CN209102320U - Airplane panel connector vibration testing device - Google Patents
Airplane panel connector vibration testing device Download PDFInfo
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- CN209102320U CN209102320U CN201822137639.0U CN201822137639U CN209102320U CN 209102320 U CN209102320 U CN 209102320U CN 201822137639 U CN201822137639 U CN 201822137639U CN 209102320 U CN209102320 U CN 209102320U
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- interlayer
- steering
- connector
- upper interlayer
- bottom plate
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Abstract
The utility model relates to a kind of airplane panel connector vibration testing devices, including steering assembly and charging assembly, steering assembly is fixed on vibration table surface, steering assembly includes turning to vertical plate, turn to bottom plate and two support side plates, turning to vertical plate, bottom plate is vertical fixes with steering, the vertical side edge for turning to vertical plate and steering bottom plate is connect with support side plate respectively, charging assembly includes upper interlayer, lower interlayer, load counterweight, mounting base, upper interlayer connector and lower interlayer connector, mounting base, which is fixed on, to be turned on bottom plate, the edge of mounting base is connect with the end face for turning to vertical plate, upper interlayer and lower interlayer are successively arranged on load counterweight, the first end face of lower interlayer is connect with the end face of load counterweight, the first end of upper interlayer is fixed on the end face of mounting base after passing through the square groove for loading counterweight, the second end and lower interlayer of upper interlayer are equal Connecting hole is offered, upper interlayer connector is connected after sequentially passing through connecting hole with lower interlayer connector, simulates the actual loading of interlayer connector.
Description
Technical field
The utility model belongs to standard component experimental technique field, is related to a kind of airplane panel connector vibration testing device.
Background technique
Airplane panel is the functions such as a kind of, structure member open for realizing internal structure connection and interior trim on aircraft
Common components.Typical airplane panel realizes the connection of laminate by connectors such as unit bolt nut, quick-detachable locks, typically
Airplane panel connector includes the upper interlayer connector being connected on upper interlayer panel and the lower folder that is mounted on lower interlayer panel
Layer connector.
Vibration test is the various Environmental Virbration Influences that artificial product is suffered from transportation, installation and use environment,
For determining ability that whether product can bear various ambient vibrations.Vibration test is that evaluation component, components and complete machine exist
Resistivity in expected transport and use environment.Vibration test is carried out in material object or model of the laboratory to vibrational system
Test can be examined in laboratory by carrying out vibration test, acceleration test and impact test to airplane panel connector
Performance of the testpieces under the extreme environment of actual condition carries out sufficient Performance Assessment to testpieces, to meet actual use
Demand.Existing experimental rig vibrates airplane panel connector, acceleration and impact test examination do not apply quality usually and bear
It carries, does not examine and bear certain mass load airplane panel Connector Environments performance, it can not more real simulation testpieces actual condition
Condition.
Utility model content
In view of the deficiencies of the prior art, the utility model provides a kind of airplane panel connector vibration testing device, gram
It has taken existing airplane panel connector vibration testing device and can not simulate actual condition environment, direction of vibration converts cumbersome, test
Device requires the disadvantages of high, and the conversion of compact-sized, analog actual condition load, direction of vibration is convenient.
The utility model is realized in this way:
A kind of airplane panel connector vibration testing device comprising steering assembly and charging assembly, the steering assembly
Be fixed on vibration table surface, the charging assembly is fixed on the steering assembly, the steering assembly include turn to vertical plate,
Bottom plate and two support side plates are turned to, the steering bottom plate or steering vertical plate are fixed on the vibration table surface, the steering
Vertical plate is vertical with the steering bottom plate to be fixed, and the edge for turning to vertical plate links together with the steering bottom plate, and described turn
It is connect respectively with the support side plate to vertical plate and the vertical side edge for turning to bottom plate, the charging assembly includes upper interlayer, lower folder
Layer, load counterweight, mounting base, upper interlayer connector and lower interlayer connector, the mounting base are fixed on the steering bottom
On plate, the edge of the mounting base is connect with the end face for turning to vertical plate, is successively arranged upper interlayer on the load counterweight
And lower interlayer, the first end face of the lower interlayer with it is described load counterweight end face connect, the second end face of the lower interlayer and
The upper interlayer contact, the first end of the upper interlayer are fixed on the mounting base after passing through the square groove for loading counterweight
On end face, the second end and lower interlayer of the upper interlayer offer connecting hole, and the upper interlayer connector sequentially passes through described
It is connected after connecting hole with the lower interlayer connector.
Preferably, the upper interlayer is the undercut shape structure that middle part offers the connecting hole.
Preferably, the load counterweight is the cylindrical structure opened up there are two square groove, the two side walls of the upper interlayer
After the square groove, the end face of side wall is connect with the mounting base.
Preferably, the lower interlayer is disc.
Preferably, the connecting hole includes counterbore and through-hole.
Compared with prior art, the utility model has the following beneficial effects:
(1) the utility model carries out airplane panel connector, that is, interlayer connector using charging assembly simulation real load
Load carries out the conversion of direction of vibration by steering assembly to interlayer connector, is realized using the load counterweight for offering square groove
The load of interlayer connector is vibrated, is impacted and acceleration test, the actual loading of interlayer connector can be simulated, it can
More really examine the environmental performance of interlayer connector.
(2) the utility model can be realized the vibration of interlayer connector, impact and acceleration direction using steering assembly
Conversion can be realized as the vibration to three directions of interlayer connecting-piece structure, impact by the testing equipment of single direction and add
The experiment examination of speed, it is more convenient to operate, convenient for mounting and clamping, saves test period, reduces equipment requirement.
(3) the utility model test efficiency height and test are more acurrate, are applicable not only to airplane panel connector, apply also for
The correlation test of vibration, the impact and acceleration of the multi-field interlayer connection structure such as aerospace, mechanical industry, it is easy to spread to answer
With.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the airplane panel connector vibration testing device of the utility model；
Fig. 2 be the utility model vibration testing device along interlayer connector axial vibration when structural schematic diagram；
Fig. 3 be the utility model vibration testing device along interlayer connector radial vibration when structural schematic diagram；
Fig. 4 is the structural schematic diagram of steering assembly；
Fig. 5 is the structural schematic diagram of charging assembly；
Fig. 6 is the diagrammatic cross-section of charging assembly；
Fig. 7 is the structural schematic diagram for turning to bottom plate；
Fig. 8 is the structural schematic diagram for turning to vertical plate；
Fig. 9 is the structural schematic diagram of mounting base；
Figure 10 is the structural schematic diagram of support side plate；
Figure 11 is the structural schematic diagram for loading counterweight；
Figure 12 a is the structural schematic diagram of upper interlayer；
Figure 12 b is the side view of upper interlayer；
Figure 13 a is the structural schematic diagram of lower interlayer；And
Figure 13 b is the bottom view of lower interlayer.
In figure: 1, steering assembly 2, charging assembly 3, vibration table surface
11, it turns to vertical plate 12, turn to bottom plate 13, the first support side plate 14, the second support side plate
21, upper interlayer 22, lower interlayer 23, load counterweight 24, mounting base 25, upper interlayer connector
26, lower interlayer connector 27, load counterweight connection bolt 28, mounting base connect bolt
121, bottom plate fixation hole 122 is turned to, vertical plate connection mounting hole 123 is turned to, turns to backplanes support threaded hole
111, shake table mounting hole 112, steering vertical plate installation threaded hole 113, steering vertical plate support threaded hole
241, mounting base fixation hole 242, upper interlayer mounting hole
131, it turns to vertical plate mounting hole 132, turn to bottom plate mounting hole
231, square groove 232, lower interlayer install threaded hole
212, upper interlayer counterbore 213, upper interlayer through-hole 214, upper interlayer fixing screwed hole
221, lower interlayer through-hole 222, lower interlayer counterweight mounting hole 223, lower interlayer counterbore
Specific embodiment
The exemplary embodiment, feature and aspect of performance of the utility model are described in detail below with reference to attached drawing.In attached drawing
Identical appended drawing reference indicates element functionally identical or similar.Although the various aspects of embodiment are shown in the attached drawings,
It is unless otherwise indicated, it is not necessary to attached drawing drawn to scale.
As shown in Figures 1 to 3, a kind of airplane panel connector vibration testing device comprising steering assembly 1 and charging assembly
2, steering assembly 1 or charging assembly 2 are fixed on vibration table surface 3, and charging assembly 2 is fixed on steering assembly 1, steering assembly
1 includes turning to vertical plate 11, turning to bottom plate 12 and two support side plates, and steering vertical plate 11 is vertical with bottom plate 12 is turned to fixed, turns to
The edge of vertical plate 11 with turn to bottom plate 12 link together, turn to vertical plate 11 and steering bottom plate 12 vertical side edge respectively with support
Side plate connection, charging assembly 2 include upper interlayer 21, lower interlayer 22, load counterweight 23, mounting base 24, upper interlayer connector 25
With lower interlayer connector 26, mounting base 24, which is fixed on, to be turned on bottom plate 12, edge and the steering vertical plate 11 of mounting base 24
End face connection loads and is successively arranged upper interlayer 21 and lower interlayer 22 on counterweight 23, the first end face and load counterweight of lower interlayer 22
23 end face connection, the second end face of lower interlayer 22 are contacted with 21 upper interlayers, and the first end of upper interlayer 21 passes through load counterweight 23
Square groove after be fixed on the end face of mounting base 24, the second end and lower interlayer 22 of upper interlayer 21 offer connecting hole, on
Interlayer connector 25 is connected after sequentially passing through the connecting hole of upper interlayer and the connecting hole of lower interlayer with lower interlayer connector 26.
Preferably, upper interlayer 21 is the undercut shape structure that middle part offers connecting hole, for simulating airplane panel
Interlayer.Lower interlayer is disc, for simulating the lower interlayer of airplane panel.The second of the recess portion end face of upper interlayer 21 and lower interlayer
The first end face of end face contact, lower interlayer 22 is connect with load counterweight 23.
Preferably, load counterweight 23 is the cylindrical structure opened up there are two square groove, and the two side walls of upper interlayer 21 pass through
After square groove, the end face of side wall is connect with mounting base 24, is loaded for analog-quality.
Preferably, connecting hole includes counterbore and through-hole, and as shown in figures 12 a and 12b, upper interlayer connecting hole includes that upper interlayer is heavy
Hole 212 and upper interlayer through-hole 213, upper interlayer counterbore 212 are located at the top of upper interlayer through-hole 213, as shown in figures 13a andb, under
Interlayer connecting hole includes lower interlayer counterbore 223 and lower interlayer through-hole 221, and lower interlayer counterbore 223 is located under lower interlayer through-hole 221
Side.It is heavy that upper interlayer connector 25 sequentially passes through upper interlayer counterbore 212, upper interlayer through-hole 213, lower interlayer through-hole 221 and lower interlayer
It is connected behind hole 223 with lower interlayer connector 26.
Preferably, the utility model, which is all made of, is bolted.
In the present embodiment, as shown in figure 4, steering assembly 1 include turn to vertical plate 11, turn to bottom plate 12, left side first
Second support side plate 14 of support side plate 13 and right side, as shown in fig. 7, turning to bottom plate 12 is plate profile structure part, for the side of test
To transformation when vibration table install, when direction of vibration along interlayer connector shaft to when, the steering bottom plate 12 of steering assembly 1 is fixed on
On vibration table surface 3, the end face for turning to bottom plate 12 is equipped with multiple steering bottom plate fixation holes 121 and connects mounting hole with vertical plate is turned to
122, two opposite sides are equipped with multiple steering backplanes support threaded holes 123；As shown in figure 8, turning to vertical plate 11 is template knot
Component, vibration table is installed when for test direction transformation, when direction of vibration is along interlayer connector radial direction, steering assembly 1
Vertical plate 11 is turned to be fixed on vibration table surface 3, the end face for turning to vertical plate 11 is equipped with multiple shake table mounting holes 111, wherein
One side is equipped with multiple steering vertical plates and installs threaded hole 112, and two opposite sides are supported equipped with multiple steering vertical plates
Threaded hole 113；As shown in Figure 10, support side plate is triangle template structural member, and two right-angle sides of support side plate are respectively equipped with more
A steering vertical plate mounting hole 131 and steering bottom plate mounting hole 132；The steering vertical plate connection mounting hole 122 for turning to bottom plate passes through spiral shell
Bolt links together with the steering vertical plate installation threaded hole 112 for turning to vertical plate, keeps steering vertical plate 11 vertical with bottom plate 12 is turned to solid
Fixed, mounting base 24 is fixed on steering bottom plate 12 by turning to bottom plate fixation hole 121, turns to the end face and installation bottom of vertical plate 11
The edge of plate 24 contacts, and the steering vertical plate support threaded hole 113 turned on the two opposite sides side of vertical plate 11 is supported with first respectively
Steering vertical plate mounting hole 131 on side plate and the second support side plate is bolted, on the two opposite sides side for turning to bottom plate 12
Steering backplanes support threaded hole 123 respectively with the steering bottom plate mounting hole 132 in the first support side plate and the second support side plate
It is bolted.
As shown in figure 5, charging assembly 2 includes upper interlayer 21, lower interlayer 22, load counterweight 23, mounting base 24, upper interlayer
Connector 25 and lower interlayer connector 26, as shown in figure 9, mounting base 24 is plate profile structure part, for the fixation of upper interlayer, peace
The quadrangle for filling bottom plate 24 is equipped with mounting base fixation hole 241, middle part is equipped with upper interlayer mounting hole 242, and mounting base 24 passes through
It is connect across mounting base fixation hole 241 and the bolt for turning to bottom plate fixation hole 121 with bottom plate 12 is turned to；As shown in figure 11, add
Carrying counterweight 23 is the cylindrical structure set there are two square groove 231, and the center of circle of load counterweight 23 is equipped with multiple lower interlayers and installs screw thread
Hole 232；As depicted in figs. 12 a and 12b, upper interlayer 21 is undercut shape structure, and middle part is successively arranged upper interlayer counterbore 212
Upper interlayer fixing screwed hole 214 is equipped with the end face of upper interlayer through-hole 213, the two sidewalls of upper interlayer 21；Such as Figure 13 a and Figure 13 b
Shown, lower interlayer 22 is disc-shaped structure, lower interlayer through-hole equipped with multiple lower interlayer counterweight mounting holes 222 and center successively and
Lower interlayer counterbore 223；After the two side walls of upper interlayer 21 pass through the square groove 231 of load counterweight 23, end face is by passing through upper folder
The mounting base of layer fixing screwed hole 214 and upper interlayer mounting hole 242 connection bolt 28 is connect with mounting base 24, lower interlayer 22
It is mounted between upper interlayer 21 and load counterweight 23, upper interlayer connector 25 sequentially passes through upper interlayer counterbore 212, upper interlayer through-hole
213, it is connected after lower interlayer counterbore 223 and lower interlayer through-hole 221 with lower interlayer connector 26, lower interlayer is by passing through lower interlayer weight
The load counterweight connection bolt 27 of code mounting hole 222 is connected with load counterweight 23.
The process of vibration test is carried out using the airplane panel connector vibration testing device of the utility model specifically:
As shown in Fig. 2, when direction of vibration along interlayer connector, that is, airplane panel connector shaft to when, steering assembly 1 turn
It is fixed on vibration table surface 3 to bottom plate 12, charging assembly 2 is bolted on steering assembly 1, and the ginseng of shake table is arranged
Number starts to test shake table along the vibration of vertical table-board direction, axial experiment examination is carried out to airplane panel connector.
As shown in figure 3, steering assembly 1 turns when direction of vibration is along interlayer connector, that is, airplane panel connector radial direction
It is fixed on vibration table surface 3 to vertical plate 11, charging assembly 2 is bolted on steering assembly 1, and the ginseng of shake table is arranged
Number starts to test shake table along the vibration of vertical table-board direction, radial experiment examination is carried out to airplane panel connector.
As shown in figure 3, when direction of vibration along interlayer connector, that is, another radial direction of airplane panel connector i.e. both perpendicular to
When interlayer connector direction axially and radially, by the steering vertical plate 11 of steering assembly 1 using 3 normal orientation of vibration table surface as axis
It is mounted on vibration table surface 3 for 90 ° to rotation, charging assembly 2 is bolted on steering assembly 1, and shake table is arranged
Parameter starts to test shake table along the vibration of vertical table-board direction, carries out another radial experiment examination to airplane panel connector.
The vibration testing device of the utility model is applicable not only to airplane panel connector, can be also used for other interlayers company
The vibration test of fitting.
To sum up, the utility model has the advantage that
(1) the utility model carries out aircraft face face connector, that is, interlayer connector using charging assembly simulation real load
Load carries out the conversion of direction of vibration by steering assembly to interlayer connector, is realized using the load counterweight for offering square groove
The load of interlayer connector is vibrated, is impacted and acceleration test, the actual loading of interlayer connector can be simulated, it can
More really examine the environmental performance of interlayer connector.
(2) the utility model can be realized the vibration of interlayer connector, impact and acceleration direction using steering assembly
Conversion can be realized as the vibration to three directions of interlayer connecting-piece structure, impact by the testing equipment of single direction and add
The experiment examination of speed, it is more convenient to operate, convenient for mounting and clamping, saves test period, reduces equipment requirement.
(3) the utility model test efficiency height and test are more acurrate, are applicable not only to airplane panel connector, apply also for
The correlation test of vibration, the impact and acceleration of the multi-field interlayer connection structure such as aerospace, mechanical industry, it is easy to spread to answer
With.
Finally, it should be noted that above-described each embodiment is merely to illustrate technical solutions of the utility model, rather than it is right
It is limited；Although the utility model is described in detail with reference to the foregoing embodiments, those skilled in the art are answered
Work as understanding: it can still modify to technical solution documented by previous embodiment, or to part of or whole skills
Art feature is equivalently replaced；And these modifications or substitutions, it does not separate the essence of the corresponding technical solution, and the utility model is each
The range of embodiment technical solution.
Claims (5)
1. a kind of airplane panel connector vibration testing device, it is characterised in that: it includes steering assembly and charging assembly, described
Steering assembly is fixed on vibration table surface, and the charging assembly is fixed on the steering assembly,
The steering assembly includes turning to vertical plate, turning to bottom plate and two support side plates, and the steering bottom plate or steering vertical plate are solid
Be scheduled on the vibration table surface, the steering vertical plate is vertical with the steering bottom plate to be fixed, it is described turn to vertical plate edge with
The steering bottom plate links together, and the vertical side edge for turning to vertical plate and turning to bottom plate connects with the support side plate respectively
It connects,
The charging assembly includes that upper interlayer, lower interlayer, load counterweight, mounting base, upper interlayer connector are connected with lower interlayer
Part, the mounting base are fixed on the steering bottom plate, and the edge of the mounting base and the end face for turning to vertical plate connect
It connects, upper interlayer and lower interlayer, the first end face of the lower interlayer and the load counterweight is successively arranged on the load counterweight
End face connection, the second end face of the lower interlayer are contacted with the upper interlayer, and the first end of the upper interlayer passes through the load
It is fixed on after the square groove of counterweight on the end face of the mounting base, the second end and lower interlayer of the upper interlayer offer connection
Hole, the upper interlayer connector are connected after sequentially passing through the connecting hole with the lower interlayer connector.
2. airplane panel connector vibration testing device according to claim 1, it is characterised in that: during the upper interlayer is
Portion offers the undercut shape structure of the connecting hole.
3. airplane panel connector vibration testing device according to claim 2, it is characterised in that: the load counterweight is
The cylindrical structure there are two square groove is opened up, after the two side walls of the upper interlayer pass through the square groove, the end face of side wall and institute
State mounting base connection.
4. airplane panel connector vibration testing device according to claim 3, it is characterised in that: the lower interlayer is circle
Dish type.
5. airplane panel connector vibration testing device according to claim 1 or 2, it is characterised in that: the connecting hole
Including counterbore and through-hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822137639.0U CN209102320U (en) | 2018-12-19 | 2018-12-19 | Airplane panel connector vibration testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822137639.0U CN209102320U (en) | 2018-12-19 | 2018-12-19 | Airplane panel connector vibration testing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209102320U true CN209102320U (en) | 2019-07-12 |
Family
ID=67163023
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822137639.0U Active CN209102320U (en) | 2018-12-19 | 2018-12-19 | Airplane panel connector vibration testing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209102320U (en) |
-
2018
- 2018-12-19 CN CN201822137639.0U patent/CN209102320U/en active Active
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