An aviation wire experimental workbench

Abstract

The invention discloses an aviation wire experimental workbench, which drives the output shaft of the servo motor to rotate, thereby driving the eccentric roller to rotate axially. The eccentric wheel is installed between the inner and outer rings of the eccentric guide ring, so that the eccentric roller slides between the eccentric guide rings, drives the steering connection block to rotate with the axis of the eccentric roller as the center point, drives the connecting slide bar to slide up and down in the guide cylinder, thereby driving the back plate to vibrate up and down. Since the wire is installed on the inner side of the back plate and the skin is installed on the outer side of the back plate, the reagent working condition of the wire inside the aircraft is simulated, and the experimental result of the wire is more credible.

Description

Technical Field

[0001] The invention relates to the technical field of aviation equipment, in particular to an aviation wire experimental workbench. Background Art

[0002] At present, the aerospace industry has been in need of a cable that can guarantee high reliability, light weight, clean, soft and low toxicity in harsh environments. Special cables are cables with special uses and can be used in specific occasions, such as cables that are resistant to high temperatures, acids and alkalis, and termites, as well as wires and cables used in ships, aircraft, nuclear power plants and other occasions. In terms of classification, it does not belong to the same classification method as power, control, computer cables and other categories, that is, the above-listed cables also include special cables. Generally, special cables require the formulation of enterprise internal control standards. Special cables are a series of products with unique properties and special structures. Compared with ordinary wires and cables with large quantities and wide applications, they have the characteristics of higher technical content, stricter use conditions, smaller batches and higher added value.

[0003] After the aviation wires are actually assembled on the aircraft, the protective layer of the aviation wires is easily worn out due to the long-term use of the aircraft. However, there is currently no experimental workbench that can well simulate the actual working conditions of the aircraft during flight, making it impossible to accurately obtain the simulation test results of the aviation wires. Summary of the invention

[0004] The purpose of the present invention is to provide an aviation wire experimental workbench, aiming to solve the technical problems in the prior art.

[0005] To achieve the above-mentioned purpose, the present invention adopts an aviation wire experimental workbench, which includes a platform, a wire and a supporting device; the wire is connected to the platform through the supporting device and is located on one side of the platform; the supporting device includes a supporting plate, a back plate, a skin and a vibration assembly, the supporting plate is fixedly connected to the platform and is located on the side of the platform close to the wire, the back plate is slidably connected to the supporting plate and is fixedly connected to the wire and is located on the side of the supporting plate away from the platform, the skin is fixedly connected to the back plate and is located on the side of the back plate away from the wire; the vibration assembly includes a guide cylinder, a connecting slide bar, a servo motor and an eccentric member, the guide cylinder is fixedly connected to the support plate and passes through the support plate and is located between the platform and the back plate, one end of the connecting slide bar is fixedly connected to the back plate, and the other end passes through the guide cylinder and partially extends into the platform, the servo motor is fixedly connected to the platform, and the output shaft is rotationally connected to the connecting slide bar through the eccentric member, and is located on the side of the platform close to the connecting slide bar.

[0006] Wherein, the eccentric component includes an eccentric guide ring and an eccentric roller. The eccentric guide ring is fixedly connected to the connecting slide rod and is located on a side of the connecting slide rod close to the servo motor. The eccentric roller is rotatably connected to the eccentric guide ring and is fixedly connected to the output end of the servo motor and is located on a side of the eccentric guide ring close to the servo motor.

[0007] Wherein, the eccentric component also includes a steering connection block, which is rotatably connected to the connecting slide rod and fixedly connected to the eccentric guide ring, and is located on a side of the connecting slide rod close to the eccentric guide ring.

[0008] Wherein, the eccentric component also includes a connecting shaft, which is fixedly connected to the steering connecting block and rotatably connected to the connecting slide rod, and is located on a side of the steering connecting block close to the connecting slide rod.

[0009] Wherein, the eccentric component also includes a connecting bearing, which is fixedly connected to the connecting slide rod and rotatably connected to the connecting shaft, and is located on a side of the connecting slide rod close to the connecting shaft.

[0010] Wherein, the vibration assembly also includes a hydraulic cylinder and a telescopic rod, the hydraulic cylinder is fixedly connected to the support plate and is located on the side of the support plate close to the back plate; one end of the telescopic rod is fixedly connected to the output end of the hydraulic cylinder, and the other end is rotatably connected to the support plate and is located between the hydraulic cylinder and the back plate.

[0011] Wherein, the vibration assembly also includes a steering bearing, which is fixedly connected to the back plate and rotatably connected to the telescopic rod, and is located on a side of the back plate close to the telescopic rod.

[0012] Wherein, the supporting device further comprises a wire clamp, which is fixedly connected to the back plate, abuts against the wire, and is located on a side of the back plate close to the wire.

[0013] Wherein, the supporting device further comprises a back plate coating, wherein the back plate coating is fixedly connected to the skin and is located on a side of the skin away from the back plate.

[0014] An aviation wire experimental workbench of the present invention drives the output shaft of the servo motor to rotate, thereby driving the eccentric roller to rotate axially. The eccentric wheel is installed between the inner and outer rings of the eccentric guide ring, so that the eccentric roller slides between the eccentric guide rings, driving the steering connection block to rotate with the axis of the eccentric roller as the center point, driving the connecting slide bar to slide up and down in the guide cylinder, thereby driving the back plate to vibrate up and down. Since the wire is installed on the inner side of the back plate and the skin is installed on the outer side of the back plate, the reagent working condition of the wire inside the aircraft is simulated, and the experimental result of the wire is more credible. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0016] Figure 1 It is a schematic structural diagram of the vibration component of the present invention.

[0017] Figure 2 It is a schematic diagram of the internal structure of the platform body of the present invention.

[0018] Figure 3 It is a structural schematic diagram of the eccentric component of the present invention.

[0019] Figure 4 It is a structural schematic diagram of the supporting device of the present invention.

[0020] In the figure: 1- platform, 2- conductor, 3- supporting device, 31- supporting plate, 32- back plate, 33- skin, 34- vibration assembly, 35- wire clamp, 36- back plate coating, 100- aviation conductor experimental workbench, 341- guide cylinder, 342- connecting slide rod, 343- servo motor, 344- eccentric member, 345- hydraulic cylinder, 346- telescopic rod, 347- steering bearing, 3441- eccentric guide ring, 3442- eccentric roller, 3443- steering connecting block, 3444- connecting shaft, 3445- connecting bearing. DETAILED DESCRIPTION

[0021] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0022] In the description of the present invention, it should be understood that the terms "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, in the description of the present invention, "multiple" means two or more, unless otherwise clearly and specifically defined.

[0023] See also Figures 1 to 4 The present invention provides an aviation wire experimental workbench 100, comprising a platform 1, a wire 2 and a supporting device 3; the wire 2 is connected to the platform 1 through the supporting device 3 and is located on one side of the platform 1; the supporting device 3 comprises a supporting plate 31, a back plate 32, a skin 33 and a vibration assembly 34, the supporting plate 31 is fixedly connected to the platform 1 and is located on a side of the platform 1 close to the wire 2, the back plate 32 is slidably connected to the supporting plate 31, and is fixedly connected to the wire 2 and is located on a side of the supporting plate 31 away from the platform 1, the skin 33 is fixedly connected to the back plate 32 and is located on a side of the back plate 32 away from the One side of the wire 2; the vibration assembly 34 includes a guide cylinder 341, a connecting slide 342, a servo motor 343 and an eccentric member 344, the guide cylinder 341 is fixedly connected to the support plate 31, passes through the support plate 31, and is located between the table 1 and the back plate 32, one end of the connecting slide 342 is fixedly connected to the back plate 32, and the other end passes through the guide cylinder 341, and partially extends into the table 1, the servo motor 343 is fixedly connected to the table 1, and the output shaft is rotatably connected to the connecting slide 342 through the eccentric member 344, and is located on the side of the table 1 close to the connecting slide 342.

[0024] For further information, see Figure 3 The eccentric component 344 includes an eccentric guide ring 3441 and an eccentric roller 3442. The eccentric guide ring 3441 is fixedly connected to the connecting slide rod 342 and is located on a side of the connecting slide rod 342 close to the servo motor 343. The eccentric roller 3442 is rotatably connected to the eccentric guide ring 3441 and is fixedly connected to the output end of the servo motor 343 and is located on a side of the eccentric guide ring 3441 close to the servo motor 343.

[0025] For further information, see Figure 3 and Figure 4The eccentric component 344 also includes a steering connection block 3443, which is rotatably connected to the connecting slide rod 342 and fixedly connected to the eccentric guide ring 3441, and is located on a side of the connecting slide rod 342 close to the eccentric guide ring 3441.

[0026] In this embodiment, the platform 1 is placed on the ground, and the interior of the platform 1 is hollow, and the top of the platform 1 has an opening, the support plate 31 is threadedly installed at the top opening of the platform 1, the support plate 31 has a through hole, the guide cylinder 341 is installed in the through hole of the support plate 31 and penetrates the through hole of the support plate 31, the interior of the guide cylinder 341 is hollow, the connecting slide rod 342 is slidably installed in the interior of the guide cylinder 341, and the top is rotatably connected to the support plate 31 The bottom is rotatably connected with the steering connection block 3443, and the steering connection block 3443 swings left and right through the rotating shaft and the bottom of the connecting slide bar 342, and the eccentric guide ring 3441 is threadedly installed on the surface of the steering connection block 3443, and the eccentric guide ring 3441 includes an inner ring and an outer ring, and the eccentric roller 3442 is rotatably installed inside the eccentric guide ring 3441, one side of the eccentric roller 3442 is threadedly fixed with the output shaft of the servo motor 343, and the other side has a thread, The eccentric roller 3442 is rotatably connected to the inner and outer rings of the eccentric guide ring 3441 through a thread, and the inner and outer rings of the eccentric guide ring 3441 slide and limit the outer side of the eccentric roller 3442, so that the eccentric roller 3442 can only slide between the inner and outer rings of the eccentric guide ring 3441. In this way, the output shaft of the servo motor 343 is driven to rotate, which drives the eccentric roller 3442 to rotate axially. The eccentric wheel is installed between the inner and outer rings of the eccentric guide ring 3441, so that the eccentric roller 3442 can slide only between the inner and outer rings of the eccentric guide ring 3441. The center roller 3442 slides between the eccentric guide rings 3441, driving the steering connection block 3443 to rotate with the axis of the eccentric roller 3442 as the center point, driving the connecting slide rod 342 to slide up and down in the guide cylinder 341, thereby driving the back plate 32 to vibrate up and down. Since the wire 2 is installed on the inner side of the back plate 32 and the skin 33 is installed on the outer side of the back plate 32, the actual working condition of the wire 2 inside the aircraft is simulated, and the experimental results of the wire 2 are more credible.

[0027] For further information, see Figure 2 The eccentric member 344 also includes a connecting shaft 3444, which is fixedly connected to the steering connecting block 3443 and rotatably connected to the connecting slide rod 342, and is located on a side of the steering connecting block 3443 close to the connecting slide rod 342.

[0028] In this embodiment, the connecting shaft 3444 is threadedly fixed to the steering connecting block 3443 and axially rotates with the connecting slide rod 342, thereby driving the steering connecting block 3443 and the connecting slide rod 342 to rotate. When the servo motor 343 drives the eccentric roller 3442 to slide in the eccentric guide ring 3441, it drives the steering connecting block 3443 to swing, and the connecting shaft 3444 enables the steering connecting block 3443 to rotate with the connecting slide rod 342.

[0029] For further information, see Figure 3 The eccentric member 344 also includes a connecting bearing 3445, which is fixedly connected to the connecting slide rod 342 and rotatably connected to the connecting shaft 3444, and is located on a side of the connecting slide rod 342 close to the connecting shaft 3444.

[0030] In this embodiment, the outer ring of the connecting bearing 3445 is threadedly fixed on the connecting slide rod 342, and is connected to the connecting shaft 3444 through the inner ring, and is driven to rotate by the balls between the outer ring and the inner ring. There are two connecting bearings 3445, which are respectively installed at both ends of the connecting shaft 3444, so that the rotation of the connecting shaft 3444 and the connecting slide rod 342 is more stable.

[0031] For further information, see Figure 1 The vibration assembly 34 also includes a hydraulic cylinder 345 and a telescopic rod 346. The hydraulic cylinder 345 is fixedly connected to the support plate 31 and is located on the side of the support plate 31 close to the back plate 32; one end of the telescopic rod 346 is fixedly connected to the output end of the hydraulic cylinder 345, and the other end is rotatably connected to the support plate 31 and is located between the hydraulic cylinder 345 and the back plate 32.

[0032] In this embodiment, the hydraulic cylinder 345 is threadedly fixed on the top of the support plate 31, and the telescopic rod 346 is installed on the top of the hydraulic cylinder 345. The telescopic rod 346 supports the end of the back plate 32, and the telescopic rod 346 cooperates with the up and down sliding of the connecting slide rod 342 through the telescopic movement of the telescopic rod 346, so that the back plate 32 shakes back and forth, thereby simulating the turbulence of the aircraft.

[0033] For further information, see Figure 1 The vibration assembly 34 also includes a steering bearing 347 , which is fixedly connected to the back plate 32 and rotatably connected to the telescopic rod 346 , and is located on a side of the back plate 32 close to the telescopic rod 346 .

[0034] In this embodiment, a transverse rod is installed at the end of the telescopic rod 346, and the steering bearing 347 is threadedly fixed on the back plate 32 and is rotatably connected to the transverse rod at the end of the telescopic rod 346, so that the back plate 32 and the telescopic rod 346 rotate, thereby causing the back plate 32 to shake.

[0035] For further information, see Figure 4 The supporting device 3 also includes a wire clamp 35 , which is fixedly connected to the back plate 32 , abuts against the wire 2 , and is located on a side of the back plate 32 close to the wire 2 .

[0036] In this embodiment, the wire clamp 35 is threadedly fixed on the inner side of the back plate 32 , and the wire 2 is clamped and fixed by a limit card, so that the installation of the wire 2 is more stable.

[0037] For further information, see Figure 4 The supporting device 3 further includes a back plate coating 36 , which is fixedly connected to the skin 33 and is located on a side of the skin 33 away from the back plate 32 .

[0038] In this embodiment, the back panel coating 36 is the coating of the skin 33 of the aircraft, and is coated on the surface of the skin 33 to simulate the coating layer on the outer surface of the aircraft.

[0039] What is disclosed above is only a preferred embodiment of the present invention, and it certainly cannot be used to limit the scope of rights of the present invention. Ordinary technicians in this field can understand that all or part of the processes of the above embodiment and equivalent changes made according to the claims of the present invention still fall within the scope of the invention.

Claims

1. An aviation wire experimental workbench, characterized in that: It includes a platform, a conductor and a supporting device; The wire is connected to the platform through the supporting device and is located on one side of the platform; The support device comprises a support plate, a back plate, a skin and a vibration assembly, wherein the support plate is fixedly connected to the platform and is located on a side of the platform close to the wire, the back plate is slidably connected to the support plate and is fixedly connected to the wire and is located on a side of the support plate away from the platform, and the skin is fixedly connected to the back plate and is located on a side of the back plate away from the wire; The vibration assembly includes a guide cylinder, a connecting slide rod, a servo motor and an eccentric member. The guide cylinder is fixedly connected to the support plate, passes through the support plate, and is located between the platform and the back plate. One end of the connecting slide rod is fixedly connected to the back plate, and the other end passes through the guide cylinder and partially extends into the platform. The servo motor is fixedly connected to the platform, and the output shaft is rotationally connected to the connecting slide rod through the eccentric member, and is located on a side of the platform close to the connecting slide rod. The eccentric member includes an eccentric guide ring and an eccentric roller, wherein the eccentric guide ring is fixedly connected to the connecting slide bar and is located on a side of the connecting slide bar close to the servo motor, and the eccentric roller is rotatably connected to the eccentric guide ring and is fixedly connected to an output end of the servo motor and is located on a side of the eccentric guide ring close to the servo motor; The eccentric component further comprises a steering connection block, which is rotatably connected to the connecting slide bar and fixedly connected to the eccentric guide ring, and is located on a side of the connecting slide bar close to the eccentric guide ring; The eccentric guide ring comprises an inner ring and an outer ring, and the eccentric roller is rotatably mounted inside the eccentric guide ring. One side of the eccentric roller is threadedly fixed to the output shaft of the servo motor, and the other side has a thread.

2. The aviation wire test bench according to claim 1, characterized in that: The eccentric component also includes a connecting shaft, which is fixedly connected to the steering connecting block and rotatably connected to the connecting slide rod, and is located on a side of the steering connecting block close to the connecting slide rod.

3. The aviation wire test bench as claimed in claim 2, characterized in that: The eccentric component also includes a connecting bearing, which is fixedly connected to the connecting slide bar and rotatably connected to the connecting shaft, and is located on a side of the connecting slide bar close to the connecting shaft.

4. The aviation wire test bench according to claim 1, characterized in that: The vibration assembly also includes a hydraulic cylinder and a telescopic rod. The hydraulic cylinder is fixedly connected to the support plate and is located on a side of the support plate close to the back plate. One end of the telescopic rod is fixedly connected to the output end of the hydraulic cylinder, and the other end is rotatably connected to the support plate and is located between the hydraulic cylinder and the back plate.

5. The aviation wire test bench as claimed in claim 4, characterized in that: The vibration assembly also includes a steering bearing, which is fixedly connected to the back plate and rotatably connected to the telescopic rod, and is located on a side of the back plate close to the telescopic rod.

6. The aviation wire test bench according to claim 1, characterized in that: The supporting device also includes a wire clamp, which is fixedly connected to the back plate, abuts against the wire, and is located on a side of the back plate close to the wire.

7. The aviation wire test bench according to claim 1, characterized in that: The supporting device further comprises a back plate coating, which is fixedly connected to the skin and is located on a side of the skin away from the back plate.

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