Aircraft detection platform

Abstract

The utility model provides an aircraft detection platform, and belongs to the technical field of aircraft detection platforms. The aircraft detection platform comprises a rack, a detection assembly and a protection assembly. The rack comprises a bottom plate and a top plate, and the bottom plate and the top plate are connected through supporting columns; the detection assembly comprises a hydraulic cylinder, a support part and a clamping part, the support part is arranged above the bottom plate, the clamping part is installed above the support part, the hydraulic cylinder is installed at the top of the top plate, the rod end of the hydraulic cylinder movably penetrates through the top plate, a pressure sensor is arranged at the output rod end of the hydraulic cylinder, and a pressing plate is fixed to the bottom of the pressure sensor. And the transparent door plate is stably covered between the first panel and the second panel through the magnetic attraction matching of the magnet block and the metal block. The hydraulic cylinder pushes the pressure sensor and the pressing plate to press the part for compression resistance detection, fragments generated by the part in the detection process can be shielded by the transparent door plate, the first panel and the second panel even if the fragments splash, and an operator is well protected.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft testing platforms, in particular to an aircraft testing platform. Background Art

[0002] During the development and production stage of the outer shell and other parts of different batches of aircraft, it is necessary to conduct compression tests on the hardness of the outer shell. For example, the public document with announcement number CN210681192U describes a pressure and detection device for aircraft parts processing, including a base and a hydraulic cylinder, a first slide is fixed on both sides of the left and right sides of the base, and the first slide is slidably connected to a pull-out box, a controller is fixed on the front side of the base, and a gravity sensor and a second slide are embedded on the upper side of the base. The above-mentioned detection device can perform compressive strength tests on aircraft parts, but when the shell parts are crushed under pressure, fragments may fly, which will threaten the physical safety of the operator and pose certain safety hazards. Utility Model Content

[0003] In order to make up for the above deficiencies, the utility model provides an aircraft inspection platform, which aims to improve the problem in the related technology that when aircraft shell parts are crushed under pressure, fragments may fly, which will pose a threat to the physical safety of the operator.

[0004] The utility model is achieved in this way:

[0005] The utility model provides an aircraft detection platform, which comprises a frame, a detection component and a protection component.

[0006] The frame comprises a bottom plate and a top plate, and the bottom plate and the top plate are connected by support columns;

[0007] The detection assembly includes a hydraulic cylinder, a support portion and a clamping portion, wherein the support portion is arranged above the bottom plate, the clamping portion is installed above the support portion, the hydraulic cylinder is installed on the top of the top plate, and the rod end of the hydraulic cylinder movably penetrates the top plate, the output rod end of the hydraulic cylinder is provided with a pressure sensor, and a pressure plate is fixed at the bottom of the pressure sensor;

[0008] The protective component includes a first panel, a second panel and a transparent door panel, the first panel and the second panel are respectively arranged on the front sides of the bottom plate and the top plate, the transparent door panel is hinged to the first panel, a magnet block is arranged on the front side of the second panel, a handle is installed on the outer side of the transparent door panel, and a metal block magnetically matched with the magnet block is arranged on the inner side of the transparent door panel.

[0009] In one embodiment of the utility model, the support portion includes a base and a support plate, the base is fixed above the bottom plate, a first threaded rod is rotatably provided on the base, a first hand wheel is installed at one end of the first threaded rod, and the first threaded rod is threadedly connected to and passes through the support plate.

[0010] In an embodiment of the utility model, a through slot is provided on the top of the base, a support block is slidably provided inside the through slot, and the first threaded rod is threadedly connected and passes through the support block.

[0011] In an embodiment of the present invention, end covers are fixed at both ends of the through slot, and the end of the first threaded rod rotates and passes through the end covers.

[0012] In an embodiment of the utility model, a slide groove is arranged on the top of the base, and the sliding block fixedly connected to the support plate is slidably arranged inside the slide groove.

[0013] In one embodiment of the utility model, the clamping part includes a clamping seat and a clamping plate, the clamping seat is fixed above the support plate, the clamping plate is slidably arranged above the clamping seat, a second threaded rod is rotatably arranged at the bottom of the clamping plate, and a second hand wheel is arranged at one end of the second threaded rod away from the clamping plate.

[0014] In an embodiment of the present invention, elastic gaskets are provided on opposite sides of the clamping seat and the clamping plate.

[0015] In an embodiment of the present invention, opposite sides of the bottom plate and the top plate are respectively provided with card slots matching with the first panel and the second panel.

[0016] The beneficial effects of the utility model are as follows: the utility model obtains an aircraft inspection platform through the above design, and the transparent door panel is firmly covered between the first panel and the second panel through the magnetic attraction of the magnet block and the metal block. The hydraulic cylinder pushes the pressure sensor and the pressure plate to press the parts to perform pressure resistance testing. Even if the fragments generated by the parts during the testing process are splashed, they will be blocked by the transparent door panel, the first panel and the second panel, which has a good protective effect on the operator. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solution of the implementation mode of the utility model, the drawings required for use in the implementation mode will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the utility model and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying creative work.

[0018] Figure 1It is a schematic diagram of the structure of an aircraft test bench provided by an embodiment of the utility model;

[0019] Figure 2 A schematic diagram of the structure of the rack and detection components provided for the implementation of the utility model;

[0020] Figure 3 A schematic diagram of the support structure without a support plate provided in an embodiment of the utility model;

[0021] Figure 4 A schematic diagram of the support plate and slider structure provided in the embodiment of the utility model;

[0022] Figure 5 A schematic diagram of the expanded structure of the protection component provided in an embodiment of the utility model.

[0023] In the figure: 10-frame; 110-bottom plate; 120-top plate; 130-support column; 20-detection component; 210-hydraulic cylinder; 220-pressure sensor; 230-pressing plate; 240-support part; 241-base; 242-support plate; 243-first threaded rod; 244-first hand wheel; 245-slide groove; 246-slider; 247-support block; 250-clamping part; 251-clamping seat; 252-clamping plate; 253-second threaded rod; 254-second hand wheel; 30-protection component; 310-first panel; 320-second panel; 330-transparent door panel; 340-handle; 350-magnet block; 360-metal block. DETAILED DESCRIPTION

[0024] In order to make the purpose, technical solution and advantages of the implementation of the utility model clearer, the technical solution in the implementation of the utility model will be clearly and completely described below in conjunction with the drawings in the implementation of the utility model. Obviously, the described implementation is a part of the implementation of the utility model, not all of the implementations. Based on the implementation of the utility model, all other implementations obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0025] Example

[0026] See also Figure 1-Figure 5 The utility model provides an aircraft inspection platform, including a frame 10, a detection component 20 and a protection component 30.

[0027] Among them, the frame 10 is used to support the detection component 20 and the protection component 30. The detection component 20 can perform pressure resistance tests on components such as the aircraft shell, and the protection component 30 plays a good role in protecting against flying debris, that is, it has a good protective effect on the operator.

[0028] See also Figure 1 , Figure 2 and Figure 5 The frame 10 includes a bottom plate 110 and a top plate 120. The bottom plate 110 and the top plate 120 are connected by a support column 130. The detection component 20 includes a hydraulic cylinder 210, a support portion 240 and a clamping portion 250, and the support portion 240 is arranged above the bottom plate 110. The clamping portion 250 is installed above the support portion 240, the hydraulic cylinder 210 is installed on the top of the top plate 120, and the rod end of the hydraulic cylinder 210 movably passes through the top plate 120, the output rod end of the hydraulic cylinder 210 is provided with a pressure sensor 220, and a pressure plate 230 is fixed at the bottom of the pressure sensor 220. The protection component 30 includes a first panel 310, a second panel 320 and a transparent door panel 330. The first panel 310 and the second panel 320 are respectively arranged on the front sides of the bottom plate 110 and the top plate 120, the transparent door panel 330 is hinged to the first panel 310, a magnet block 350 is arranged on the front side of the second panel 320, a handle 340 is installed on the outside of the transparent door panel 330, and a metal block 360 magnetically matched with the magnet block 350 is arranged on the inside of the transparent door panel 330.

[0029] The transparent door panel 330 is opened by the handle 340, and the aircraft parts to be inspected are placed on the clamping part 250 for clamping and fixing. The transparent door panel 330 is firmly covered between the first panel 310 and the second panel 320 by the magnetic attraction of the magnet block 350 and the metal block 360. The hydraulic cylinder 210 pushes the pressure sensor 220 and the pressure plate 230 to press the parts for pressure resistance testing. Even if the debris generated by the parts during the testing process is splashed, it will be blocked by the transparent door panel 330, the first panel 310 and the second panel 320, which has a good protective effect on the operator.

[0030] The transparent door panel 330 may be a transparent acrylic door panel, so that the operator can observe the pressure test process of the rear parts.

[0031] In the above specific implementation, please refer to Figure 3 and Figure 4The support portion 240 includes a base 241 and a support plate 242. The base 241 is fixed above the bottom plate 110. A first threaded rod 243 is rotatably provided on the base 241, and a first hand wheel 244 is installed at one end of the first threaded rod 243. The first threaded rod 243 is screwed through the support plate 242. A through slot is provided at the top of the base 241, and a support block 247 is slidably provided inside the through slot. The first threaded rod 243 is screwed through the support block 247. End caps are fixed at both ends of the through slot, and the end of the first threaded rod 243 is rotatably provided through the end cap. Rotating the first hand wheel 244 drives the first threaded rod 243 to rotate, and the rotating first threaded rod 243 drives the support plate 242 to move through the support block 247, that is, drives the upper clamping portion 250 to move and adjust.

[0032] Furthermore, a slide groove 245 is provided on the top of the base 241, and a slider 246 fixedly connected to the support plate 242 is slidably provided inside the slide groove 245. The provision of the slide groove 245 and the slider 246 enhances the stability of the support plate 242 when it moves.

[0033] For specific settings, see Figure 2 The clamping part 250 includes a clamping seat 251 and a clamping plate 252. The clamping seat 251 is fixed above the support plate 242. The clamping plate 252 is slidably arranged above the clamping seat 251. A second threaded rod 253 is rotatably arranged at the bottom of the clamping plate 252, and a second hand wheel 254 is arranged at one end of the second threaded rod 253 away from the clamping plate 252. The second hand wheel 254 is rotated to drive the clamping plate 252 to move, and cooperate with the clamping seat 251 to fix the parts. Elastic gaskets are arranged on the opposite sides of the clamping seat 251 and the clamping plate 252. The arrangement of the elastic gasket is to increase the stability when clamping the parts.

[0034] Furthermore, the bottom plate 110 and the top plate 120 are provided with slots on opposite sides thereof respectively, which are matched with the first panel 310 and the second panel 320. The first panel 310 and the second panel 320 are inserted into the slots at both ends respectively, and then fixedly connected by bolts.

[0035] It should be noted that the specific model specifications of the hydraulic cylinder 210 and the pressure sensor 220 need to be selected and determined according to the actual specifications of the device, and the specific selection calculation method adopts the existing technology in the field, so it will not be described in detail. The power supply and principle of the hydraulic cylinder 210 and the pressure sensor 220 are clear to those skilled in the art and will not be described in detail here.

[0036] The working principle of the aircraft inspection platform is as follows: when in use, the transparent door panel 330 is opened by the handle 340, and the aircraft parts to be inspected are placed on the clamping part 250 for clamping and fixing. Through the magnetic attraction of the magnet block 350 and the metal block 360, the transparent door panel 330 is firmly covered between the first panel 310 and the second panel 320. The hydraulic cylinder 210 pushes the pressure sensor 220 and the pressure plate 230 to press the parts for pressure resistance testing. Even if the debris generated by the parts during the inspection process is splashed, it will be blocked by the transparent door panel 330, the first panel 310 and the second panel 320, which has a good protective effect on the operator.

[0037] The above description is only the preferred implementation of the utility model, and is not intended to limit the utility model. For those skilled in the art, the utility model can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.

Claims

1. An aircraft testing station, characterized in that: include A frame (10), the frame (10) comprising a bottom plate (110) and a top plate (120), the bottom plate (110) and the top plate (120) being connected via a support column (130); A detection assembly (20), the detection assembly (20) comprising a hydraulic cylinder (210), a support portion (240) and a clamping portion (250), the support portion (240) being arranged above the bottom plate (110), the clamping portion (250) being installed above the support portion (240), the hydraulic cylinder (210) being installed on the top of the top plate (120), and the rod end of the hydraulic cylinder (210) being movable and penetrating through the top plate (120), the output rod end of the hydraulic cylinder (210) being provided with a pressure sensor (220), and a pressure plate (230) being fixed at the bottom of the pressure sensor (220); A protective component (30), the protective component (30) comprising a first panel (310), a second panel (320) and a transparent door panel (330), the first panel (310) and the second panel (320) being respectively arranged on the front sides of both ends of the bottom panel (110) and the top panel (120), the transparent door panel (330) being hinged to the first panel (310), a magnet block (350) being arranged on the front side of the second panel (320), a handle (340) being installed on the outer side of the transparent door panel (330), and a metal block (360) being magnetically matched with the magnet block (350) being arranged on the inner side of the transparent door panel (330).

2. An aircraft test bench according to claim 1, characterized in that: The support portion (240) comprises a base (241) and a support plate (242); the base (241) is fixed above the bottom plate (110); a first threaded rod (243) is rotatably arranged on the base (241); a first hand wheel (244) is installed at one end of the first threaded rod (243); the first threaded rod (243) is threadedly connected to and passes through the support plate (242).

3. An aircraft test bench according to claim 2, characterized in that: A through slot is provided at the top of the base (241), a support block (247) is slidably provided inside the through slot, and the first threaded rod (243) is threadedly connected and passes through the support block (247).

4. An aircraft test bench according to claim 3, characterized in that: End covers are fixed at both ends of the through slot, and the end of the first threaded rod (243) rotates and passes through the end covers.

5. The aircraft test bench according to claim 2, characterized in that: A slide groove (245) is provided on the top of the base (241), and a sliding block (246) fixedly connected to the support plate (242) is slidably provided inside the slide groove (245).

6. The aircraft test bench according to claim 2, characterized in that: The clamping portion (250) comprises a clamping seat (251) and a clamping plate (252), wherein the clamping seat (251) is fixed above the support plate (242), and the clamping plate (252) is slidably arranged above the clamping seat (251), a second threaded rod (253) is rotatably arranged at the bottom of the clamping plate (252), and a second hand wheel (254) is arranged at one end of the second threaded rod (253) away from the clamping plate (252).

7. An aircraft testing platform according to claim 6, characterized in that: Elastic gaskets are provided on opposite sides of the clamping seat (251) and the clamping plate (252).

8. The aircraft test bench according to claim 1, characterized in that: The opposite sides of the bottom plate (110) and the top plate (120) are respectively provided with card slots that match the first panel (310) and the second panel (320).

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