CN205656086U - A check out test set for detecting aircraft dope's shock resistance - Google Patents
A check out test set for detecting aircraft dope's shock resistance Download PDFInfo
- Publication number
- CN205656086U CN205656086U CN201521140080.7U CN201521140080U CN205656086U CN 205656086 U CN205656086 U CN 205656086U CN 201521140080 U CN201521140080 U CN 201521140080U CN 205656086 U CN205656086 U CN 205656086U
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- CN
- China
- Prior art keywords
- cavity
- shock resistance
- workbench
- aircraft skin
- guide rail
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
- 230000035939 shock Effects 0.000 title claims abstract description 25
- 239000011248 coating agent Substances 0.000 claims abstract description 38
- 238000000576 coating method Methods 0.000 claims abstract description 38
- 238000001514 detection method Methods 0.000 claims abstract description 38
- 238000012827 research and development Methods 0.000 abstract 1
- 238000001035 drying Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Abstract
The utility model discloses a check out test set for detecting aircraft dope's shock resistance, comprising a base plate, be equipped with the guide rail on the bottom plate, the workstation of setting on the guide rail of bottom plate, follow the gliding pulley of guide rail inside being equipped with of workstation, inside at the workstation still is equipped with the motor, the output shaft of motor is connected with the pulley, the cavity has been seted up on the workstation, be equipped with the die board at the middle part of cavity, a plurality of die hole have been seted up on the die board, place the pick -up plate that the coating has aircraft dope at the upside of die board, it stores up a box to be equipped with in one side of workstation, still set up on the workstation and connect the play piece passageway that stores up a box and cavity, stamping device, PLC control system, PLC control system are connected with motor, photoelectric sensing ware and the cylinder drive arrangement that drives actuating cylinder respectively. The utility model discloses detection that can be accurate goes out aircraft dope's shock resistance to can make aircraft dope's the accurate parameter of shocking resistance that gets of research and development person.
Description
Technical field
This utility model relates to detecting equipment technical field, is related specifically to the detection equipment of a kind of shock resistance for detecting aircraft skin coating.
Background technology
Shock resistance is one of important performance of aircraft skin coating, is also the important parameter meeting production and application.
At present, when aircraft skin coating is after production completes, need the shock resistance of aircraft skin coating is detected, and the detection equipment overall structure of the existing shock resistance for aircraft skin coating is complex, be difficult to detect accurately the shock resistance of detection aircraft skin coating.
But for the deficiencies in the prior art, developer is necessary to develop a kind of reasonable in design, simple in construction, can detect the shock resistance of aircraft skin coating accurately such that it is able to make the developer of aircraft skin coating accurately the detection equipment of the shock resistance for detecting aircraft skin coating of shock resistance parameter.
Utility model content
For solving the problem that prior art exists, this utility model provides a kind of reasonable in design, simple in construction, can detect the shock resistance of aircraft skin coating accurately such that it is able to make the developer of aircraft skin coating accurately the detection equipment of the shock resistance for detecting aircraft skin coating of shock resistance parameter.
For solving above technical problem, this utility model realizes by the following technical solutions:
A kind of detection equipment of the shock resistance for detecting aircraft skin coating, including
One base plate, is provided with guide rail on described base plate；
Workbench on one guide rail being arranged on described base plate, the pulley along slide it is provided with inside described workbench, it is additionally provided with motor in the inside of workbench, the output shaft of described motor is connected with pulley, cavity is offered in described workbench upper end, it is provided with concave template at the middle part of described cavity, described concave template offers multiple die hole, the detection plate being coated with aircraft skin coating it is placed with in the upside of described concave template, be provided with in the side of described workbench storage part box, described workbench is further opened with connect storage part box and cavity go out part passage；
One decompressor, described decompressor includes the support being arranged on base plate, it is provided with installing plate in the upper end of described support, it is provided with cylinder in the lower end of described installing plate, it is provided with fixed plate in the downside of described cylinder, described fixed plate is connected with the telescopic end of described cylinder, is provided with the multiple drifts corresponding with multiple die holes in the lower surface of described fixed plate, is additionally provided with photoelectric sensor in the lower end of described fixed plate；
One PLC control system, described PLC control system cylinder driver with motor, photoelectric sensor and driving cylinder respectively is connected.
In a preferred embodiment of the present utility model, offer pickup groove in the side of described cavity.
In a preferred embodiment of the present utility model, it is provided with locating part at the two ends of described guide rail.
nullCompared with prior art，This utility model overall structure is relatively simple，When detecting the shock resistance of aircraft skin coating，Have only to be coated in by aircraft skin coating on detection plate，It is placed on the concave template in cavity after aircraft skin coating being dried by drying unit，Then PLC control system is started，PLC control system controls motor work，Move so that being operated under the effect of pulley along guide rail，When workbench drives detection plate to move to the position corresponding with drift，Signal is delivered to PLC control system by photoelectric sensor，PLC control system controls motor and quits work，Control cylinder driver work simultaneously，So that the telescopic end of cylinder stretches out，Drift is made to match with die hole，Multiple detection piece will be swept away on the detection plate being placed on concave template，And detection piece slides in storage part box by going out part passage，Developer observes the completing property of detection piece surface aircraft skin coating by collecting，Analytical data draws the anti-impact force performance of this aircraft skin coating，Calculate the shock resistance parameter of this aircraft skin coating accurately.
Accompanying drawing explanation
In order to be illustrated more clearly that this utility model embodiment or technical scheme of the prior art, the accompanying drawing used required in embodiment or description of the prior art will be briefly described below, apparently, accompanying drawing in describing below is only embodiments more of the present utility model, for those of ordinary skill in the art, on the premise of not paying creative work, it is also possible to obtain other accompanying drawing according to these accompanying drawings.
Fig. 1 is structural representation of the present utility model.
Detailed description of the invention
For the technological means making this utility model realize, creation characteristic, reach purpose and be easy to understand with effect, below in conjunction with being specifically illustrating, this utility model is expanded on further.
With reference to shown in Fig. 1, the detection equipment of a kind of shock resistance for detecting aircraft skin coating be given in figure, including base plate 100, workbench 400, decompressor and PLC control system (not shown).
Base plate 100 is set side by side with two guide rails 200,300, it is equipped with locating part 210 at the two ends of guide rail 200, and limited block 310 it is equipped with at the two ends of guide rail 300, the setting of locating part 210,310, it can be avoided that workbench 400 skids off guide rail 200,300, further increases the security performance of this detection equipment.
Workbench 400 is arranged on two guide rails 200,300, the pulley (not shown) along slide it is provided with in the inside of workbench 400, it is additionally provided with motor in the inside of workbench 400, the output shaft of motor is connected with pulley, cavity 410 is offered in workbench 400 upper end, it is provided with concave template 500 at the middle part of cavity 410, concave template 500 offers multiple die hole 510, is placed with the detection plate (not shown) being coated with aircraft skin coating in the upside of concave template 500.
Storage part box 600 it is provided with in the side of workbench 400, workbench 400 is further opened with connect storage part box 600 and cavity 410 go out part passage 420, going out part passage 420 is an inclined-plane passage, go out part passage 420 and connect one end of cavity 410 higher than the one end connecting part box 600, this kind of structure is easier to make detection piece slide in storage part box 600 from the bottom of cavity 410, further increases the serviceability of this detection equipment.
Decompressor includes the support 710 being arranged on base plate 100, it is provided with installing plate 720 in the upper end of support 710, it is provided with cylinder (not shown) in the lower end of installing plate 720, it is provided with fixed plate 730 in the downside of cylinder, fixed plate 730 is connected with the telescopic end of cylinder, it is provided with the multiple drifts 740 corresponding with multiple die holes 510 in the lower surface of fixed plate 730, is additionally provided with photoelectric sensor in the lower end of fixed plate 730.
PLC control system cylinder driver with motor, photoelectric sensor and driving cylinder respectively is connected.
Offer pickup groove 411 in the side of cavity 410, detection piece more convenient can be taken out or be placed in cavity 410 by the setting of pickup groove 411, further increases the Practical Performance of this detection equipment.
Concrete operations of the present utility model are as follows:
nullFirst aircraft skin coating to be detected is coated on detection plate，It is baked to by drying unit，It is then placed within the concave template 500 in cavity 410，Subsequent start-up PLC control system，PLC control system controls motor work，Move so that being operated under the effect of pulley along guide rail，When workbench 400 drives detection plate to move to the position corresponding with drift 740，Signal is delivered to PLC control system by photoelectric sensor，PLC control system controls motor and quits work，Control cylinder driver work simultaneously，So that the telescopic end of cylinder stretches out，Drift 740 is made to match with die hole 510，Multiple detection piece will be swept away on the detection plate being placed on concave template 500，And detection piece slides in storage part box 600 by going out part passage 420，Developer observes the completing property of detection piece surface aircraft skin coating by collecting，Analytical data draws the anti-impact force performance of this aircraft skin coating，Calculate the shock resistance parameter of this aircraft skin coating accurately.
nullThis utility model overall structure is relatively simple in sum，When detecting the shock resistance of aircraft skin coating，Have only to be coated in by aircraft skin coating on detection plate，It is placed on the concave template in cavity after aircraft skin coating being dried by drying unit，Then PLC control system is started，PLC control system controls motor work，Move so that being operated under the effect of pulley along guide rail，When workbench drives detection plate to move to the position corresponding with drift，Signal is delivered to PLC control system by photoelectric sensor，PLC control system controls motor and quits work，Control cylinder driver work simultaneously，So that the telescopic end of cylinder stretches out，Drift is made to match with die hole，Multiple detection piece will be swept away on the detection plate being placed on concave template，And detection piece slides in storage part box by going out part passage，Developer observes the completing property of detection piece surface aircraft skin coating by collecting，Analytical data draws the anti-impact force performance of this aircraft skin coating，Calculate the shock resistance parameter of this aircraft skin coating accurately.
Of the present utility model ultimate principle, principal character and of the present utility model advantage have more than been shown and described.Skilled person will appreciate that of the industry; this utility model is not restricted to the described embodiments; described in above-described embodiment and description, principle of the present utility model is simply described; on the premise of without departing from this utility model spirit and scope, this utility model also has various changes and modifications, in the range of these changes and improvements both fall within claimed this utility model.This utility model claims scope and is defined by appending claims and equivalent thereof.
Claims (3)
1. the detection equipment being used for detecting the shock resistance of aircraft skin coating, it is characterised in that include
One base plate, is provided with guide rail on described base plate；
Workbench on one guide rail being arranged on described base plate, the pulley along slide it is provided with inside described workbench, it is additionally provided with motor in the inside of workbench, the output shaft of described motor is connected with pulley, cavity is offered in described workbench upper end, it is provided with concave template at the middle part of described cavity, described concave template offers multiple die hole, the detection plate being coated with aircraft skin coating it is placed with in the upside of described concave template, be provided with in the side of described workbench storage part box, described workbench is further opened with connect storage part box and cavity go out part passage；
One decompressor, described decompressor includes the support being arranged on base plate, it is provided with installing plate in the upper end of described support, it is provided with cylinder in the lower end of described installing plate, it is provided with fixed plate in the downside of described cylinder, described fixed plate is connected with the telescopic end of described cylinder, is provided with the multiple drifts corresponding with multiple die holes in the lower surface of described fixed plate, is additionally provided with photoelectric sensor in the lower end of described fixed plate；
One PLC control system, described PLC control system cylinder driver with motor, photoelectric sensor and driving cylinder respectively is connected.
The detection equipment of a kind of shock resistance for detecting aircraft skin coating the most according to claim 1, it is characterised in that: offer pickup groove in the side of described cavity.
The detection equipment of a kind of shock resistance for detecting aircraft skin coating the most according to claim 1, it is characterised in that: it is provided with locating part at the two ends of described guide rail.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521140080.7U CN205656086U (en) | 2015-12-31 | 2015-12-31 | A check out test set for detecting aircraft dope's shock resistance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521140080.7U CN205656086U (en) | 2015-12-31 | 2015-12-31 | A check out test set for detecting aircraft dope's shock resistance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205656086U true CN205656086U (en) | 2016-10-19 |
Family
ID=57356294
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521140080.7U Expired - Fee Related CN205656086U (en) | 2015-12-31 | 2015-12-31 | A check out test set for detecting aircraft dope's shock resistance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205656086U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112557191A (en) * | 2020-11-30 | 2021-03-26 | 盐城瑾诚科技有限公司 | A part equipment check out test set for intelligent unmanned aerial vehicle research and development design |
| WO2021249019A1 (en) * | 2020-06-11 | 2021-12-16 | 东莞宜安科技股份有限公司 | Testing device |
-
2015
- 2015-12-31 CN CN201521140080.7U patent/CN205656086U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021249019A1 (en) * | 2020-06-11 | 2021-12-16 | 东莞宜安科技股份有限公司 | Testing device |
| CN112557191A (en) * | 2020-11-30 | 2021-03-26 | 盐城瑾诚科技有限公司 | A part equipment check out test set for intelligent unmanned aerial vehicle research and development design |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161019 Termination date: 20181231 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |