CN111977018A - Supporting method for airplane body component assembly posture adjustment positioning - Google Patents
Supporting method for airplane body component assembly posture adjustment positioning Download PDFInfo
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- CN111977018A CN111977018A CN202010747462.5A CN202010747462A CN111977018A CN 111977018 A CN111977018 A CN 111977018A CN 202010747462 A CN202010747462 A CN 202010747462A CN 111977018 A CN111977018 A CN 111977018A
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- body component
- clamping plate
- bracket
- supporting
- airplane body
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Abstract
The supporting method for the assembly, posture adjustment and positioning of the airplane body component comprises the steps of supporting the airplane body component through an integral tool bracket, enabling a three-coordinate positioning system to be in cross-linking with the integral tool bracket, adjusting the integral tool bracket through the three-coordinate positioning system to achieve posture adjustment of the airplane body component, replacing a traditional support joint which is independently installed through the integral tool bracket, avoiding assembly stress caused by posture adjustment due to a supporting mode, improving product quality, being simple in technological process and convenient to operate, achieving rapid station transfer of the airplane body component, and having general popularization for posture adjustment and positioning of the airplane body component.
Description
Technical Field
The application relates to the technical field of airplane assembly, in particular to a supporting method for realizing the attitude adjusting and positioning process of airplane components through an integral tooling bracket.
Background
The butt joint of the airplane body components is an important content of airplane assembly, and the butt joint state of the components largely determines the manufacturing period, the production cost and the final quality of the airplane. At present, in a digital flexible assembly system, a support mode based on the matching of a three-coordinate positioning system and a process joint installed on an aircraft body is mostly adopted for adjusting and positioning the attitude of an aircraft body component, namely, the process joint (support joint for short) with a ball head structure for supporting the aircraft body component is installed on the aircraft body component, the three-coordinate positioning system is provided with an inverted cone structure, and generally, the three-coordinate positioning system comprises more than three independent three-coordinate positioners which are matched with the ball head structure on the support joint, so that the support of the aircraft component product is realized for adjusting the attitude and positioning.
The mode that the support joint adopted the frock locator location to install in the profile of organism part more, and the location error of organism part appearance error and support joint leads to the great and difficult control of the installation tolerance of support joint, and simultaneously, the support joint is generally installed at part assembly station, and the handling is used to part butt joint station, consequently with also having certain commentaries on classics station error, the relative deviation between support joint and the three-coordinate positioning system can directly arouse the problem of accent appearance stress. Secondly, the contact area between the support joint and the machine body part is small, and the local deformation on the machine body part is large, so that the product quality is influenced. Finally, the number of the supporting joints is at least three in general when the supporting joints are matched with a three-coordinate positioning system, and in order to ensure accurate installation of the supporting joints, the positioning tool is complex in structure, the installation process is complex, and the manufacturing period is influenced.
Therefore, a supporting method for adjusting and positioning the attitude of the airplane body component needs to be designed, the influence of stress generated by a supporting mode on the adjusting and positioning of the attitude of the airplane component is avoided, the deviation between the actual attitude state of the airplane component product and the theoretical model of the airplane is reduced, the product quality is improved, and the realization of stress-free assembly is the development direction of the existing airplane assembly technology. Meanwhile, the rapid station transfer of the parts is realized, and the assembly period is shortened so as to meet the assembly production requirement of the butt joint of the airplane parts.
Disclosure of Invention
The application aims to provide a supporting method for adjusting and positioning the attitude of an airplane body component, which can realize the quick station transfer and stress-free attitude adjusting and positioning of the airplane body component.
A supporting method for the assembly, posture adjustment and positioning of airplane body components is characterized by comprising the following steps of supporting the airplane body components through an integral tooling bracket, enabling a three-coordinate positioning system to be in cross-linking with the integral tooling bracket, and adjusting the integral tooling bracket through the three-coordinate positioning system to achieve posture adjustment of the airplane body components.
The integral tooling bracket comprises a semi-enclosure frame type bracket base and an appearance supporting clamping plate, a plurality of ball head structures butted with a three-coordinate positioning system are arranged on the bracket base, at least two appearance supporting clamping plates are fixed on the upper surface of the bracket base, the appearance supporting clamping plate is matched with the appearance of an airplane body part, and a limiting locking mechanism for limiting the position of the airplane body part is further arranged on each appearance supporting clamping plate.
The upper surface of the bracket base of the integral tooling bracket is also provided with at least one auxiliary supporting appearance clamping plate, the auxiliary supporting appearance clamping plate is fixed on the upper surface of the bracket base through a lifting mechanism, and the auxiliary supporting appearance clamping plate is parallel to the appearance supporting clamping plate.
When the airplane body component is adjusted in posture, the auxiliary supporting appearance clamping plate is lowered by the lifting mechanism to be separated from the supporting of the airplane body component, the integral tool bracket is adjusted by the three-coordinate positioning system to adjust the posture of the airplane body component, and the auxiliary supporting appearance clamping plate is lifted by the lifting mechanism to be supported in an auxiliary mode for workers to enter the airplane body component to work.
The beneficial effect of this application lies in: the airplane component is supported by the integral tool bracket to adjust the posture and position, the traditional independently-installed supporting joint is replaced, the assembling stress generated by adjusting the posture in a supporting mode is avoided, and the product quality is improved. Meanwhile, the relative position between the tool bracket and the aircraft component has no accurate requirement, the process is simple, the operation is convenient, and the rapid station transfer of the aircraft component is realized. The process method is simple in principle, and has general popularization for adjusting and positioning the machine body parts.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a schematic view of a unitary tooling bracket construction.
FIG. 2 is a schematic view of a supporting method for adjusting the attitude and positioning of the components of the airplane body.
The numbering in the figures illustrates: 1 integral frock bracket, 2 appearance support cardboards, 3 auxiliary stay appearance cardboard, 4 bulb structures, 5 spacing locking mechanism, 6 elevating system, 7 three-dimensional positioning system, 8 aircraft organism parts.
Detailed Description
Referring to the attached drawings, the support method for adjusting and positioning the attitude of the airplane body component supports the airplane body component 8 through the integral tooling bracket 1, adopts a three-coordinate positioning system 7 to be cross-linked with the integral tooling bracket 1, and adjusts the attitude of the airplane body component 8 by adjusting the integral tooling bracket 1 through the three-coordinate positioning system 7. This 1 structural style of integral frock bracket contains the bracket base unanimous with 8 bottom profile sizes of aircraft body part, be equipped with in bracket base lower part with a plurality of bulb structures 4 of last cup awl matched with of three-dimensional locator system, be fixed with two at least appearances on bracket base upper portion and support cardboard 2, this appearance supports cardboard 2 and aircraft body part 8's appearance and matches, every appearance supports cardboard 2 and still is equipped with the spacing locking mechanism 5 of injecing the 8 positions of aircraft body part. Simultaneously, the upper portion of bracket base still is equipped with at least one auxiliary stay appearance cardboard 3, and this auxiliary stay appearance cardboard 3 is fixed at the upper surface of bracket base through an elevating system 6, and auxiliary stay appearance cardboard 3 is parallel to each other with appearance support cardboard 2. Before the airplane body component 8 is adjusted the appearance location, hoist the airplane body component 8 to integral frock bracket 1 on, support 2 supports of cardboard through appearance on the frock bracket 1, appearance support cardboard 2 does not have accurate relative position requirement with the airplane body component 8, only support spacing locking mechanism 5 on the cardboard 2 restriction airplane body component 8 and integral frock bracket 1 through the appearance and adjust the relative displacement of appearance in-process can. In the attitude adjusting process of the airplane body component 1, the auxiliary support appearance clamping plate is lowered through the lifting mechanism 6 to be separated from the support of the airplane body component 8, the integral tool bracket 1 is adjusted through the three-coordinate positioning system 7 to adjust the attitude of the airplane body component 8, and the auxiliary support appearance clamping plate 3 is lifted through the lifting mechanism 6 to be used for implementing auxiliary support on the airplane body component 8 and enabling a worker to enter the airplane body component to work.
The posture adjusting steps are as follows:
1) adjusting the integral tool bracket 1 through a three-coordinate positioning system 7 to enable the integral tool bracket 1 to be in a horizontal state; 2) the auxiliary supporting clamping plate 3 is lowered to be in a non-working state, and the limiting mechanism 5 is opened to be in the non-working state; 3) hoisting the airplane body component 8 to the integral tooling bracket 1 to ensure that the airplane body component 8 is attached to the appearance supporting clamping plate 2 on the tooling bracket; 4) closing the limiting locking mechanism 5, and fixing the relative position of the airplane body part on the integral tool bracket 1; 5) the auxiliary support appearance clamping plate 3 is adjusted to be in a working state, the airplane body component 8 is supported in an auxiliary mode, and workers can enter the airplane body component to work before the airplane body component is adjusted in posture and positioned. 6) When the attitude of the aircraft body part is adjusted, the auxiliary supporting clamping plate 3 is lowered again to be in a non-working state; 7) the space position of the integral tool bracket 1 is adjusted through the three-coordinate positioning system 7, so that the attitude adjusting and positioning of the airplane body 8 are realized. 8) And lifting the auxiliary support clamping plate 3 to a working state to realize auxiliary support on the airplane body part 8, so that workers can enter the airplane body part to work.
Claims (4)
1. A supporting method for the assembly, posture adjustment and positioning of airplane body components is characterized by comprising the following steps of supporting the airplane body components through an integral tooling bracket, enabling a three-coordinate positioning system to be in cross-linking with the integral tooling bracket, and adjusting the integral tooling bracket through the three-coordinate positioning system to achieve posture adjustment of the airplane body components.
2. The method for supporting the assembly, attitude adjustment and positioning of the aircraft body components according to claim 1, wherein the integral tooling pallet comprises a semi-enclosure type pallet base and a shape supporting clamping plate, a plurality of ball head structures which are butted with a three-coordinate positioning system are arranged on the pallet base, at least two shape supporting clamping plates are fixed on the upper surface of the pallet base, the shape supporting clamping plates are matched with the shape of the aircraft body components, and each shape supporting clamping plate is further provided with a limit locking mechanism for limiting the position of the aircraft body components.
3. An aircraft body component assembly posture-adjusting positioning support method as claimed in claim 1 or 2, characterized in that the upper surface of the bracket base of the integral tooling bracket is further provided with at least one auxiliary support contour clamping plate, the auxiliary support contour clamping plate is fixed on the upper surface of the bracket base through a lifting mechanism, and the auxiliary support contour clamping plate and the contour support clamping plate are parallel to each other.
4. A support method for the assembly, posture adjustment and positioning of an aircraft body component as claimed in claim 3, wherein when the aircraft body component is adjusted in posture, the auxiliary support appearance clamping plate is lowered by the lifting mechanism to be separated from the support of the aircraft body component, the integrated tool bracket is adjusted by the three-coordinate positioning system to adjust the posture of the aircraft body component, and then the auxiliary support appearance clamping plate is lifted by the lifting mechanism to be supported in an auxiliary manner for the worker to enter the aircraft body component to work.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010747462.5A CN111977018A (en) | 2020-07-29 | 2020-07-29 | Supporting method for airplane body component assembly posture adjustment positioning |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010747462.5A CN111977018A (en) | 2020-07-29 | 2020-07-29 | Supporting method for airplane body component assembly posture adjustment positioning |
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| Publication Number | Publication Date |
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| CN111977018A true CN111977018A (en) | 2020-11-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010747462.5A Pending CN111977018A (en) | 2020-07-29 | 2020-07-29 | Supporting method for airplane body component assembly posture adjustment positioning |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113734459A (en) * | 2021-05-19 | 2021-12-03 | 中航西安飞机工业集团股份有限公司 | Attitude adjusting and positioning method for wall plate on lower surface of airplane body |
| CN113858086A (en) * | 2021-05-19 | 2021-12-31 | 中航西安飞机工业集团股份有限公司 | Positioning tool and positioning method for cylindrical part |
| CN114291288A (en) * | 2022-01-05 | 2022-04-08 | 中国航空制造技术研究院 | Production line system suitable for fuselage assembly |
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| EP0290809A2 (en) * | 1987-04-14 | 1988-11-17 | Northrop Grumman Corporation | Manufacturing system using three-dimensional graphics models |
| CN101907893A (en) * | 2010-07-02 | 2010-12-08 | 北京航空航天大学 | Aircraft component attitude adjusting assembly system based on parallel mechanism with six degrees of freedom and debugging method |
| CN102001451A (en) * | 2010-11-12 | 2011-04-06 | 浙江大学 | Airplane component attitude adjusting and butting system based on four numeric control positioners, attitude adjusting platform and mobile bracket and corresponding method |
| CN102730197A (en) * | 2012-05-16 | 2012-10-17 | 中国商用飞机有限责任公司 | Machine body positioning and posture adjusting device and method |
| CN104148914A (en) * | 2014-08-07 | 2014-11-19 | 天津航天长征火箭制造有限公司 | Posture adjustment assembly system used for butt joint of components of rocket and posture adjustment method |
| CN105479450A (en) * | 2015-12-15 | 2016-04-13 | 南昌航空大学 | Six-degree-of-freedom non-redundant drive automatic fuselage posture adjusting mechanism |
| CN107283159A (en) * | 2017-08-14 | 2017-10-24 | 上海航天设备制造总厂 | Large-scale section numerical control posture adjustment Butt Assembling system |
| CN110001998A (en) * | 2019-03-12 | 2019-07-12 | 南京航空航天大学 | A kind of Large Aircraft Components frame structure docking guide device and method based on laser ranging |
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2020
- 2020-07-29 CN CN202010747462.5A patent/CN111977018A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0290809A2 (en) * | 1987-04-14 | 1988-11-17 | Northrop Grumman Corporation | Manufacturing system using three-dimensional graphics models |
| CN101907893A (en) * | 2010-07-02 | 2010-12-08 | 北京航空航天大学 | Aircraft component attitude adjusting assembly system based on parallel mechanism with six degrees of freedom and debugging method |
| CN102001451A (en) * | 2010-11-12 | 2011-04-06 | 浙江大学 | Airplane component attitude adjusting and butting system based on four numeric control positioners, attitude adjusting platform and mobile bracket and corresponding method |
| CN102730197A (en) * | 2012-05-16 | 2012-10-17 | 中国商用飞机有限责任公司 | Machine body positioning and posture adjusting device and method |
| CN104148914A (en) * | 2014-08-07 | 2014-11-19 | 天津航天长征火箭制造有限公司 | Posture adjustment assembly system used for butt joint of components of rocket and posture adjustment method |
| CN105479450A (en) * | 2015-12-15 | 2016-04-13 | 南昌航空大学 | Six-degree-of-freedom non-redundant drive automatic fuselage posture adjusting mechanism |
| CN107283159A (en) * | 2017-08-14 | 2017-10-24 | 上海航天设备制造总厂 | Large-scale section numerical control posture adjustment Butt Assembling system |
| CN110001998A (en) * | 2019-03-12 | 2019-07-12 | 南京航空航天大学 | A kind of Large Aircraft Components frame structure docking guide device and method based on laser ranging |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113734459A (en) * | 2021-05-19 | 2021-12-03 | 中航西安飞机工业集团股份有限公司 | Attitude adjusting and positioning method for wall plate on lower surface of airplane body |
| CN113858086A (en) * | 2021-05-19 | 2021-12-31 | 中航西安飞机工业集团股份有限公司 | Positioning tool and positioning method for cylindrical part |
| CN114291288A (en) * | 2022-01-05 | 2022-04-08 | 中国航空制造技术研究院 | Production line system suitable for fuselage assembly |
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Application publication date: 20201124 |