CN112373715A - Device for mounting wing leading edge component of large aircraft - Google Patents
Device for mounting wing leading edge component of large aircraft Download PDFInfo
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- CN112373715A CN112373715A CN202011097172.7A CN202011097172A CN112373715A CN 112373715 A CN112373715 A CN 112373715A CN 202011097172 A CN202011097172 A CN 202011097172A CN 112373715 A CN112373715 A CN 112373715A
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- leading edge
- wing
- assembly
- offset
- upright post
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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 invention discloses a device for mounting a leading edge component of a large airplane wing, which comprises an outer side upright post, an inner side upright post and a cross beam movably mounted between the outer side upright post and the inner side upright post, wherein a leading edge component positioning device for supporting and positioning a leading edge of the wing is mounted on the cross beam; the leading edge component positioning device comprises a leading edge component position adjusting device used for adjusting the position of the leading edge of the wing, a leading edge intersection point single-shaft positioner used for connecting the leading edge component, and a leading edge intersection point adapter plate used for connecting the leading edge intersection point single-shaft positioner and the leading edge component. According to the invention, the front edge assembly is accurately installed by utilizing the front edge assembly mounting tool and equipment, so that the problems of deformation, collision damage and the like of the front edge assembly in the mounting process are avoided as much as possible, the mounting safety of the front edge assembly and the mounting precision of the wing box are improved, and the method has a high application value in the field of aircraft assembly and manufacturing.
Description
Technical Field
The invention belongs to the field of airplane digital assembly, and particularly relates to a device for mounting a wing leading edge assembly of a large airplane.
Background
The aircraft assembly is a process of combining and connecting parts, assemblies or components according to design and technical requirements to form a high-level assembly part or a complete machine, is a key and core link of aircraft manufacture, and determines the final quality, the manufacturing cost and the period of the aircraft to a great extent.
With the rapid development of digital measurement technology, computer control technology, robotics, computer networks and application integration technology, the airplane digital assembly technology has moved to a new height. The airplane digital assembly technology is essentially deeper application of the digital technology in the airplane manufacturing process, is comprehensive application of various advanced technologies, and is an assembly technology which can adapt to quick development and production, low-cost manufacturing requirements and modularized and reconfigurable equipment and tools. The wing digital assembly system is a typical application of airplane digital assembly technology, and the technical level of the wing digital assembly system is bound to develop along with the development of airplane assembly technology. Such as the aircraft wing assembly systems provided in publication nos. CN 107323684 a and CN 109605300 a.
In the field of aerospace manufacturing, an aircraft wing leading edge assembly is one of important components of a wing, and is difficult to hoist and mount and difficult to guarantee the mounting precision due to complex structure, large size, weak rigidity and high positioning difficulty.
In the traditional method, the front edge assembly is directly hoisted into place by a crane, and the front edge assembly is easy to deform due to large size and weak rigidity in the hoisting process. Meanwhile, the problems of low positioning precision, large assembly stress and the like of the front edge assembly are easily caused due to the fact that a travelling crane is difficult to hoist in place. On the other hand, the large-sized leading edge assembly is prone to interference with external tooling equipment.
Disclosure of Invention
Aiming at the existing problems, the invention provides a mounting device of a large-sized airplane leading edge component, which utilizes mounting tooling and equipment of the leading edge component to finish the accurate installation of the leading edge component in the mounting process of the leading edge component, avoids the problems of deformation, collision damage and the like of the leading edge component in the mounting process as much as possible, improves the mounting safety of the leading edge component and the assembly precision of a wing box, and has higher application value in the field of airplane assembly and manufacturing.
The invention adopts the following specific technical scheme:
a device for mounting a leading edge component of a large airplane wing comprises an outer side upright post, an inner side upright post and a cross beam movably mounted between the outer side upright post and the inner side upright post, wherein a leading edge component positioning device for supporting and positioning a leading edge of the wing is mounted on the cross beam;
the leading edge component positioning device comprises a leading edge component position adjusting device used for adjusting the position of the leading edge of the wing, a leading edge intersection point single-shaft positioner used for connecting the leading edge component, and a leading edge intersection point adapter plate used for connecting the leading edge intersection point single-shaft positioner and the leading edge component.
Several alternatives are provided below, but not as an additional limitation to the above general solution, but merely as a further addition or preference, each alternative being combinable individually for the above general solution or among several alternatives without technical or logical contradictions.
Optionally, the outer column is composed of a tower column, an outer offset sliding table and a span-wise sliding table, the outer offset sliding table is slidably mounted on the tower column, and the span-wise sliding table is slidably mounted on the outer offset sliding table.
Optionally, the inner side vertical column is composed of a tower column and an inner offset sliding table, and the inner offset sliding table is slidably mounted on the tower column.
Optionally, the cross beam is supported on the outer side column and the inner side column through the extension sliding table, the outer offset sliding table and the inner offset sliding table, and the cross beam is driven to perform offset motion through synchronous motion of the outer offset sliding table and the inner offset sliding table.
Optionally, the direction of the guide rail sliding block between the outer offset sliding table and the span-wise sliding table is consistent with the length direction of the cross beam, and the end portion of the cross beam slides along the guide rail sliding block along with the span-wise sliding table.
Optionally, the beam is provided with a front edge lifting tool, and the front edge lifting tool is connected with the front edge upper frame posture adjusting auxiliary tool through a guide rail sliding block.
Optionally, the front edge upper frame posture adjusting auxiliary tool is connected with a posture adjusting numerical control positioner, and a ball socket on the posture adjusting numerical control positioner is connected with a support ball head of the front edge upper frame posture adjusting auxiliary tool.
Optionally, the front edge position adjusting device is composed of a plurality of sets of lifting mechanisms and a plurality of sets of transverse supporting plates; the lifting mechanism comprises an A-type front edge numerical control positioner containing a transverse dragging mechanism and a B-type front edge numerical control positioner not containing the transverse dragging mechanism, all sets of transverse supporting plates are connected through aluminum connecting rods, and two long guide rails are arranged at the lower part of each supporting plate.
Optionally, the leading edge intersection single axis positioner is in sliding fit along the long guide rail.
Optionally, the front edge intersection adapter plate is mutually matched and positioned with the three convex cups on the front edge intersection single-shaft positioner through the three conical concave cups, and is locked by the locking pins; the front edge intersection point adapter plate is connected with each intersection point of the front edge assembly in a mode of two positioning pins and a gasket.
The invention has the advantages that:
(1) the offset sliding tables on the inner side upright post and the outer side upright post move synchronously to drive the cross beam to perform offset movement;
(2) the front edge component positioning device is arranged on the cross beam, so that the space is saved;
(3) two long guide rails are arranged at the lower part of a transverse supporting plate of the leading edge position adjusting device, and a slat intersection point and engine hanging intersection point positioner (18 pairs in total) is connected to the guide rails through a sliding block so as to facilitate the positioning operation of a leading edge assembly;
(4) the front edge intersection point adapter plate is provided with three conical concave cups which are mutually matched and positioned with three convex cups on the front edge intersection point single-shaft locator sliding plate and locked by a locking pin, and the position of a positioning hole of the front edge intersection point adapter plate is coordinated with the position of a corresponding intersection point of the front edge, so that the positioning accuracy and reliability are ensured;
(5) arranging a plurality of measuring points on the front edge adapter plate for evaluating the measuring attitude of the front edge assembly;
(6) the front edge intersection point adapter plate is connected with each intersection point of the front edge assembly in a mode of two positioning pins and a gasket, the pose of the front edge intersection point adapter plate can indirectly represent the pose of the front edge assembly, and the problem that the direct measurement of the front edge assembly has no reference is solved;
(7) and a six-degree-of-freedom fine adjustment mechanism is arranged on each front edge intersection point single-shaft positioner, so that the requirement on convenience of regular inspection and adjustment of tooling equipment can be met.
Drawings
FIG. 1 is an elevation view of an apparatus for mounting a leading edge assembly to a large aircraft wing;
FIG. 2 is an isometric view of a hangar tooling for a device for racking a leading edge assembly of a large aircraft wing;
FIG. 3 is an isometric view of an attitude adjustment numerically controlled positioner for a device for racking a leading edge assembly of a large aircraft wing;
FIG. 4 is an outboard stud isometric view of a device for racking a leading edge assembly of a large aircraft wing;
FIG. 5 is an inboard isometric view of the apparatus for mounting the leading edge assembly of a large aircraft wing;
FIG. 6 is an isometric view of a lift mechanism of a device for racking a leading edge assembly of a large aircraft wing, wherein (A) is a side view thereof and (B) is another side view thereof.
In the figure: the front edge lifting device comprises an outer upright post 1, an inner upright post 2, a cross beam 3, a front edge upper frame posture adjusting auxiliary tool 4, a front edge lifting appliance 5, a front edge component positioning system 6, a posture adjusting numerical control positioner 7, a tower post 8, an outer offset sliding table 9, a spreading sliding table 10, a guide rail sliding block 11, a tower post 12, an inner offset sliding table 13, a front edge position adjusting device 14, a front edge intersection point single-shaft positioner 15, a front edge intersection point adapter plate 16, a lifting mechanism 17, a transverse supporting plate 18, an A-type front edge numerical control positioner 19, a B-type front edge numerical control positioner 20 and a long guide rail 21.
Detailed Description
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, however, the present invention may be practiced in other ways than those specifically described herein, and thus the present invention is not limited to the specific embodiments disclosed below. The terms "upper", "lower", "left" and "right" as used herein are set forth with reference to the accompanying drawings, and it is understood that the presence of the terms does not limit the scope of the present invention.
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.
In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
As shown in fig. 1, 2 and 3, the leading edge positioning tool and device are mainly used for positioning and adjusting the position of the leading edge assembly of the left and right outer wing boxes of the wing.
A device for putting on a frame of a wing leading edge component of a large airplane comprises an outer side upright post 1, an inner side upright post 2 and a cross beam 3 movably erected between the outer side upright post 1 and the inner side upright post 2, wherein a leading edge component positioning device 6 for supporting and positioning a wing leading edge is arranged on the cross beam 3. The leading edge component positioning device 6 comprises a leading edge component position adjusting device 14 for adjusting the position of the leading edge of the wing, a leading edge intersection point single-shaft positioner 15 for connecting the leading edge component, and a leading edge intersection point adapter plate 16 for connecting the leading edge intersection point single-shaft positioner 15 and the leading edge component.
In this embodiment, the outboard leg 1, the inboard leg 2, and the cross member 3 comprise a positioning system for supporting and securing the leading edge assembly. The beam 3 is used for installing an installation base of the leading edge component positioning and adjusting device and driving the leading edge component to do offset movement. The outer and inner uprights 1, 2 serve to support the cross-beam 3 and provide a guide base for the cross-beam 3 in an offset movement.
As shown in fig. 4, the outer column 1 is composed of a column tower 8, an outer offset slipway 9 and a span slipway 10. The column tower 8 is a main bearing part of the supporting beam 3 and is of a steel welding structure. The ends of which are fitted with external offset ramps 9. The spanwise slipway 10 is positioned at the upper part of the outer offset slipway 9 and is connected with the outer offset slipway 9 through a guide rail slide block 11, and the direction of the guide rail is consistent with the length direction of the cross beam 3 and is used for releasing the stress of the cross beam 3 caused by thermal deformation. The upper end of the spanwise slipway 10 is the outer end mounting surface of the crossbeam 3.
As shown in fig. 5, the inner column 2 is composed of a column tower 12 and an inner offset slipway 13. The column tower 12 is a main bearing part of the supporting beam 3 and is of a steel welding structure, an inner offset sliding table 13 is installed at the end part of the column tower, and the inner offset sliding table 13 is driven by a full closed-loop control system consisting of a servo motor, a lead screw, a guide rail and a grating ruler and moves synchronously with an outer offset sliding table 9 on the outer side upright post 1 to drive the beam 3 to do accurate offset movement.
The leading edge assembly positioning system 6 is installed on the cross beam 3 and used for realizing position adjustment, positioning and supporting suspension of the leading edge assembly, and mainly comprises a digital control leading edge assembly position adjusting device 14, a leading edge intersection point single-shaft positioner 15 and a leading edge intersection point adapter plate 16. As shown in fig. 6 (a) and (B), the entire leading edge assembly position adjustment device 14 is composed of 6 sets of lifting mechanisms 17 and 6 sets of transverse support plates 18, wherein 3 sets of a-type leading edge numerical control locators 19 contain a transverse dragging mechanism therein, and 3 sets of B-type leading edge numerical control locators 20 contain no transverse dragging mechanism therein. The 6 sets of lifting mechanisms 17 can adjust the position of the leading edge component in the height direction, and the 3 sets of transverse dragging mechanisms can adjust the position of the leading edge component in the wingspan direction by synchronous movement. The transverse supporting plate 18 is an installation basis of the intersection point positioner of the front edge assembly, and in order to inhibit adverse effects of temperature changes on the coordination of the intersection point positioner and the front edge assembly, the transverse supporting plate 18 is made of aluminum alloy materials and is connected with the lifting mechanism 17 through a guide rail slider. Two long guide rails 21 are arranged at the lower part of each supporting plate 18, and the slat intersection point and engine hanging intersection point locators 18 are connected to the guide rails through sliding blocks so as to facilitate the locating operation of the leading edge assembly.
The front edge lifting appliance 5 is installed on the cross beam 3 and is connected with the front edge upper frame posture adjusting auxiliary tool 4 through a guide rail sliding block 11. The movement of the front edge upper frame posture adjusting auxiliary tool 4 is controlled by a wallboard positioner 7, and 8 wallboard positioners 7 are connected with a support ball head of the front edge upper frame posture adjusting auxiliary tool 4 through ball sockets on a numerical control positioner by using 4 positioners of an upper wallboard and a lower wallboard respectively.
The steps of implementing the device for putting the large aircraft wing leading edge on the shelf by adopting the invention are as follows:
(1) moving the cross beam 3 to the offset position to make a safe space for the upper frame of the front edge assembly;
(2) moving 8 wallboard positioners 7 to the working configuration position of the front edge connecting component upper frame to connect the front edge upper frame posture adjusting auxiliary tool 4;
(3) the front edge assembly is placed on the front edge upper frame posture adjusting auxiliary tool 4 for positioning and fixing, the front edge assembly is connected with a front edge intersection point adapter plate 16 through two positioning pins and a gasket, and the front edge upper frame posture adjusting auxiliary tool 4 is hung on 8 wall plate numerical control positioners 7 through a front edge lifting appliance 5;
(4) the pose of the leading edge assembly is adjusted by a leading edge assembly pose adjusting system consisting of 8 wall plate positioners 7;
(5) moving the beam 3 to a working position, extending a front edge intersection point single-shaft positioner 15 in a digital control front edge position adjusting device 14 downwards, mutually matching and positioning three convex cups on a sliding plate of the front edge intersection point single-shaft positioner and three conical concave cups arranged on a front edge intersection point adapter plate 16, and locking by using a locking pin to realize connection with a front edge assembly;
(6) completely separating the front edge component from the front edge upper frame posture adjusting auxiliary tool 4, and driving the front edge upper frame posture adjusting auxiliary tool 4 to move to a hanging position by a control 8 posture adjusting numerical control positioner 7;
(7) hoisting the front edge upper frame posture adjusting auxiliary tool 4 to an external placing position by using a travelling crane;
(8) completing racking of the leading edge assembly.
The above description is only exemplary of the preferred embodiments of the present invention, and is not intended to limit the present invention, and any modifications, equivalents, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A device for putting on a frame of a wing leading edge component of a large airplane is characterized by comprising an outer side upright post (1) and an inner side upright post (2), a cross beam (3) movably erected between the outer side upright post (1) and the inner side upright post (2), and a leading edge component positioning device (6) for supporting and positioning a wing leading edge is installed on the cross beam (3);
the leading edge component positioning device (6) comprises a leading edge component position adjusting device (14) used for adjusting the position of the leading edge of the wing, a leading edge intersection point single-axis positioner (15) used for connecting the leading edge component, and a leading edge intersection point adapter plate (16) used for connecting the leading edge intersection point single-axis positioner (15) and the leading edge component.
2. The device for the upper frame of the wing leading edge assembly of the large airplane according to claim 1, wherein the outer upright post (1) consists of a tower column (8), an outer offset slipway (9) and a spanwise slipway (10), the outer offset slipway (9) is slidably arranged on the tower column (8), and the spanwise slipway (10) is slidably arranged on the outer offset slipway (9).
3. A device for landing a leading edge assembly on a wing of a large aircraft according to claim 2, characterised in that the inboard strut (2) is formed by a tower (12) and an internally offset ramp (13), the internally offset ramp (13) being slidably mounted on the tower (12).
4. The device for mounting the leading edge assembly of the wing of the large airplane according to claim 3, wherein the cross beam (3) is supported on the outer side upright post (1) and the inner side upright post (2) through the span-wise slipway (10), the outer offset slipway (9) and the inner offset slipway (13), and the synchronous movement of the outer offset slipway (9) and the inner offset slipway (13) drives the cross beam (3) to perform offset movement.
5. The device for the upper frame of the wing leading edge assembly of the large aircraft according to claim 4, wherein the direction of the guide rail sliding block (11) between the outer offset sliding table (9) and the spanwise sliding table (10) is consistent with the length direction of the cross beam (3), and the end part of the cross beam (3) slides along the guide rail sliding block (11) along with the spanwise sliding table (10).
6. The device for mounting the leading edge component of the large aircraft wing according to claim 1, wherein a leading edge hanger is mounted on the cross beam (3) and is connected with the leading edge mounting posture adjusting auxiliary tool (4) through a guide rail sliding block (11).
7. The device for putting on a large aircraft wing leading edge assembly according to claim 1, further comprising an attitude adjusting numerical control positioner (7) connected with the leading edge putting on frame attitude adjusting auxiliary tool (4), wherein a ball socket on the attitude adjusting numerical control positioner (7) is connected with a support ball head of the leading edge putting on frame attitude adjusting auxiliary tool (4).
8. The device for landing a leading edge assembly of a large aircraft wing according to claim 1, characterised in that the leading edge position adjustment device (14) consists of a plurality of sets of lifting mechanisms (17) and a plurality of sets of transverse pallets (18); the lifting mechanism (17) comprises an A-type front edge numerical control positioner (19) with a transverse dragging mechanism and a B-type front edge numerical control positioner (20) without the transverse dragging mechanism, all sets of transverse supporting plates (18) are connected through aluminum connecting rods, and two long guide rails (21) are arranged at the lower part of each supporting plate.
9. An apparatus for racking a leading edge assembly for a large aircraft wing according to claim 8 wherein said leading edge intersection single axis locator (15) is slip fit along a long rail (21).
10. The device for mounting a leading edge assembly of a large aircraft wing according to claim 1, characterized in that the leading edge intersection adapter plate (16) is positioned by three conical concave cups in cooperation with three convex cups on the leading edge intersection single-shaft positioner (15) and locked by a locking pin; the front edge intersection point adapter plate (16) is connected with each intersection point of the front edge assembly in the form of two positioning pins and a gasket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011097172.7A CN112373715A (en) | 2020-10-14 | 2020-10-14 | Device for mounting wing leading edge component of large aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011097172.7A CN112373715A (en) | 2020-10-14 | 2020-10-14 | Device for mounting wing leading edge component of large aircraft |
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| CN112373715A true CN112373715A (en) | 2021-02-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011097172.7A Pending CN112373715A (en) | 2020-10-14 | 2020-10-14 | Device for mounting wing leading edge component of large aircraft |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113071702A (en) * | 2021-03-30 | 2021-07-06 | 杭州艾美依航空制造装备有限公司 | Airplane central wing positioning and clamping device and method |
| CN113772116A (en) * | 2021-09-18 | 2021-12-10 | 中航西安飞机工业集团股份有限公司 | Modular reconfigurable aircraft movable wing surface assembly tool and assembly method |
| CN113978751A (en) * | 2021-11-12 | 2022-01-28 | 中航西安飞机工业集团股份有限公司 | Modular reconfigurable tool frame structure and reconfiguration method |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113071702A (en) * | 2021-03-30 | 2021-07-06 | 杭州艾美依航空制造装备有限公司 | Airplane central wing positioning and clamping device and method |
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