CN105234646A - Aircraft component rapid assembly tool with assigned track - Google Patents
Aircraft component rapid assembly tool with assigned track Download PDFInfo
- Publication number
- CN105234646A CN105234646A CN201410318617.8A CN201410318617A CN105234646A CN 105234646 A CN105234646 A CN 105234646A CN 201410318617 A CN201410318617 A CN 201410318617A CN 105234646 A CN105234646 A CN 105234646A
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- China
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- assembly
- beam assembly
- cross beam
- track
- hanging point
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Abstract
An aircraft component rapid assembly tool with an assigned track is characterized in that the aircraft component rapid assembly tool is composed of a support assembly, a cross beam assembly and a hanging point simulator mechanism; the support assembly is fixed to the ground and used for supporting the cross beam assembly, the hanging point simulator mechanism is fixed to the cross beam assembly and rigidly connected with the cross beam assembly integrally; the cross beam assembly comprises guide rails, pulleys, a stress cross beam, an adjustment cross beam and a connection plate; the hanging point simulator mechanism is composed of a fixing flat plate, a connection angle seat, a hydraulic oil cylinder, a guide shaft, a sleeve, an inner fixing block, a track flat plate, a track shaft and a simulator tentacle. Component products are moved to a pre-assembling position through the cross beam assembly, and the locator sleeve in the hanging point simulator mechanism moves up and down in a reciprocating mode along the guide shaft; the simulator tentacle is driven to move along the track shaft on the track flat plate to a pointed position, the inner fixing block is a limiting device, and the locating precision of the component products is guaranteed. The hydraulic oil cylinder is used for providing drive force in the process. The aircraft component rapid assembly tool has the advantages that the assembling precision is improved on the basis of substantially lowering the manual operation intensity.
Description
Technical field
The present invention relates to aircraft components assembling field, specifically a kind of aircraft components fixtures for rapid assembly that can improve the intended trajectory of usefulness and positioning precision.
Background technology
In current transporation by plane field, parts assembling is a ring important in final assembly, and the feature of parts product is that weight is comparatively large, need the banjo fixing butt jointing intersection point of Coordinative assembling many, and interchangeability requires high.The design of existing aircraft components banjo fixing butt jointing locator adopts rocker-arm locator substantially, the axially-movable of locator joint is utilized to reach the requirement of locator location and exit status, its shortcoming has: (1) is in order to ensure integral rigidity, locator volume often more greatly and heavier, causes manual operation to be wasted time and energy; (2) operating space is limited, the efficiency of impact operation and precision; (3) manufacturing cycle is long, efficiency of assembling is low.
Summary of the invention
In order to overcome the shortcoming of above-mentioned prior art, the invention provides a kind of aircraft components fixtures for rapid assembly of intended trajectory, realizing the object improving assembling and positioning precision on the basis significantly reducing manual operation intensity.
In order to achieve the above object, the technical solution used in the present invention is: a kind of assembly tooling, the hanging point simulator mechanism (3) comprising the bracket component (1) being fixed on ground, the transverse beam assembly (2) be connected with bracket component (1) and be connected with transverse beam assembly (2), when axle sleeve (3-06) in hanging point simulator mechanism (3) axially moves along the axis of guide (3-05), drive simulator tentacle (3-10) according to the motion of track axle (3-09) intended trajectory, to meet the requirement of product orientation, quick assembling and undercarriage.
Operation principle of the present invention is: the rolling movement adjutant parts product formed with the guide rail (2-01) in transverse beam assembly (2) and assembly pulley (2-02) moves to pre-assembled position, then the simulator tentacle (3-10) in hanging point simulator mechanism (3) is utilized product orientation to be assembled, exited along intended trajectory by simulator tentacle (3-10) after orientation assemble completes, hanging point simulator mechanism (3) adopts hydraulic jack (3-03) for driving power again.
Structural design of the present invention, driving force is made by adopting hydraulic jack (3-03) mechanism, drive simulator tentacle (3-10) along intended trajectory build-up member, significantly reducing operator's labour intensity, increasing work efficiency and ensure that the positioning precision of parts product simultaneously.
Accompanying drawing explanation
Fig. 1 is integral shaft mapping;
Fig. 2 is bracket component axonometric drawing;
Fig. 3 is transverse beam assembly axonometric drawing;
Fig. 4 is hanging point simulator assembly axonometric drawing;
Fig. 5 is hanging point simulator movement locus figure.
detailed description of the invention is as follows
By reference to the accompanying drawings the present invention is described in detail:
Referring to figs. 1 through a kind of assembly tooling of Fig. 5, comprise bracket component (1), transverse beam assembly (2) and hanging point simulator mechanism (3), bracket component (1) is as the primary load bearing body of total, adopt the square tube of 300mm × 300mm × 12mm, to ensure rigidity and the intensity of main body, according to depth-width ratio example setting underframe and contact area of ground, to ensure overall structure stability.
Transverse beam assembly (2) and bracket component (1) adopt the mode of rigidity seamless link, eliminate the local micro-strain because gap produces to greatest extent.
Hanging point simulator mechanism (3) is fixed on transverse beam assembly (2), adopts the mode of rigidity seamless link, to reduce distortion and because being out of shape the position error produced.
Simulator tentacle (3-10) in hanging point simulator mechanism (3) adopts digital transfer to combine with analog quantity transmission mounting technology when assembling, first locator is pressed laser ball data mobile to pre-assembled position, again according to the fine position simulator tentacle of gauge in kind (ball data being installed according to laser), make the position co-ordination between locator with gauge consistent, ensure the interchangeability of parts.
The track groove of track flat board (3-08) designs according to the track attitude of product orientation and undercarriage, and reserves certain safe distance, to ensure that product is not bruised.
For ensureing that the repetitive positioning accuracy of parts product is in the allowed band of Product Assembly, track axle (3-09) adopts high accuracy to assemble with the track groove in track flat board (3-08), controls the rigging error of product in allowed band.
The installation site of internal fixtion block (3-07) is determined according to the actual installation position of locator, and adopts rigid connection, is connected and fixed with lower fixed flat planar (3-04).
During parts Product Assembly, first utilize the guide rail (2-01) on transverse beam assembly (2) and assembly pulley (2-02) that parts product is moved to pre-assembled position, then the power that in hanging point simulator mechanism (3), hydraulic jack (3-03) provides is utilized, drive sleeve (3-06) pumps along the axis of guide (3-05), the movement locus axle (3-09) driving simulator tentacle (3-10) to design on track flat board (3-08) moves to assigned address, and spacing by internal fixtion block (3-07), to ensure the positioning precision of parts product.
After parts Product Assembly completes, then according to the movement locus of specifying, hanging point simulator mechanism (3) is exited to precalculated position, to ensure product undercarriage.
Designed by said structure, significantly can improve the assembly precision of aircraft components, reduce resetting error, reduce the orientation assemble error that human factor produces, reduce labor strength simultaneously, increase work efficiency.
Claims (5)
1. the aircraft components fixtures for rapid assembly of intended trajectory a: when it is characterized in that axle sleeve (3-06) axially moves along the axis of guide (3-05), drives simulator tentacle (3-10) to move according to track axle (3-09) intended trajectory.
2. assembly tooling according to claim 1, it is characterized in that, the aircraft components fixtures for rapid assembly of described a kind of intended trajectory, the hanging point simulator mechanism (3) comprising bracket component (1), the transverse beam assembly (2) be connected with bracket component (1) and be connected with transverse beam assembly (2).
3. assembly tooling according to claim 2, it is characterized in that, described bracket component (1) is made up of base assembly (1-01), strut assemblies (1-02) and upper beam assembly (1-03), base assembly (1-01) fixes on the ground, and strut assemblies (1-02) is fixed on base assembly (1-01) and goes up and support upper beam assembly (1-03).
4. assembly tooling according to claim 2, it is characterized in that, described transverse beam assembly (2) is made up of guide rail (2-01), assembly pulley (2-02), stressed crossbeam (2-03), adjustment crossbeam (2-04) and connecting plate (2-05), guide rail (2-01) and assembly pulley (2-02) form rolling movement pair, and transverse beam assembly (2) adopts seamless being rigidly connected by guide rail (2-01) and the upper beam assembly (1-03) of bracket component (1).
5. assembly tooling according to claim 2, it is characterized in that, described hanging point simulator mechanism (3) is made up of upper fixed flat planar (3-01), joint angle seat (3-02), hydraulic jack (3-03), lower fixed flat planar (3-04), the axis of guide (3-05), sleeve (3-06), internal fixtion block (3-07), track flat board (3-08), track axle (3-09) and simulator tentacle (3-10), and whole hanging point simulator mechanism (3) adopts rigidity seamless link by upper fixed flat planar (3-01) and the connecting plate (2-05) in transverse beam assembly (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410318617.8A CN105234646A (en) | 2014-07-07 | 2014-07-07 | Aircraft component rapid assembly tool with assigned track |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410318617.8A CN105234646A (en) | 2014-07-07 | 2014-07-07 | Aircraft component rapid assembly tool with assigned track |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105234646A true CN105234646A (en) | 2016-01-13 |
Family
ID=55032596
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410318617.8A Pending CN105234646A (en) | 2014-07-07 | 2014-07-07 | Aircraft component rapid assembly tool with assigned track |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105234646A (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1174796A (en) * | 1996-08-22 | 1998-03-04 | 波音公司 | Counterbalance mechanism for inwardly and upwardly opening plug-type airplane cargo doors |
| CN101745905A (en) * | 2010-02-03 | 2010-06-23 | 北京航空航天大学 | Multi-degree of freedom adjustable assembling platform used for butt joint of aircraft wings |
| CN103350333A (en) * | 2013-06-03 | 2013-10-16 | 大连理工大学 | Tiny component assembling device and method |
| JP2014151393A (en) * | 2013-02-07 | 2014-08-25 | Honda Motor Co Ltd | Work assembly apparatus and work assembly method |
-
2014
- 2014-07-07 CN CN201410318617.8A patent/CN105234646A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1174796A (en) * | 1996-08-22 | 1998-03-04 | 波音公司 | Counterbalance mechanism for inwardly and upwardly opening plug-type airplane cargo doors |
| CN101745905A (en) * | 2010-02-03 | 2010-06-23 | 北京航空航天大学 | Multi-degree of freedom adjustable assembling platform used for butt joint of aircraft wings |
| JP2014151393A (en) * | 2013-02-07 | 2014-08-25 | Honda Motor Co Ltd | Work assembly apparatus and work assembly method |
| CN103350333A (en) * | 2013-06-03 | 2013-10-16 | 大连理工大学 | Tiny component assembling device and method |
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| 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 | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160113 |