CN104176270A - Fast locating method for skin at butt joint portion of aircraft components - Google Patents
Fast locating method for skin at butt joint portion of aircraft components Download PDFInfo
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- CN104176270A CN104176270A CN201410470808.6A CN201410470808A CN104176270A CN 104176270 A CN104176270 A CN 104176270A CN 201410470808 A CN201410470808 A CN 201410470808A CN 104176270 A CN104176270 A CN 104176270A
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- butt joint
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Abstract
The invention relates to a fast locating method for a skin at the butt joint portion of aircraft components, and belongs to the field of aircraft assembly. The method comprises the steps of marking four locating hole position points A, B, C and D at the butt joint portion of the two aircraft components to be connected in a butt joint mode; with the A, B, C and D as datum points, drawing straight line extension points A1, B1, C1 and D1 to the outer sides of the components I and II respectively according to certain distances L1, L2, L3 and L4; placing the butt joint skin at the butt joint portion of the components I and II, and guaranteeing that the amount of overlap of the connection portions of the skin and the components I and II is uniform and the skin is closely attached to the components I and II; with the A1, B1, C1 and D 1 as datum points, reflecting the locating hole position points to the butt joint skin according to extension lines AA1, BB1, CC1 and DD1, drilling locating holes respectively, and adopting spring locating pins for locating; after fixing the skin, removing redundant margins at the overlap portion of the components I and II; disassembling the spring locating pins fixing the skin and the components I and II, disassembling the skin, removing margins of the skin, and starting the skin installation process. According to the method, the installation accuracy of the skin in a closed or semi-closed area formed after butt joint of the aircraft components can be improved, operation is easy and fast, the quality is reliable, and inspection is visual and convenient.
Description
Technical field
The present invention relates to the method for rapidly positioning of the skin part of a kind of aircraft portion (group) part joint, after aircraft components docking, fixed, the installation of sealing (semiclosed) the docking area place panel beating class skin part of formation, belong to aircraft assembling field.
Background technology
Along with the continuous lifting of present generation aircraft performance, the pneumatic property to housing construction and the requirement of globality are more and more higher, and complex appearance structure (as double curved surface) increases gradually in the number of applications in airplane design, manufacture field.Aircraft portion (group) part assembling is an important content of aircraft manufacturing, and it is by certain setting-up procedure, according to assembly tooling, Assembly of the parts is become to the process of portion's (group) part.Because aircraft is in assembly set, general assembly operation fitting process, all use assembly tooling mounting parts, therefore this part accuracy is higher, harmony good, but the docking operation (station) at some without tool locating, needs by line location, particularly after Large Aircraft Components docking, the covering class part of sealing (semiclosed) the docking zone location forming, need to rely on operator by line, covering and its link are overlapped to size instead to covering, then position and install.Although the method exists
-determine to have solved parts in installation and the inspection of docking rear enclosed (semiclosed) district covering in degree, but the method cycle is longer, operator's labour intensity is large, need expend a large amount of human and material resources; Owing to relying on the manual line of operator location completely, therefore position error is larger, very easily cause covering to scrap, product design is difficult to ensure.
Summary of the invention
The object of this invention is to provide one after aircraft components docking, the installation method of sealing (semiclosed) place of the district covering class part of formation.
The object of the invention is to be achieved through the following technical solutions:
A kind of aircraft components joint covering method for rapidly positioning, is characterized in that, comprises the steps:
(1) according to installed covering shape and size, identify 4 position of positioning hole point A, B, C, D at the joint of two aircraft componentss to be docked, wherein position of positioning hole point A, B are positioned in aircraft components I, and position of positioning hole point C, D are positioned in aircraft components II;
(2) taking aforementioned position of positioning hole point A, B, C, D as benchmark, L1, L2, L3, L4 at a certain distance, make straight line to parts I, parts II outside respectively and extend some A1, B1, C1, D1, extended line AA1, the BB1, CC1, the DD1 that form are to extending away from docking area direction, and vertical with parts joint axis, the length of extended line AA1, BB1, CC1, DD1 is respectively L1, L2, L3, L4, and L1, L2, L3, L4≤1/2L
i-II, wherein L
i-IIfor the spacing between parts I, parts II;
(3) joint to parts I, parts II by docking covering III pre-determined bit, ensures that the amount of lap of covering III and parts I, parts II junction is evenly also fitted closely;
(4) taking A1, B1, C1, D1 as bench mark,, as orientation distance position of positioning hole point is seted off by contrast in docking covering III by the length L of extended line AA1, BB1, CC1, DD1 1, L2, L3, L4, drill respectively knock hole, and locate with spring holder;
(5) covering III fixing after, mark covering and parts I, the unnecessary surplus of parts II lap-joint with covering scriber;
(6) pull down the spring holder of fixing covering III and parts I, parts II, pull down covering III and remove the surplus of covering, enter covering installation procedure.
Described position of positioning hole point A, B and line AB and the CD of position of positioning hole point C, D are parallel to each other.
Described extended line AA1, BB1, the length L 1 of CC1, DD1, L2, L3, L4 length range are being 5 ~ 20mm.
Beneficial effect of the present invention: the present invention adopts such scheme, the cycle that has solved existence in the covering installation of original docking area is grown, work capacity is large, it is inaccurate to measure and be easily subject to the problems such as operator's operant level factor impact.The method not only can improve the installation accuracy of aircraft components docking rear enclosed (semiclosed) district covering, and simple to operate quick, and reliable in quality, checks intuitive and convenient, can shorten aircraft components joint covering installation period more than 50%.
Brief description of the drawings
Fig. 1 is the enforcement view of the inventive method.
Detailed description of the invention
A kind of aircraft components joint covering method for rapidly positioning, as shown in Figure 1, comprises the steps:
(1) according to installed covering shape and size, identify 4 φ, 4.1 position of positioning hole point A, B, C, D at the joint of parts I, parts II respectively, wherein position of positioning hole point A, B are positioned in aircraft components I, and position of positioning hole point C, D are positioned in aircraft components II; Wherein line AB and the CD of position of positioning hole point A, B and position of positioning hole point C, D are parallel to each other;
(2) taking aforementioned position of positioning hole point A, B, C, D as benchmark, L1, L2, L3, L4 at a certain distance, make straight line to parts I, parts II outside respectively and extend some A1, B1, C1, D1, extended line AA1, the BB1, CC1, the DD1 that form are to extending away from docking area direction, and vertical with parts joint axis, within the length range that the length of extended line AA1, BB1, CC1, DD1 is respectively L1, L2, L3, L4 is controlled at 5 ~ 20mm conventionally, and L1, L2, L3, L4≤1/2L
i-II, wherein L
i-IIfor the spacing between parts I, parts II;
(3) joint to parts I, parts II by docking covering III pre-determined bit, ensures that the amount of lap of covering III and parts I, parts II junction is evenly also fitted closely;
(4) taking A1, B1, C1, D1 as bench mark,, as orientation distance position of positioning hole point is seted off by contrast in docking covering III by the length L of extended line AA1, BB1, CC1, DD1 1, L2, L3, L4, drill respectively knock hole, and locate with spring holder;
(5) covering III fixing after, mark covering and parts I, the unnecessary surplus of parts II lap-joint with covering scriber;
(6) pull down the spring holder of fixing covering III and parts I 1, parts II 2, pull down covering III and remove the surplus of covering, and by former requirement, covering is installed.
Claims (3)
1. an aircraft components joint covering method for rapidly positioning, is characterized in that, comprises the steps:
(1) according to installed covering shape and size, identify 4 position of positioning hole point A, B, C, D at the joint of two aircraft componentss to be docked, wherein position of positioning hole point A, B are positioned in aircraft components I, and position of positioning hole point C, D are positioned in aircraft components II;
(2) taking aforementioned position of positioning hole point A, B, C, D as benchmark, L1, L2, L3, L4 at a certain distance, make straight line to parts I, parts II outside respectively and extend some A1, B1, C1, D1, extended line AA1, the BB1, CC1, the DD1 that form are to extending away from docking area direction, and vertical with parts joint axis, the length of extended line AA1, BB1, CC1, DD1 is respectively L1, L2, L3, L4, and L1, L2, L3, L4≤1/2L
i-II, wherein L
i-IIfor the spacing between parts I, parts II;
(3) joint to parts I, parts II by docking covering III pre-determined bit, ensures that the amount of lap of covering III and parts I, parts II junction is evenly also fitted closely;
(4) taking A1, B1, C1, D1 as bench mark,, as orientation distance position of positioning hole point is seted off by contrast in docking covering III by the length L of extended line AA1, BB1, CC1, DD1 1, L2, L3, L4, drill respectively knock hole, and locate with spring holder;
(5) covering III fixing after, mark covering and parts I, the unnecessary surplus of parts II lap-joint with covering scriber;
(6) pull down the spring holder of fixing covering III and parts I, parts II, pull down covering III and remove the surplus of covering, enter covering installation procedure.
2. a kind of aircraft components joint covering method for rapidly positioning according to claim 1, is characterized in that, described position of positioning hole point A, B and line AB and the CD of position of positioning hole point C, D are parallel to each other.
3. a kind of aircraft components joint covering method for rapidly positioning according to claim 1, is characterized in that, described extended line AA1, BB1, the length L 1 of CC1, DD1, L2, L3, L4 length range are being 5 ~ 20mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410470808.6A CN104176270B (en) | 2014-09-16 | 2014-09-16 | A kind of aircraft components joint covering method for rapidly positioning |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410470808.6A CN104176270B (en) | 2014-09-16 | 2014-09-16 | A kind of aircraft components joint covering method for rapidly positioning |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104176270A true CN104176270A (en) | 2014-12-03 |
| CN104176270B CN104176270B (en) | 2016-04-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410470808.6A Active CN104176270B (en) | 2014-09-16 | 2014-09-16 | A kind of aircraft components joint covering method for rapidly positioning |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104816837A (en) * | 2015-05-07 | 2015-08-05 | 哈尔滨飞机工业集团有限责任公司 | Aluminum alloy skin digital assembly method |
| CN105035354A (en) * | 2015-08-04 | 2015-11-11 | 航天材料及工艺研究所 | Composite material skin net edge coordination tools and assembling method for skins |
Citations (6)
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|---|---|---|---|---|
| CN202080431U (en) * | 2011-02-17 | 2011-12-21 | 中国航空工业集团公司西安飞机设计研究所 | Intelligent skin |
| CN102975866A (en) * | 2012-12-05 | 2013-03-20 | 成都晋威科技有限公司 | Self-adaptive flexible airplane assembly device and method |
| CN103072700A (en) * | 2013-01-21 | 2013-05-01 | 西北工业大学 | Method for flexibly assembling leading edge flap |
| CN103448901A (en) * | 2012-05-30 | 2013-12-18 | 波音公司 | Bonded composite airfoil and fabrication method |
| CN103847981A (en) * | 2014-03-17 | 2014-06-11 | 沈阳飞机工业（集团）有限公司 | Assembly and inspection method of dual-curvature skin type part |
| CN104002993A (en) * | 2014-06-13 | 2014-08-27 | 沈阳飞机工业（集团）有限公司 | Flexible device for assembling airplane shell and assembly method of flexible device |
-
2014
- 2014-09-16 CN CN201410470808.6A patent/CN104176270B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202080431U (en) * | 2011-02-17 | 2011-12-21 | 中国航空工业集团公司西安飞机设计研究所 | Intelligent skin |
| CN103448901A (en) * | 2012-05-30 | 2013-12-18 | 波音公司 | Bonded composite airfoil and fabrication method |
| CN102975866A (en) * | 2012-12-05 | 2013-03-20 | 成都晋威科技有限公司 | Self-adaptive flexible airplane assembly device and method |
| CN103072700A (en) * | 2013-01-21 | 2013-05-01 | 西北工业大学 | Method for flexibly assembling leading edge flap |
| CN103847981A (en) * | 2014-03-17 | 2014-06-11 | 沈阳飞机工业（集团）有限公司 | Assembly and inspection method of dual-curvature skin type part |
| CN104002993A (en) * | 2014-06-13 | 2014-08-27 | 沈阳飞机工业（集团）有限公司 | Flexible device for assembling airplane shell and assembly method of flexible device |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104816837A (en) * | 2015-05-07 | 2015-08-05 | 哈尔滨飞机工业集团有限责任公司 | Aluminum alloy skin digital assembly method |
| CN105035354A (en) * | 2015-08-04 | 2015-11-11 | 航天材料及工艺研究所 | Composite material skin net edge coordination tools and assembling method for skins |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104176270B (en) | 2016-04-20 |
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