CN105667833A - Adjustment handle for airplane component parallel connection positioner - Google Patents
Adjustment handle for airplane component parallel connection positioner Download PDFInfo
- Publication number
- CN105667833A CN105667833A CN201610193293.9A CN201610193293A CN105667833A CN 105667833 A CN105667833 A CN 105667833A CN 201610193293 A CN201610193293 A CN 201610193293A CN 105667833 A CN105667833 A CN 105667833A
- Authority
- CN
- China
- Prior art keywords
- clamping plate
- parallel connection
- plate
- adjustment handle
- parallel
- Prior art date
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Clamps And Clips (AREA)
Abstract
The invention discloses an adjustment handle for an airplane component parallel connection positioner. The adjustment handle structurally comprises a clamping plate A (1), a clamping plate B (2) and a clamping plate C (3), wherein the clamping plate A (1) and the clamping plate B (2) are connected through a connection plate A (4-1); the clamping plate B (2) and the clamping plate C (3) are connected through a connection plate B (4-2); the clamping plate A (1) and the clamping plate C (3) are connected through a spring buckle (6); grips (5) are arranged on the outer sides of the clamping plate A (1), the clamping plate B (2) and the clamping plate C (3); and parallel connection positioner clamping blocks (7) are arranged on the inner sides of the clamping plate A (1), the clamping plate B (2) and the clamping plate C (3). The adjustment handle has the advantages that an angle of the parallel connection positioner can be controlled manually, and the parallel connection positioner can be conveniently adjusted roughly, so that precise positioning and adjustment of multi-degree-of-freedom positions and postures of various components are realized; and the adjustment handle is convenient, fast, simple in structure, firm and durable.
Description
Technical field
What the present invention relates to is aircraft components steady arm regulating handle in parallel.
Background technology
In aircraft manufacturing process, the assembling of parts and the labor capacity of installation work account for the 50%～60% of the total labor capacity of aircraft manufacturing. During assembling, adopt flexible location technology, the change of part structure to a certain degree can be adapted to, location stress inevitable in conventional rigid locator means can be reduced simultaneously.
At present, in aircraft manufacturing process, mostly adopt based on the method for fixing tool type frame, manual setting, significantly limit the raising of the reduction of frock cost and efficiency of assembling. Traditional way pose adjusts function singleness, locates coordination relation complexity between inaccurate, parts and frock. For adapting to the long lifetime, high stealthy demand, the complex constructions such as current aircraft many employings complex profile, special-shaped framework, this just needs to adapt to complex-curved location requirement in the Design and manufacture of assembly tooling to greatest extent.
Summary of the invention
What the present invention proposed is aircraft components steady arm regulating handle in parallel, plays object and is intended to overcome prior art above shortcomings, it is achieved adjustment steady arm angle in parallel flexibly, adapts to complex-curved location requirement.
The technical solution of the present invention: aircraft components steady arm regulating handle in parallel, its structure comprises A clamping plate, B clamping plate and C clamping plate, wherein A clamping plate and B clamping plate are connected by A web plate, B clamping plate and C clamping plate are connected by B web plate, A clamping plate and C clamping plate are connected by clamp button of the spring, all establish hand handle outside A clamping plate, B clamping plate and C clamping plate, inside A clamping plate, B clamping plate and C clamping plate, all establish steady arm card block in parallel.
Preferably, length and the width of described A clamping plate, B clamping plate and C clamping plate are all equal.
The advantage of the present invention: by the angle of Non-follow control steady arm in parallel, facilitates coarse adjustment steady arm in parallel, it is achieved the accurate location of various parts and multiple degree of freedom position, pose adjustment; Can greatly reduce frock cost and the requirement to frock precision; Can combine with automatic punching system, realize the coordinated manipulation of the base part pose adjustment of rudder face and drilling, respective advantage can be played to greatest extent, and then greatly improve efficiency of assembling and assembly quality, it is achieved the automatization of the component such as aircraft wallboard, beam, rib, long purlin assembly and high precision assembling; Convenient and swift, structure is simple, sturdy and durable.
Accompanying drawing explanation
Fig. 1 is the structural representation of aircraft components steady arm regulating handle in parallel.
In figure 1 is A clamping plate, 2 to be B clamping plate, 3 be C clamping plate, 4-1 are A web plate, 4-2 to be B web plate, 5 be hand, 6 be clamp button of the spring, 7 be steady arm card block in parallel.
Embodiment
Below in conjunction with embodiment and embodiment, the present invention is further detailed explanation.
As shown in Figure 1, aircraft components steady arm regulating handle in parallel, its structure comprises A clamping plate 1, B clamping plate 2 and C clamping plate 3, wherein A clamping plate 1 and B clamping plate 2 are connected by A web plate 4-1, B clamping plate 2 and C clamping plate 3 are connected by B web plate 4-2, A clamping plate 1 and C clamping plate 3 are connected by clamp button of the spring 6, all establish hand all establishing steady arm card block 7 in parallel inside 5, A clamping plate 1, B clamping plate 2 and C clamping plate 3 outside A clamping plate 1, B clamping plate 2 and C clamping plate 3.
Length and the width of described A clamping plate 1, B clamping plate 2 and C clamping plate 3 are all equal.
Above-described is only the preferred embodiment of the present invention, it should be noted that for the person of ordinary skill of the art, without departing from the concept of the premise of the invention, it is also possible to make some distortion and improvement, these all belong to protection scope of the present invention.
Claims (2)
1. aircraft components steady arm regulating handle in parallel, its feature comprises A clamping plate (1), B clamping plate (2) and C clamping plate (3), wherein A clamping plate (1) and B clamping plate (2) are connected by A web plate (4-1), B clamping plate (2) and C clamping plate (3) are connected by B web plate (4-2), A clamping plate (1) and C clamping plate (3) are connected by clamp button of the spring (6), A clamping plate (1), B clamping plate (2) and C clamping plate (3) outside all establish hand (5), A clamping plate (1), steady arm card block (7) in parallel is all established in B clamping plate (2) and C clamping plate (3) inner side.
2. aircraft components as claimed in claim 1 steady arm regulating handle in parallel, is characterized in that length and the width of described A clamping plate (1), B clamping plate (2) and C clamping plate (3) is all equal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610193293.9A CN105667833A (en) | 2016-03-30 | 2016-03-30 | Adjustment handle for airplane component parallel connection positioner |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610193293.9A CN105667833A (en) | 2016-03-30 | 2016-03-30 | Adjustment handle for airplane component parallel connection positioner |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105667833A true CN105667833A (en) | 2016-06-15 |
Family
ID=56224810
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610193293.9A Pending CN105667833A (en) | 2016-03-30 | 2016-03-30 | Adjustment handle for airplane component parallel connection positioner |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105667833A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080046003A1 (en) * | 2006-08-17 | 2008-02-21 | Uwe Renger | Tubular medical instrument |
| CN103225381A (en) * | 2013-05-07 | 2013-07-31 | 俞昌书 | Plug-in type plate frame variable-angle connecting piece |
| CN203885150U (en) * | 2014-06-05 | 2014-10-22 | 杭州中瑞思创科技股份有限公司 | Base removing tool |
| CN104594828A (en) * | 2015-02-11 | 2015-05-06 | 四川西林石油物资装备有限公司 | Drill pipe slip convenient for replacing friction components |
| CN204431170U (en) * | 2015-01-21 | 2015-07-01 | 中煤第三建设（集团）有限责任公司 | Disassembling tool for special oil cylinder of heading machine |
| CN205469876U (en) * | 2016-03-30 | 2016-08-17 | 宜兴市融兴铸造有限公司 | Aircraft component locator adjustment handle that connects in parallel |
-
2016
- 2016-03-30 CN CN201610193293.9A patent/CN105667833A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080046003A1 (en) * | 2006-08-17 | 2008-02-21 | Uwe Renger | Tubular medical instrument |
| CN103225381A (en) * | 2013-05-07 | 2013-07-31 | 俞昌书 | Plug-in type plate frame variable-angle connecting piece |
| CN203885150U (en) * | 2014-06-05 | 2014-10-22 | 杭州中瑞思创科技股份有限公司 | Base removing tool |
| CN204431170U (en) * | 2015-01-21 | 2015-07-01 | 中煤第三建设（集团）有限责任公司 | Disassembling tool for special oil cylinder of heading machine |
| CN104594828A (en) * | 2015-02-11 | 2015-05-06 | 四川西林石油物资装备有限公司 | Drill pipe slip convenient for replacing friction components |
| CN205469876U (en) * | 2016-03-30 | 2016-08-17 | 宜兴市融兴铸造有限公司 | Aircraft component locator adjustment handle that connects in parallel |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160615 |
|
| WD01 | Invention patent application deemed withdrawn after publication |