CN205311923U - Be used for electronic location locking device of aircraft frock skeleton - Google Patents
Be used for electronic location locking device of aircraft frock skeleton Download PDFInfo
- Publication number
- CN205311923U CN205311923U CN201520958299.1U CN201520958299U CN205311923U CN 205311923 U CN205311923 U CN 205311923U CN 201520958299 U CN201520958299 U CN 201520958299U CN 205311923 U CN205311923 U CN 205311923U
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- China
- Prior art keywords
- locking
- skeleton
- aircraft
- assembly
- base
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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.)
- Withdrawn - After Issue
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Abstract
The utility model relates to a be used for electronic location locking device of aircraft frock skeleton is equipped with locking locating component in the base, locking locating component's outer end sets up the mounting flange subassembly, is equipped with the control subassembly at the terminal surface of mounting flange subassembly. This locking device under the condition that airplane assembling frock skeleton precision and reliability do not reduce, can realize the quick reconsitution of large -scale airplane assembling frock skeleton to realized large -scale airplane assembling frock skeleton reuse, and then reduced new type aircraft development cost, shortened the aircraft development production preparation cycle by a wide margin, satisfied the aircraft new model and develop the demand fast.
Description
Technical field
The invention relates to a kind of for the electronic positioning and locking device of Aircraft Tools skeleton, fills the location clamping between skeleton for aircraft rigger, belongs to the assembling field of aeronautical manufacture.
Background technology
Aircraft assembling is a numerous and diverse process, and technology requires higher, and thousands of parts need to position accurately and support. owing to conventional airplane frock adopts the pressure location mode of rigidity, between conventional rigid frock skeleton, many employing screw threads and welding manner are attached, its precision is not high and controllability is poor, when aircraft type changes, conventional rigid frock skeleton can not match with new parts very well, its bad adaptability, the rigid tooling skeleton of these specialties must redesign manufacture, cause significant wastage, improve aircraft manufacturing cost, significantly extend the Operational preparation cycle of aircraft development, thus affecting aircraft type entirety to develop process, the above-mentioned drawback of conventional airplane frock skeleton type of attachment, aircraft development process is created very big negative effect.
Summary of the invention
The invention to solve the technical problem that and to be to provide one for the electronic positioning and locking device of Aircraft Tools skeleton, this locking device, when aircraft rigger fills skeleton precision and reliability does not reduce, large aircraft assembly tooling skeleton quick reconfiguration can be realized, it is achieved thereby that the recycling of large aircraft assembly tooling skeleton, and then reduce type aircraft development cost, aircraft development Operational preparation cycle is greatly shortened, has met novel aircraft rapid development demand.
For solving problem above, the concrete technical scheme of the invention is as follows: a kind of for the electronic positioning and locking device of Aircraft Tools skeleton, being provided with locking positioning assembly in base, the outer end of locking positioning assembly arranges locating flange assembly, and the end face at locating flange assembly is provided with monitor component.
The structure of described locking positioning assembly is, be provided with two-phase stepping motor I in the outer end of base, two-phase stepping motor I is connected with the threaded rod of chassis interior by reductor I, threaded screw on threaded rod, screw is bolted alignment pin, and alignment pin end stretches out base; Being connected by the end of bearing gland assembly with location column sleeve near reductor I end at threaded rod, the other end of location column sleeve is fixed on base;Column sleeve outer face, location is connected with gear wheel inner face; The excircle pinion mate of gear wheel, and little rotary gear shaft is connected with the two-phase stepping motor II on base end face by reductor; Be provided with locking jaw flange in the outer face of gear wheel, locking jaw flange is provided with the locking jaw of circle distribution, and locking jaw is flexibly connected with locating flange assembly.
The structure of described locating flange assembly is, keeper one end of cylindricality is provided with locating flange, and the other end is provided with locking ring flange, and locking ring flange is provided with the limited block of circle distribution, and limited block is flexibly connected with locking jaw; On locking ring flange, circle distribution has the locking face of wedge shape.
The described gear wheel described in monitor component and little gear be provided externally with gear protective cover, gear protective cover is provided with the video camera of runing rest.
Described threaded rod is provided with mobile plectrum, is provided with three proximity switches in base top, and three proximity switches are sequentially located on the path of mobile plectrum.
This is used for the structure that the electronic positioning and locking device of Aircraft Tools skeleton adopts locking positioning assembly, locating flange assembly and monitor component to combine, so that location is more accurately, quickly.
Locking positioning assembly adopts two-phase stepping motor II to drive threaded rod to rotate, so that alignment pin can be capable of expansion and contraction, makes alignment pin that frock skeleton to be positioned, and is engaged by gear simultaneously and drives locating flange assembly to rotate wedging.
Locating flange assembly arranges limited block be connected with locking jaw, lozenges disposed circumferentially around, in order to carry out wedging with frock skeleton and be connected.
Position for video camera is in gear protective cover, in order to observes the position in hole, location, makes location more accurate.
Mobile plectrum on threaded rod can pass through proximity switch and control the stroke of alignment pin.
Accompanying drawing explanation
Fig. 1 is the overall structure schematic diagram for the electronic positioning and locking device of Aircraft Tools skeleton.
Fig. 2 is the axonometric drawing I of locking positioning assembly.
Fig. 3 is the axonometric drawing II of locking positioning assembly.
Fig. 4 is the axonometric drawing III of locking positioning assembly.
Fig. 5 is the sectional structure chart of locking positioning assembly.
Fig. 6 is the axonometric drawing of locating flange assembly.
Fig. 7 is the axonometric drawing of monitor component.
Detailed description of the invention
Being provided with locking positioning assembly 3 as it is shown in figure 1, a kind of in base for the electronic positioning and locking device of Aircraft Tools skeleton, the outer end of locking positioning assembly 3 arranges locating flange assembly 1, and the end face at locating flange assembly 1 is provided with monitor component 2.
As shown in Figures 2 to 5, the structure of described locking positioning assembly 3 is, it is provided with two-phase stepping motor I 20 in the outer end of base 17, two-phase stepping motor I 20 is connected with the threaded rod 38 within base 17 by reductor I 19, threaded screw 40 on threaded rod 38, screw 40 is bolted alignment pin 12, and alignment pin 12 end stretches out base 17; Being connected by the end of bearing gland assembly 34 with location column sleeve 39 near reductor I 19 end at threaded rod 38, the other end of location column sleeve 39 is fixed on base 17; Column sleeve 39 outer face, location is connected with gear wheel 24 inner face; The excircle pinion mate 29 of gear wheel 24, and little gear 29 rotating shaft is connected with the two-phase stepping motor II 32 on base 17 end face by reductor; Be provided with locking jaw flange 27 in the outer face of gear wheel 24, locking jaw flange 27 is provided with the locking jaw 26 of circle distribution, and locking jaw 26 is flexibly connected with locating flange assembly 1.
As shown in Figure 6, the structure of described locating flange assembly 1 is, keeper one end of cylindricality is provided with locating flange 4, and the other end is provided with locking ring flange 6, and locking ring flange 6 is provided with the limited block 5 of circle distribution, and limited block 5 is flexibly connected with locking jaw 26; On locking ring flange 6, circle distribution has the locking face of wedge shape.
As it is shown in fig. 7, the described gear wheel 24 described in monitor component 2 and little gear 29 be provided externally with gear protective cover 13, gear protective cover 13 is provided with the video camera 11 of runing rest 10.
Described threaded rod 38 is provided with mobile plectrum, is provided with three proximity switches 15 in base top, and three proximity switches 15 are sequentially located on the path of mobile plectrum, and what three proximity switches controlled threaded rod respectively stretches out position, retraction position and locking positioning position.
The method utilizing positioning and locking device that Aircraft Tools skeleton is positioned, comprises the following steps:
1) by the monitoring of the video camera on monitor component 2, control to be arranged on the frock skeleton that need to position by the front end of locating flange assembly 1;
2) starting two-phase stepping motor I 20, alignment pin 12 is protruding, and is inserted in the hole, location of frock skeleton to be positioned, and now the hole, location of frock skeleton is coaxial with locating flange assembly;
3) after mobile plectrum touches the proximity switch 15 of locking positioning, starting two-phase stepping motor II 32 drives little gear 29 to rotate, and rotated by the gear wheel 24 engaged, thus driving locking ring flange 6 to rotate, the locating flange 4 of locating flange assembly 1 is positioned clamping skeleton locking and is connected by wedge lock face with frock.
Claims (5)
1. one kind is used for the electronic positioning and locking device of Aircraft Tools skeleton, it is characterized in that: in base, be provided with locking positioning assembly (3), the outer end of locking positioning assembly (3) arranges locating flange assembly (1), and the end face at locating flange assembly (1) is provided with monitor component (2).
2. as claimed in claim 1 for the electronic positioning and locking device of Aircraft Tools skeleton, it is characterized in that: the structure of described locking positioning assembly (3) is, it is provided with two-phase stepping motor I (20) in the outer end of base (17), two-phase stepping motor I (20) is connected by the threaded rod (38) that reductor I (19) is internal with base (17), at the upper threaded screw (40) of threaded rod (38), screw (40) is bolted alignment pin (12), and alignment pin (12) end stretches out base (17); Being connected by the end of bearing gland assembly (34) with location column sleeve (39) near reductor I (19) end at threaded rod (38), the other end of location column sleeve (39) is fixed on base (17); Column sleeve (39) outer face, location is connected with gear wheel (24) inner face; The excircle pinion mate (29) of gear wheel (24), and little gear (29) rotating shaft is connected with the two-phase stepping motor II (32) on base (17) end face by reductor; Be provided with locking jaw flange (27) in the outer face of gear wheel (24), locking jaw flange (27) is provided with the locking jaw (26) of circle distribution, and locking jaw (26) is flexibly connected with locating flange assembly (1).
3. as claimed in claim 2 for the electronic positioning and locking device of Aircraft Tools skeleton, it is characterized in that: the structure of described locating flange assembly (1) is, keeper one end of cylindricality is provided with locating flange (4), the other end is provided with locking ring flange (6), locking ring flange (6) is provided with the limited block (5) of circle distribution, and limited block (5) is flexibly connected with locking jaw (26);The locking face of wedge shape is had in the upper circle distribution of locking ring flange (6).
4. as claimed in claim 3 for the electronic positioning and locking device of Aircraft Tools skeleton, it is characterized in that: the described gear wheel (24) described in monitor component (2) and little gear (29) be provided externally with gear protective cover (13), gear protective cover (13) is provided with the video camera (11) of runing rest (10).
5. as claimed in claim 2 for the electronic positioning and locking device of Aircraft Tools skeleton, it is characterized in that: described threaded rod (38) is provided with mobile plectrum, being provided with three proximity switches (15) in base top, three proximity switches (15) are sequentially located on the path of mobile plectrum.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520958299.1U CN205311923U (en) | 2015-11-27 | 2015-11-27 | Be used for electronic location locking device of aircraft frock skeleton |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520958299.1U CN205311923U (en) | 2015-11-27 | 2015-11-27 | Be used for electronic location locking device of aircraft frock skeleton |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205311923U true CN205311923U (en) | 2016-06-15 |
Family
ID=56189382
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520958299.1U Withdrawn - After Issue CN205311923U (en) | 2015-11-27 | 2015-11-27 | Be used for electronic location locking device of aircraft frock skeleton |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205311923U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105329463A (en) * | 2015-11-27 | 2016-02-17 | 沈阳飞机工业（集团）有限公司 | Electric positioning locking device for tool frame of aircraft |
-
2015
- 2015-11-27 CN CN201520958299.1U patent/CN205311923U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105329463A (en) * | 2015-11-27 | 2016-02-17 | 沈阳飞机工业（集团）有限公司 | Electric positioning locking device for tool frame of aircraft |
| CN105329463B (en) * | 2015-11-27 | 2017-09-22 | 沈阳飞机工业（集团）有限公司 | One kind is used for the electronic positioning and locking device of Aircraft Tools skeleton |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160615 Effective date of abandoning: 20170922 |
|
| AV01 | Patent right actively abandoned |