Aero seat sponge stretching degree detection platform

Abstract

The utility model relates to the technical field of stretching detection, in particular to an aero seat sponge stretching degree detection platform which comprises a workbench and a tension assembly, and the tension assembly comprises a clamping component, a tension detector, a supporting frame, a stretching air cylinder, a mounting plate, a transverse plate, a first clamping plate and a first air cylinder. One end of a to-be-tested sponge is clamped through the clamping component, then the other end of the to-be-tested sponge is clamped on the transverse plate through the first clamping plate controlled by the first air cylinder, after clamping is stable, the sponge is pulled through the stretching air cylinder, and in the pulling process, the tension detector is used for detecting the tension borne by the sponge in the stretching process; the supporting frame slides on the workbench to adjust the clamping position of the device so that the device can clamp sponges of different lengths, the supporting frame is driven to move through a driving mechanism, the driving mechanism is composed of a motor and a threaded rod, the motor drives the threaded rod to rotate, and therefore the supporting frame in threaded connection with the threaded rod is controlled to move.

Description

Technical Field

[0001] This utility model relates to the field of tensile testing technology, and in particular to a platform for testing the tensile strength of aircraft seat foam. Background Technology

[0002] With the development of the aviation industry, more and more people are choosing to travel by air, and airline seats are an important item among them. In order to improve comfort, foam is installed on the airline seat frame.

[0003] A sponge tensile strength testing device (CN221612561U) is available, including a worktable with four legs evenly fixedly installed at the bottom. A testing mechanism is installed on the worktable for testing the tensile strength of sponge. The fixing mechanism includes a motor, which is fixedly installed at the bottom of the worktable. A first support plate is fixedly installed on the worktable. A rotating rod is fixedly installed at the output end of the motor. The other end of the rotating rod is rotatably connected to the first support plate. The rotating rod is provided with two reverse external threads, and a first slider and a second slider are screwed onto the two reverse external threads respectively. Two first through holes are opened at the top of the worktable, and the first slider and the second slider pass through the two first through holes respectively. A U-shaped plate is fixedly installed on both the first slider and the second slider. A screw is screwed onto both U-shaped plates, and a clamping plate is rotatably installed at the bottom end of both screws.

[0004] However, the above-mentioned utility model requires adjusting the position of the clamping structure at both ends when testing sponges of different lengths and widths during use, resulting in low testing efficiency. Utility Model Content

[0005] The purpose of this invention is to provide an aircraft seat sponge tensile testing platform, which aims to solve the problem of low testing efficiency caused by the need to adjust the position of the clamping structures at both ends when testing sponges of different lengths and widths in existing devices.

[0006] To achieve the above objectives, this utility model provides an aircraft seat sponge tensile testing platform, including a worktable and a tension assembly. The tension assembly includes a clamping component, a tension detector, a support frame, a tension cylinder, a mounting plate, a horizontal plate, a first clamping plate, and a first cylinder.

[0007] The clamping component is mounted on the workbench. The support frame is slidably connected to the workbench and located on one side of the workbench. The tension cylinder is fixedly connected to the support frame and located on top of the support frame. The tension detector is fixedly connected to the output end of the tension cylinder and located on one side of the tension cylinder. The mounting plate is mounted on the output end of the tension detector. The first cylinder is fixedly connected to the mounting plate and located on one side of the mounting plate. The first clamping plate is fixedly connected to the output end of the first cylinder and located on one side of the first cylinder. The horizontal plate is fixedly mounted on the mounting plate.

[0008] The clamping component includes a vertical plate, a second cylinder, a second clamping plate, and a limiting plate. The vertical plate is fixedly connected to the worktable and located at the top of the worktable. The second cylinder is fixedly connected to the vertical plate and located on one side of the vertical plate. The second clamping plate is fixedly installed at the output end of the second cylinder. The limiting plate is fixedly connected to the vertical plate and located on the symmetrical side of the second clamping plate.

[0009] The tension assembly further includes a support cylinder and a pad. The support cylinder is slidably connected to the worktable and located on the top of the worktable. The pad is fixedly connected to the output end of the support cylinder and located on the top of the support cylinder.

[0010] The tension assembly further includes a controller and a computer. The controller is fixedly connected to the workbench and located on top of the workbench, and the computer is fixedly connected to the controller and located on top of the controller.

[0011] The tension assembly further includes a base plate and casters. The base plate is fixedly connected to the workbench and located on one side of the workbench. The casters are rotatably connected to the base plate and located at the bottom of the base plate.

[0012] This utility model discloses an aircraft seat sponge tensile testing platform. One end of the sponge to be tested is clamped by a clamping component, and the other end is clamped to a horizontal plate by a first clamping plate controlled by a first cylinder. After stable clamping, the sponge is pulled by a stretching cylinder. During the pulling process, a tension detector detects the tensile force on the sponge. The clamping position of the support frame is adjusted by sliding on the worktable, allowing the device to clamp sponges of different lengths. The support frame is driven to move by a drive mechanism consisting of a motor and a threaded rod. The motor drives the threaded rod to rotate, thereby controlling the movement of the support frame threadedly connected to the threaded rod. This solves the problem of low testing efficiency in existing devices that require adjusting the positions of the clamping structures at both ends when testing sponges of different lengths and widths. Attached Figure Description

[0013] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the accompanying drawings used in the description of the embodiments or the prior art will be briefly introduced below.

[0014] Figure 1 This is a structural diagram of an aircraft seat sponge tensile testing platform according to the present invention.

[0015] Figure 2 This is a side view of an aircraft seat sponge tensile testing platform according to the present invention.

[0016] 101-Workbench, 102-Tension assembly, 103-Clamping component, 104-Tension detector, 105-Support frame, 106-Tension cylinder, 107-Mounting plate, 108-Horizontal plate, 109-First clamping plate, 110-First cylinder, 111-Upright plate, 112-Second cylinder, 113-Second clamping plate, 114-Limiting plate, 115-Supporting cylinder, 116-Pad plate, 117-Controller, 118-Computer, 119-Base plate, 120-Wheel casters. Detailed Implementation

[0017] The embodiments of this utility model are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this utility model, and should not be construed as limiting this utility model.

[0018] First Embodiment

[0019] Please see Figures 1-2 , Figure 1 This is a structural diagram of an aircraft seat sponge tensile testing platform according to the present invention. Figure 2 This is a side view of an aircraft seat sponge tensile testing platform according to the present invention.

[0020] This utility model provides a platform for testing the tensile strength of aircraft seat foam, comprising a worktable 101 and a tension assembly 102. The tension assembly 102 includes a clamping component 103, a tension detector 104, a support frame 105, a tension cylinder 106, a mounting plate 107, a horizontal plate 108, a first clamping plate 109, a first cylinder 110, a vertical plate 111, a second cylinder 112, a second clamping plate 113, a limiting plate 114, a support cylinder 115, a pad 116, a controller 117, a computer 118, a base plate 119, and casters 120. This solution solves the problem of low testing efficiency in existing devices where the positions of the clamping structures at both ends need to be adjusted when testing foams of different lengths and widths.

[0021] In this embodiment, the clamping member 103 is mounted on the workbench 101. The support frame 105 is slidably connected to the workbench 101 and located on one side of the workbench 101. The tension cylinder 106 is fixedly connected to the support frame 105 and located on top of the support frame 105. The tension detector 104 is fixedly connected to the output end of the tension cylinder 106 and located on one side of the tension cylinder 106. The mounting plate 107 is mounted on the output end of the tension detector 104. The first cylinder 110 is fixedly connected to the mounting plate 107 and located on one side of the mounting plate 107. The first clamping plate 109 is fixedly connected to the output end of the first cylinder 110 and located on one side of the first cylinder 110. The horizontal plate 108 is fixedly mounted on the mounting plate. 103 clamps one end of the sponge to be tested, and then clamps the other end onto the horizontal plate 108 by the first clamping plate 109 controlled by the first cylinder 110. After the clamping is stable, the sponge is pulled by the stretching cylinder 106. During the pulling process, the tension detector 104 is used to detect the tension force on the sponge. The support frame 105 slides on the worktable 101 to adjust the clamping position of the device, so that the device can clamp sponges of different lengths. The support frame 105 is driven to move by a drive mechanism, which consists of a motor and a threaded rod. The motor drives the threaded rod to rotate, thereby controlling the movement of the support frame 105 threadedly connected to the threaded rod. This solves the problem of low testing efficiency caused by the need to adjust the position of the clamping structure at both ends when testing sponges of different lengths and widths in the existing device.

[0022] The clamping member 103 includes a vertical plate 111, a second cylinder 112, a second clamping plate 113, and a limiting plate 114. The vertical plate 111 is fixedly connected to the worktable 101 and is located on the top of the worktable 101. The second cylinder 112 is fixedly connected to the vertical plate 111 and is located on one side of the vertical plate 111. The second clamping plate 113 is fixedly installed at the output end of the second cylinder 112. The limiting plate 114 is fixedly connected to the vertical plate 111 and is located on the symmetrical side of the second clamping plate 113. The vertical plate 111 is used to install the second cylinder 112. The second cylinder 112 controls the second clamping plate 113 to move toward the limiting plate 114, thereby clamping one end of the sponge through the second clamping plate 113 and the limiting plate 114.

[0023] Secondly, the tension assembly 102 also includes a support cylinder 115 and a pad 116. The support cylinder 115 is slidably connected to the worktable 101 and is located on the top of the worktable 101. The pad 116 is fixedly connected to the output end of the support cylinder 115 and is located on the top of the support cylinder 115. The support cylinder 115 controls the movement of the pad 116 to lift the bottom of the sponge during the installation process, preventing long sponges from sagging and causing installation inconvenience.

[0024] Furthermore, the tension assembly 102 also includes a controller 117 and a computer 118. The controller 117 is fixedly connected to the workbench 101 and located on top of the workbench 101. The computer 118 is fixedly connected to the controller 117 and located on top of the controller 117. The controller 117 is used to control the use of the device. The computer 118 is installed on the controller 117 and records the observed and detected data through the computer 118.

[0025] Finally, the tension assembly 102 also includes a base plate 119 and casters 120. The base plate 119 is fixedly connected to the workbench 101 and is located on one side of the workbench 101. The casters 120 are rotatably connected to the base plate 119 and are located at the bottom of the base plate 119. The base plate 119 is used to install the casters 120. The casters 120 reduce the friction between the device and the ground, making it easier to move the device. The casters 120 are provided with a locking mechanism to lock the casters 120 to prevent the device from moving during testing.

[0026] In the aviation seat sponge tensile testing platform of this utility model, one end of the sponge to be tested is clamped by the clamping member 103, and the other end is clamped on the horizontal plate 108 by the first clamping plate 109 controlled by the first cylinder 110. After the clamping is stable, the sponge is pulled by the stretching cylinder 106. During the pulling process, the tension detector 104 is used to detect the tension force on the sponge. The support frame 105 slides on the worktable 101 to adjust the clamping position of the device, so that the device can clamp sponges of different lengths. The support frame 105 is driven to move by a drive mechanism, which consists of a motor and a threaded rod. The motor drives the threaded rod to rotate, thereby controlling the movement of the support frame 105 threadedly connected to the threaded rod. This solves the problem of low testing efficiency caused by the need to adjust the position of the clamping structure at both ends when testing sponges of different lengths and widths in existing devices.

[0027] The above-disclosed embodiments are merely preferred embodiments of the aircraft seat sponge stretchability testing platform of this utility model, and should not be construed as limiting the scope of this utility model. Those skilled in the art can understand that implementing all or part of the above embodiments and making equivalent changes in accordance with the claims of this utility model still fall within the scope of this utility model.

Claims

1. A platform for testing the stretchability of aircraft seat foam, comprising a worktable, characterized in that: It also includes a tension assembly, which includes a clamping member, a tension detector, a support frame, a tension cylinder, a mounting plate, a cross plate, a first clamping plate, and a first cylinder; The clamping component is mounted on the workbench. The support frame is slidably connected to the workbench and located on one side of the workbench. The tension cylinder is fixedly connected to the support frame and located on top of the support frame. The tension detector is fixedly connected to the output end of the tension cylinder and located on one side of the tension cylinder. The mounting plate is mounted on the output end of the tension detector. The first cylinder is fixedly connected to the mounting plate and located on one side of the mounting plate. The first clamping plate is fixedly connected to the output end of the first cylinder and located on one side of the first cylinder. The horizontal plate is fixedly mounted on the mounting plate.

2. The aircraft seat foam tensile testing platform as described in claim 1, characterized in that: The clamping component includes a vertical plate, a second cylinder, a second clamping plate, and a limiting plate. The vertical plate is fixedly connected to the worktable and located at the top of the worktable. The second cylinder is fixedly connected to the vertical plate and located on one side of the vertical plate. The second clamping plate is fixedly installed at the output end of the second cylinder. The limiting plate is fixedly connected to the vertical plate and located on the symmetrical side of the second clamping plate.

3. The aircraft seat foam tensile testing platform as described in claim 2, characterized in that: The tension assembly also includes a support cylinder and a pad. The support cylinder is slidably connected to the worktable and located on the top of the worktable. The pad is fixedly connected to the output end of the support cylinder and located on the top of the support cylinder.

4. The aircraft seat foam tensile testing platform as described in claim 3, characterized in that: The tension assembly also includes a controller and a computer. The controller is fixedly connected to the workbench and located on top of the workbench, and the computer is fixedly connected to the controller and located on top of the controller.

5. The aircraft seat foam tensile testing platform as described in claim 4, characterized in that: The tension assembly also includes a base plate and casters. The base plate is fixedly connected to the workbench and located on one side of the workbench. The casters are rotatably connected to the base plate and located at the bottom of the base plate.

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