded rod 14 slowly rotate, two-way threaded rod 14 can drive clamping 18 through thread bush 15 and pull rod 16 slowly and remove, prevent that clamping 18 from removing too fast and leading to inconvenient controlling the device.

Above, only be the embodiment of the preferred of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the design of the present invention, equivalent replacement or change should be included in the protection scope of the present invention.

Claims

1. The utility model provides an unmanned aerial vehicle makes and uses wing intensity detection device, includes diaphragm (1), its characterized in that, two backup pads (2) of up end symmetry fixedly connected with of diaphragm (1), two the common fixedly connected with roof (3) of up end of backup pad (2), two hydraulic telescoping rod (4) of lower terminal surface symmetry fixedly connected with of roof (3), every the equal fixedly connected with connecting plate (5) of flexible end of hydraulic telescoping rod (4), every the lower terminal surface of connecting plate (5) all rotates and is connected with and draws pressure sensor (6), two draw the common fixedly connected with headstock (7) of lower extreme of pressure sensor (6), the up end fixedly connected with gear motor (8) of headstock (7), the output of gear motor (8) runs through the up end and fixedly connected with worm (9) of headstock (7), meshing is connected with worm wheel (10) on worm (9), the center department level fixed interlude of worm wheel (10) has inserted dwang (11), fixed cover has been connected with on dwang (11), gear (12) on gear wheel (12), meshing is connected with two-way threaded rod (13) on two-way threaded rod (14) of two-way fixed threaded rod (14), every the equal fixedly connected with pull rod (16) of one side of thread bush (15), two slide openings have been seted up to the lower terminal surface symmetry of fixed case (7), every the lower extreme of pull rod (16) all runs through slide opening and fixedly connected with electric telescopic handle (17), every the equal fixedly connected with clamping (18) of flexible end of electric telescopic handle (17).

2. The wing intensity detection device for unmanned aerial vehicle manufacturing of claim 1, characterized in that, two risers of symmetry fixedly connected with on the inner wall of fixed case (7), the both ends of dwang (11) are rotated respectively and are connected two on the lateral wall of riser.

3. The wing strength detection device for unmanned aerial vehicle manufacturing of claim 1, characterized in that two opposite threads are arranged on the bidirectional threaded rod (14), and both ends of the bidirectional threaded rod (14) are rotatably connected to the inner wall of the fixed box (7).

4. The wing strength detection device for unmanned aerial vehicle manufacturing of claim 1, characterized in that, both of the pull rods (16) are slidably connected in the inner wall of the sliding hole, and the diameter ratio between the first gear (12) and the second gear (13) is 1.

5. The wing strength detection device for unmanned aerial vehicle manufacturing of claim 1, characterized in that the lower end face of the transverse plate (1) is symmetrically and fixedly connected with four supporting legs, and the lower end of each supporting leg is fixedly connected with an antiskid base.