Aviation part vibration test bench

Abstract

The utility model provides an aviation part vibration test bench comprising a pedestal, a plurality of vertical springs are fixedly installed on the top of the pedestal in a rectangular array, the tops of the plurality of springs are fixedly connected with a fixing plate, the top of the fixing plate is provided with a positioning mechanism, the positioning mechanism is used for positioning aviation parts, and the positioning mechanism is used for positioning the aviation parts. Vibration motors are symmetrically and fixedly mounted at the bottom of the fixed plate; and a vertical rotating shaft is rotationally installed at the top of the base, a rotating disc is coaxially and fixedly connected to the top of the rotating shaft, a motor used for driving the rotating shaft to rotate is fixedly installed on the base, and a transmission mechanism connected with the fixing plate is installed on the rotating disc. When a vibration test is carried out on an aviation part, the fixing plate is effectively prevented from being in a same-frequency vibration state for a long time, a detection mode of carrying out the same-frequency vibration test on the aviation part is replaced, the limitation is reduced, the accuracy of the vibration test is improved, and the practicability is improved.

Description

Technical Field

[0001] This utility model relates to the field of vibration testing equipment technology, specifically to a vibration testing bench for aerospace components. Background Technology

[0002] An aircraft is any machine that takes off and flies by aerodynamically through the relative motion between its fuselage and the air; including balloons, airships, airplanes, helicopters, tiltrotor aircraft, etc.; aircraft manufacturing refers to the process of manufacturing aircraft according to the design requirements of different types of aircraft. Aircraft fuselage manufacturing involves processes such as process preparation, manufacturing of process equipment, preparation of blanks, machining of parts, assembly, and inspection; after the machining of spacecraft components is completed, it is necessary to sample the aircraft components for vibration testing in order to test the vibration resistance performance of the aircraft components.

[0003] For example, the accompanying diagram in the instruction manual. Figure 7 The diagram shows a structural schematic of a vibration test bench for aerospace components in the prior art. It includes a base, on the top of which multiple vertically oriented springs are fixedly mounted in a rectangular array. A fixed plate is fixedly connected to the top of each spring, and a positioning mechanism is mounted on the top of the fixed plate to position the aerospace components. Vibration motors are symmetrically mounted on the bottom of the fixed plate. In use, the aerospace components are placed on the fixed plate, positioned by the positioning mechanism, and two vibration motors are activated. The operation of the two motors causes the fixed plate to vibrate on top of the springs, thereby causing the aerospace components placed on the fixed plate to resonate, achieving the vibration test effect for the aerospace components. The operation is simple and easy to control. However, in actual use, the following drawbacks exist:

[0004] When two vibration motors are working, during the vibration test of aerospace components, as the working time of the two vibration motors increases, the fixed plate is likely to be in a state of vibration at the same frequency, thus conducting a same-frequency vibration test on the aerospace components. However, during the flight of an aircraft, the internal components of the aircraft are not in a state of vibration at the same frequency for a long time. Therefore, the above-mentioned vibration test bench for conducting same-frequency vibration tests on aerospace components has limitations, thereby reducing the accuracy of the vibration test and having low practicality.

[0005] Therefore, this application proposes a vibration test bench for aerospace components. Utility Model Content

[0006] To address the shortcomings of existing technologies, this utility model provides a vibration testing bench for aerospace components, which solves the problems mentioned in the background art.

[0007] To achieve the above objectives, this utility model provides the following technical solution:

[0008] The utility model provides an aviation part vibration test bench, which comprises a base, a plurality of vertical springs are fixedly installed on the top of the base in a rectangular array, the top of the plurality of springs is fixedly connected with a fixed plate, a positioning mechanism is installed on the top of the fixed plate and is used for positioning the aviation part, and a vibration motor is symmetrically fixedly installed on the bottom of the fixed plate.

[0009] A rotating shaft in a vertical state is rotatably installed on the top of the base, the top of the rotating shaft is coaxially fixedly connected with a rotating disc, a motor for driving the rotating shaft to rotate is fixedly installed on the base, and a transmission mechanism connected with the fixed plate is installed on the rotating disc.

[0010] A knocking mechanism capable of contacting the bottom of the fixed plate is installed on the base, and the bottom of the fixed plate can be intermittently knocked by the knocking mechanism when the fixed plate shakes on the top of the plurality of springs.

[0011] Further, the transmission mechanism comprises a connecting rod and a sleeve rod, the connecting rod in an inclined state is fixedly installed at the eccentric position of the top of the rotating disc, the sleeve rod is fixedly installed on the bottom of the fixed plate, the connecting rod is rotatably connected with the sleeve rod, and the sleeve rod and the connecting rod are located on the same axial direction.

[0012] Further, the knocking mechanism comprises a mounting frame fixedly installed on the top of the base, a connecting block is installed on the top of the mounting frame and below the fixed plate, a connecting plate is fixedly installed on the side of the connecting block close to the fixed plate, the end of the connecting plate extends below the fixed plate and is fixedly installed with a knocking block capable of abutting against the bottom of the fixed plate.

[0013] Further, the connecting block is hinged to the mounting frame through a hinge shaft, and an adjusting member connected with the hinge shaft is installed on the mounting frame, which is used for rotating or stopping the rotation of the hinge shaft on the mounting frame.

[0014] Further, the adjusting member comprises a worm wheel coaxially fixedly connected with the hinge shaft, and a worm is rotatably installed on the mounting frame and engaged with the worm wheel.

[0015] Further, the positioning mechanism comprises two positioning plates symmetrically and slidably installed on the top of the fixed plate, and an adjusting mechanism connected with the two positioning plates is installed on the fixed plate, which is used for reversely sliding or stopping the sliding of the two positioning plates on the fixed plate.

[0016] Further, the adjusting mechanism comprises a sliding block slidably installed on the fixed plate, the sliding direction of the sliding block on the fixed plate is perpendicular to the sliding direction of the positioning plate on the fixed plate, hinge rods are hinged to the two sides of the sliding block, the other ends of the two hinge rods are respectively hinged to the two positioning plates, an adjusting rod is rotatably installed on the fixed plate, and the adjusting rod is threadedly connected with the sliding block.

[0017] Further, two positioning plates are provided with positioning grooves on the side close to each other, and the cross section of the positioning groove is V-shaped.

[0018] The utility model provides a kind of aviation parts vibration test bench.Compared with prior art, it has the following beneficial effects:

[0019] 1. When the aviation parts are vibrated, the fixed plate is effectively avoided in the same frequency vibration state for a long time, and the detection mode of the aviation parts is replaced by the same frequency vibration test, the limitation is reduced, the accuracy of vibration test is improved, and the practicability is improved.

[0020] 2. The knocking block rotates around the hinge shaft and moves in an arc downward by adjusting the hinge shaft on the mounting frame, so that the fixed plate is not in contact with the knocking block during the shaking process on the plurality of springs, and the vibration test mode of the aviation parts is increased.

[0021] 3. The aviation parts are positioned in the inside of the positioning groove on the two positioning plates by the design of the positioning groove, and the positioning effect of the aviation parts is improved. BRIEF DESCRIPTION OF DRAWINGS

[0022] In order to more clearly illustrate the technical scheme in the embodiments of the utility model or prior art, the drawings needed in the embodiment or prior art description will be briefly introduced below, and obviously, the drawings in the following description are only some embodiments of the utility model, and other drawings can be obtained by those skilled in the art without creative labor.

[0023] Figure 1 The utility model shows the three-dimensional structure schematic diagram of the utility model;

[0024] Figure 2 The utility model shows the mounting structure schematic diagram of transmission mechanism;

[0025] Figure 3 The utility model shows the mounting structure schematic diagram of knocking mechanism;

[0026] Figure 4 The utility model shows the Figure 3 Enlarged view of A in the middle;

[0027] Figure 5 The utility model shows the mounting structure schematic diagram of hinge rod;

[0028] Figure 6 The utility model shows the mounting structure schematic diagram of adjusting part;

[0029] Figure 7A structural schematic view of an aviation part vibration test bench in the prior art is shown.

[0030] As shown in the figure: 1, base; 11, spring; 12, rotating shaft; 13, rotating disc; 14, motor; 2, fixed plate; 21, vibration motor; 3, positioning mechanism; 31, positioning plate; 4, transmission mechanism; 41, connecting rod; 42, sleeve rod; 5, knocking mechanism; 51, mounting frame; 52, connecting block; 521, hinged shaft; 53, connecting plate; 54, knocking block; 6, adjusting part; 61, worm gear; 62, worm; 7, adjusting mechanism; 71, sliding block; 72, hinged rod; 73, adjusting rod. DETAILED DESCRIPTION

[0031] In order to make the purpose, technical scheme and advantages of the embodiments of the present application more clear, the technical scheme in the embodiments of the present application is described clearly and completely. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0032] Embodiment one

[0033] To solve the technical problems in the background art, the following aviation part vibration test bench is given:

[0034] In combination Figures 1-6 with the description, the present application provides an aviation part vibration test bench, which comprises a base 1. The top of the base 1 is fixedly installed with a plurality of springs 11 in a rectangular array, which are all in a vertical state. The top of the plurality of springs 11 is fixedly connected with a fixed plate 2. The top of the fixed plate 2 is installed with a positioning mechanism 3. The positioning mechanism 3 is used for positioning the aviation part. The bottom of the fixed plate 2 is symmetrically fixedly installed with a vibration motor 21.

[0035] The top of the base 1 is rotatably installed with a rotating shaft 12 in a vertical state. The top of the rotating shaft 12 is coaxially fixedly connected with a rotating disc 13. The base 1 is fixedly installed with a motor 14 for driving the rotating shaft 12 to rotate. The rotating disc 13 is installed with a transmission mechanism 4 connected with the fixed plate 2. When the rotating disc 13 rotates around the rotating shaft 12, the fixed plate 2 is shaken on the top of the plurality of springs 11 through the transmission mechanism 4.

[0036] The base 1 is installed with a knocking mechanism 5 which can contact the bottom of the fixed plate 2. When the fixed plate 2 is shaken on the top of the plurality of springs 11, the bottom of the fixed plate 2 can be intermittently knocked through the knocking mechanism 5. The present device is powered by an external power supply.

[0037] When the vibration test is performed on the aviation part, the aviation part is placed on the fixed plate 2, and the aviation part is positioned by the positioning mechanism 3, the two vibration motors 21 are controlled to be turned on, the two vibration motors 21 work to make the fixed plate 2 resonate, so that the aviation part resonates, the vibration test effect of the aviation part is realized, during the period, the motor 14 is controlled to rotate the shaft 12 on the base 1, the rotating disc 13 rotates around the shaft 12, so that the fixed plate 2 is shaken on the top of the plurality of springs 11 through the transmission mechanism 4, the plurality of springs 11 are deformed, the vibration effect of the aviation part is improved, and during the period, the knocking mechanism 5 intermittently knocks the bottom of the fixed plate 2, so that the fixed plate 2 resonates, the fixed plate 2 is effectively prevented from being in the same frequency vibration state for a long time, the detection mode of the same frequency vibration test on the aviation part is replaced, the limitation is reduced, the accuracy of the vibration test is improved, and the practicability is improved.

[0038] Embodiment two

[0039] As Figures 1-6 shown, on the basis of the above embodiment, the embodiment further gives the following contents:

[0040] In the embodiment, the transmission mechanism 4 includes a connecting rod 41 and a sleeve rod 42, the connecting rod 41 is fixedly installed at the eccentric position of the top of the rotating disc 13 in an inclined manner, the sleeve rod 42 is fixedly installed at the bottom of the fixed plate 2, the connecting rod 41 is rotationally connected with the sleeve rod 42, and the sleeve rod 42 and the connecting rod 41 are located on the same axis direction, in use, when the rotating disc 13 rotates on the base 1, the connecting rod 41 is driven to rotate due to the inclined fixing of the connecting rod 41 at the eccentric position of the rotating disc 13, and the sleeve rod 42 is rotationally connected with the connecting rod 41 at the bottom of the fixed plate 2, and the sleeve rod 42 and the connecting rod 41 are located on the same axis, at this time, when the rotating disc 13 rotates to drive the connecting rod 41 to rotate, the spring 11 is deformed due to the fixed connection of the fixed plate 2 with the base 1 through the plurality of springs 11, and the connecting rod 41 and the sleeve rod 42 rotate relative to each other, so that the fixed plate 2 is shaken on the plurality of springs 11.

[0041] In the embodiment, the knocking mechanism 5 comprises a mounting frame 51 fixedly installed on the top of the base 1, a connecting block 52 is installed on the top of the mounting frame 51 and below the fixed plate 2, the connecting block 52 is fixedly installed with a connecting plate 53 on the side close to the fixed plate 2, the connecting plate 53 is made of beryllium bronze plate, the end of the connecting plate 53 extends below the fixed plate 2 and is fixedly installed with a knocking block 54 which can be in contact with the bottom of the fixed plate 2, in use, when the fixed plate 2 shakes on the springs 11 and the fixed plate 2 is in contact with the knocking block 54, the knocking block 54 can knock the fixed plate 2, when the fixed plate 2 presses and holds the knocking block 54 during shaking on the springs 11, the connecting plate 53 is deformed under stress, which does not affect the shaking of the fixed plate 2 on the springs 11.

[0042] In the embodiment, the connecting block 52 is hinged on the mounting frame 51 through a hinge shaft 521, the mounting frame 51 is installed with an adjusting member 6 connected with the hinge shaft 521, which is used to rotate or stop rotating the hinge shaft 521 on the mounting frame 51, in use, rotating the hinge shaft 521 on the mounting frame 51 through the adjusting member 6 can make the knocking block 54 rotate around the hinge shaft 521 and move in an arc downward, thereby avoiding the contact between the fixed plate 2 and the knocking block 54 during the shaking of the fixed plate 2 on the springs 11, and increasing the vibration test mode of the device on the aviation parts.

[0043] Embodiment three

[0044] As shown in the above embodiment, the embodiment further provides the following content: Figures 1-6

[0045] In the embodiment, the adjusting member 6 comprises a worm gear 61 coaxially fixed with the hinge shaft 521, the mounting frame 51 is rotatably installed with a worm shaft 62 engaged with the worm gear 61, in use, rotating the worm shaft 62 can drive the hinge shaft 521 to rotate on the mounting frame 51 through the worm gear 61, since the worm gear 61 and the worm shaft 62 are engaged with self-locking property, when the worm shaft 62 is not rotated, the worm gear 61 will not rotate, thereby fixing the position of the hinge shaft 521, which is simple to operate.

[0046] In the embodiment, the positioning mechanism 3 comprises positioning plates 31 symmetrically and slidably installed on the top of the fixed plate 2, the fixed plate 2 is installed with an adjusting mechanism 7 connected with both of the positioning plates 31, which is used to slide or stop sliding the two positioning plates 31 on the fixed plate 2 in opposite directions, when positioning the aviation parts, the aviation parts are placed on the top of the fixed plate 2 and between the opposite sides of the two positioning plates 31, the two positioning plates 31 are slid in opposite directions on the fixed plate 2 through the adjusting mechanism 7 to approach each other, so that the two positioning plates 31 are in contact with the aviation parts, thereby positioning the aviation parts on the fixed plate 2. ​

[0047] In the embodiment, the adjusting mechanism 7 comprises a sliding block 71 slidingly installed on the fixed plate 2, the sliding direction of the sliding block 71 on the fixed plate 2 is perpendicular to the sliding direction of the positioning plate 31 on the fixed plate 2, both sides of the sliding block 71 are hingedly connected with hinged rods 72, the other ends of the two hinged rods 72 are respectively hingedly connected with the two positioning plates 31, and an adjusting rod 73 is rotatably installed on the fixed plate 2 and is in threaded connection with the sliding block 71, in use, an acting force is applied to the adjusting rod 73 to make the adjusting rod 73 rotate on the fixed plate 2, so that the sliding block 71 can slide on the fixed plate 2, both hinged rods 72 rotate around the hinged points on the sliding block 71, and the other ends of the two hinged rods 72 rotate with the two positioning plates 31, so that the two positioning plates 31 can slide reversely on the fixed plate 2, and the operation is simple.

[0048] In the embodiment, the two positioning plates 31 are both provided with positioning grooves on the side close to each other, and the cross section of the positioning groove is in V shape, through the design of the positioning groove, when the aviation parts are positioned, the aviation parts are located inside the positioning grooves on the two positioning plates 31, and the positioning effect of the aviation parts is improved.

[0049] It should be noted that the relational terms herein such as first and second and the like are used solely to distinguish one from another entity or action, without necessarily requiring or implying any such actual relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", or any other variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus. An element proceeded by "comprises... a" does not, without more constraints, exclude the existence of additional identical elements in the process, method, article, or apparatus that comprises the element.

[0050] The above embodiments are only used to illustrate the technical solutions of the present application, but not limit it; although the foregoing embodiments of the present application have been described in detail, those skilled in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or make equivalent replacement to some technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. An aircraft component vibration test stand, characterized by: The base is provided with a plurality of vertical springs arranged in a rectangular array at the top of the base, a fixing plate fixedly connected to the top of the springs, a positioning mechanism arranged on the top of the fixing plate for positioning the aviation parts, and a vibration motor fixedly arranged on the bottom of the fixing plate. The base is provided with a vertical rotating shaft arranged at the top of the base, a rotating disc coaxially fixed to the top of the rotating shaft, a motor fixedly arranged on the base for driving the rotating shaft to rotate, and a transmission mechanism arranged on the rotating disc and connected to the fixing plate. The base is provided with a knocking mechanism arranged on the base and capable of contacting the bottom of the fixing plate.

2. The vibration test rig for an aircraft component according to claim 1, characterized in that: The transmission mechanism comprises a connecting rod and a sleeve rod, the connecting rod is fixedly arranged on the top of the rotating disc in an inclined manner, the sleeve rod is fixedly arranged on the bottom of the fixing plate, and the connecting rod is rotatably connected to the sleeve rod and arranged on the same axis as the sleeve rod.

3. The vibration test rig for an aeronautical component according to claim 1, characterized in that: The knocking mechanism comprises a mounting frame fixedly arranged on the top of the base, a connecting block arranged on the top of the mounting frame and below the fixing plate, a connecting plate fixedly arranged on the side of the connecting block close to the fixing plate, and a knocking block fixedly arranged on the end of the connecting plate and below the fixing plate and capable of contacting the bottom of the fixing plate.

4. The vibration test rig for an aeronautical component according to claim 3, characterized in that: The connecting block is hingedly connected to the mounting frame via a hinge shaft, and the mounting frame is provided with an adjusting member connected to the hinge shaft for rotating or stopping the rotation of the hinge shaft on the mounting frame.

5. The vibration test rig for an aircraft component of claim 4, wherein: The adjusting member comprises a worm wheel coaxially fixed to the hinge shaft, and the mounting frame is provided with a worm screw rotatably arranged on the mounting frame and engaged with the worm wheel.

6. The vibration test rig for an aircraft component of claim 1, wherein: The positioning mechanism comprises two positioning plates symmetrically and slidably arranged on the top of the fixing plate, and the fixing plate is provided with an adjusting mechanism connected to the two positioning plates for reversely sliding or stopping the sliding of the two positioning plates on the fixing plate.

7. The vibration test rig for an aeronautical component according to claim 6, characterized in that: The adjusting mechanism comprises a sliding block slidably arranged on the fixing plate, the sliding direction of the sliding block on the fixing plate is perpendicular to the sliding direction of the positioning plates on the fixing plate, the two sides of the sliding block are hingedly connected to two hinge rods, the other ends of the two hinge rods are respectively hingedly connected to the two positioning plates, and the fixing plate is provided with an adjusting rod rotatably arranged on the fixing plate and threadedly connected to the sliding block.

8. The vibration test rig for an aircraft component of claim 7, wherein: The two positioning plates are provided with positioning grooves arranged on the sides close to each other, and the cross section of the positioning groove is in the shape of V.

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