CN104176270B - A kind of aircraft components joint covering method for rapidly positioning - Google Patents
A kind of aircraft components joint covering method for rapidly positioning Download PDFInfo
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- CN104176270B CN104176270B CN201410470808.6A CN201410470808A CN104176270B CN 104176270 B CN104176270 B CN 104176270B CN 201410470808 A CN201410470808 A CN 201410470808A CN 104176270 B CN104176270 B CN 104176270B
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Abstract
The present invention relates to a kind of aircraft components joint covering method for rapidly positioning, belong to transporation by plane field.Comprise the steps: to identify 4 position of positioning hole points A, B, C, D at the joint of two aircraft componentss to be docked; With A, B, C, D for benchmark, L1, L2, L3, L4 at a certain distance, extends some A1, B1, C1, D1 respectively to making straight line outside parts I, II; Docking covering is placed into the joint of parts I, II, ensures that the amount of lap of covering and parts I, II junction is evenly also fitted closely; With A1, B1, C1, D1 for bench mark, by extended line AA1, BB1, CC1, DD1, position of positioning hole point is seted off by contrast on docking covering, drill knock hole respectively, and locate with spring holder; After covering is fixing, removal is taken parts I, II and is connect the unnecessary surplus in place; Pull down the spring holder of fixing covering and parts I, II, pull down covering and remove the surplus of covering, entering covering installation procedure.The method not only can improve the installation accuracy of aircraft components docking rear enclosed (semiclosed) district covering, and fast simple to operate, and reliable in quality, checks intuitive and convenient.
Description
Technical field
The present invention relates to a kind of method for rapidly positioning of skin part of aircraft portion (group) part joint, after aircraft components docking, fixed, the installation of closing (semiclosed) docking area place panel beating class skin part of formation, belong to transporation by plane field.
Background technology
Along with the continuous lifting of present generation aircraft performance, to the pneumatic property of housing construction and the requirement of globality more and more higher, complex appearance structure (as double curved surface) in airplane design, manufacture the number of applications in field and increase gradually.The assembling of aircraft portion (group) part 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 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 in some docking operations (station) without tool locating, then need by line location, particularly after Large Aircraft Components docking, the covering class part closing (semiclosed) docking zone location formed, then need to rely on operator by line, covering and its link are overlapped size instead on covering, then positions and install.Although the method exists
-determine degree to solve parts and docking installation and the inspection of rear enclosed (semiclosed) district covering, but the method cycle is longer, operator's labour intensity is large, needs at substantial human and material resources; Owing to relying on the manual location of ruling of operator completely, therefore position error is comparatively large, very easily causes covering to scrap, and product design is difficult to ensure.
Summary of the invention
The object of this invention is to provide a kind of after aircraft components docking, the installation method closing (semiclosed) place of 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, comprise the steps:
(1) according to installed covering shape and size, 4 position of positioning hole points A, B, C, D are identified at the joint of two aircraft componentss to be docked, wherein position of positioning hole point A, B are positioned on aircraft components I, and position of positioning hole point C, D are positioned on aircraft components II;
(2) with aforementioned position of positioning hole point A, B, C, D for benchmark, L1, L2, L3, L4 at a certain distance, point A1, B1, C1, D1 is extended respectively to making straight line outside parts I, parts II, extended line AA1, BB1, CC1, DD1 of being formed extend to away from direction, docking area, and with parts joint axes normal, 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 of covering III pre-determined bit to parts I, parts II will be docked, ensure that covering III is evenly also fitted closely with the amount of lap of parts I, parts II junction;
(4) with A1, B1, C1, D1 for bench mark, by the length L1 of extended line AA1, BB1, CC1, DD1, L2, L3, L4 as orientation distance, position of positioning hole point is seted off by contrast on docking covering III, drills knock hole respectively, and locate with spring holder;
(5) covering III fixing after, mark the unnecessary surplus of covering and parts I, 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, entering covering installation procedure.
Line AB and the CD of described position of positioning hole point A, B and position of positioning hole point C, D is parallel to each other.
Length L1, L2, L3, L4 length range of described extended line AA1, BB1, CC1, DD1 are being 5 ~ 20mm.
Beneficial effect of the present invention: the present invention adopts such scheme, solves during original docking area covering is installed that the cycle existed is long, work capacity is large, measures inaccurate 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 fast simple to operate, and reliable in quality, checks intuitive and convenient, can shorten aircraft components joint covering installation period more than 50%.
Accompanying drawing explanation
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, 4 φ 4.1 position of positioning hole points A, B, C, D are identified respectively at the joint of parts I, parts II, wherein position of positioning hole point A, B are positioned on aircraft components I, and position of positioning hole point C, D are positioned on 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 is parallel to each other;
(2) with aforementioned position of positioning hole point A, B, C, D for benchmark, L1, L2, L3, L4 at a certain distance, point A1, B1, C1, D1 is extended respectively to making straight line outside parts I, parts II, extended line AA1, BB1, CC1, DD1 of being formed extend to away from direction, docking area, and with parts joint axes normal, the length range that the length of extended line AA1, BB1, CC1, DD1 is respectively L1, L2, L3, L4 controls within 5 ~ 20mm usually, and L1, L2, L3, L4≤1/2L
i-II, wherein L
i-IIfor the spacing between parts I, parts II;
(3) joint of covering III pre-determined bit to parts I, parts II will be docked, ensure that covering III is evenly also fitted closely with the amount of lap of parts I, parts II junction;
(4) with A1, B1, C1, D1 for bench mark, by the length L1 of extended line AA1, BB1, CC1, DD1, L2, L3, L4 as orientation distance, position of positioning hole point is seted off by contrast on docking covering III, drills knock hole respectively, and locate with spring holder;
(5) covering III fixing after, mark the unnecessary surplus of covering and parts I, 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 3 and remove the surplus of covering, and by former requirement, covering being installed.
Claims (3)
1. an aircraft components joint covering method for rapidly positioning, is characterized in that, comprise the steps:
(1) according to installed covering shape and size, 4 position of positioning hole points A, B, C, D are identified at the joint of two aircraft componentss to be docked, wherein position of positioning hole point A, B are positioned on aircraft components I, and position of positioning hole point C, D are positioned on aircraft components II;
(2) with aforementioned position of positioning hole point A, B, C, D for benchmark, L1, L2, L3, L4 at a certain distance, point A1, B1, C1, D1 is extended respectively to making straight line outside parts I, parts II, extended line AA1, BB1, CC1, DD1 of being formed extend to away from direction, docking area, and with parts joint axes normal, 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 of covering III pre-determined bit to parts I, parts II will be docked, ensure that covering III is evenly also fitted closely with the amount of lap of parts I, parts II junction;
(4) with A1, B1, C1, D1 for bench mark, by the length L1 of extended line AA1, BB1, CC1, DD1, L2, L3, L4 as orientation distance, position of positioning hole point is seted off by contrast on docking covering III, drills knock hole respectively, and locate with spring holder;
(5) covering III fixing after, mark the unnecessary surplus of covering and parts I, 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, entering covering installation procedure.
2. a kind of aircraft components joint covering method for rapidly positioning according to claim 1, it is characterized in that, line AB and the CD of described position of positioning hole point A, B and position of positioning hole point C, D is parallel to each other.
3. a kind of aircraft components joint covering method for rapidly positioning according to claim 1, it is characterized in that, the length L1 of described extended line AA1, BB1, CC1, DD1, L2, L3, L4 length range are 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 |
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| Publication Number | Publication Date |
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| CN104176270A CN104176270A (en) | 2014-12-03 |
| CN104176270B true CN104176270B (en) | 2016-04-20 |
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| 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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Families Citing this family (3)
| 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 |
| CN105035354B (en) * | 2015-08-04 | 2017-09-29 | 航天材料及工艺研究所 | Coordinate frock and assembly method in a kind of net side of composite material skin |
| CN111438393A (en) * | 2020-05-15 | 2020-07-24 | 沈阳飞机工业（集团）有限公司 | Quick positioning and guiding hole device for riveting hole of aircraft skin and use method |
Family Cites Families (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 |
| US9352822B2 (en) * | 2012-05-30 | 2016-05-31 | The Boeing Company | Bonded composite airfoil |
| CN102975866B (en) * | 2012-12-05 | 2015-01-28 | 成都晋威科技有限公司 | Self-adaptive flexible airplane assembly device and method |
| CN103072700B (en) * | 2013-01-21 | 2015-06-03 | 西北工业大学 | Method for flexibly assembling leading edge flap |
| CN103847981B (en) * | 2014-03-17 | 2015-12-30 | 沈阳飞机工业（集团）有限公司 | A kind of assembling of Double curve degree covering class part and the method for inspection |
| CN104002993B (en) * | 2014-06-13 | 2016-04-20 | 沈阳飞机工业（集团）有限公司 | A kind of flexible apparatus to the assembling of aircraft housing and assembly method thereof |
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