CN112606990A - Aircraft wallboard butt-joint structural - Google Patents
Aircraft wallboard butt-joint structural Download PDFInfo
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- CN112606990A CN112606990A CN202011598153.2A CN202011598153A CN112606990A CN 112606990 A CN112606990 A CN 112606990A CN 202011598153 A CN202011598153 A CN 202011598153A CN 112606990 A CN112606990 A CN 112606990A
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- 210000001503 joint Anatomy 0.000 claims abstract description 261
- 238000009434 installation Methods 0.000 claims abstract description 35
- 238000003032 molecular docking Methods 0.000 claims description 23
- 230000000670 limiting effect Effects 0.000 claims description 10
- 239000002184 metal Substances 0.000 claims description 3
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 230000005540 biological transmission Effects 0.000 abstract description 9
- 238000011900 installation process Methods 0.000 abstract description 4
- 238000012423 maintenance Methods 0.000 abstract description 4
- 230000000694 effects Effects 0.000 abstract description 3
- 238000003780 insertion Methods 0.000 abstract description 2
- 230000037431 insertion Effects 0.000 abstract description 2
- 238000006073 displacement reaction Methods 0.000 description 10
- 238000000034 method Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 6
- 238000003754 machining Methods 0.000 description 6
- 238000004519 manufacturing process Methods 0.000 description 6
- 238000005452 bending Methods 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 238000012999 compression bending Methods 0.000 description 2
- 230000002401 inhibitory effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
- B64C1/069—Joining arrangements therefor
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Abstract
The invention discloses an aircraft wallboard butt joint structure, which comprises: the butt joint of the wall plates of the main box section is realized by adopting a structure form of a distributed double-layer toothed butt joint belt plate; particularly comprises at least one pair of distributed double-layer tooth-shaped butt-joint belt plates; each butt joint band plate comprises an upper and a lower double-layer tooth-shaped butt joint lug set which are arranged in an internal and external staggered mode, and each group of lugs are in butt joint in a single lap joint mode, so that the joint surfaces of the lug sets are attached to be coaxial with the butt joint holes; the butt joint installation and the disassembly of the airplane wallboard adopt a direct insertion/direct pulling mode, and the tooth-shaped lug has certain taper, so that the installation guide effect can be realized; the wallboard butt joint mode can ensure the advantages of smooth pneumatic surface, good force transmission route, convenient disassembly and installation process and the like. The embodiment of the invention solves various problems of the existing large-scale wing surface box section wall plate butt joint structure, and realizes effective maintenance of the force transmission path and the force transmission characteristic of the wall plate.
Description
Technical Field
The invention relates to the technical field of aircraft structure design, in particular to an aircraft wall plate butt joint structure.
Background
At present, the conventional butt joint schemes of the wall plates are as follows: single lap butt plate, double lap butt plate, single and double lug butt, etc. Wherein, the single lap butt strap is usually butt jointed at the butt joint of the wall panels by arranging internal butt strap plates or rib rims and the like, and the wing panel is connected with the central section or the fuselage by using a plurality of rows of fasteners; double lap butt strap panels are typically butt jointed at the panel butt joint by providing external straps and internal butt straps/or ribbing, etc., and connecting the airfoil panel to the center section or fuselage using rows of fasteners; the single-lug and double-lug butt joint type common wall plate realizes butt joint by matching a plurality of groups of single lugs with a plurality of groups of double-lug joints.
The single-lap butt-joint band plate type connecting piece has the defects that the connecting piece is large in quantity, basically has a non-detachable butt-joint structure, and a force transmission line has local eccentric load; the double-lap butt joint belt plate type has the defects that the number of connecting pieces is large, the connecting pieces are basically of a non-detachable butt joint structure, the appearance has a protruding area, and the local pneumatic performance is influenced; the single-double lug butt joint type has the defects that the appearance has a protruding double-lug structure, local rectification is needed, in addition, the load transmission of the single-double lug butt joint type is relatively concentrated, the original force transmission path is changed, the load dispersion is not facilitated, and the single-double lug butt joint type is only used for butt joint of a vertical stabilizing surface wall plate and a machine body and the like.
Disclosure of Invention
The purpose of the invention is as follows: the embodiment of the invention provides an aircraft wall plate butt joint structure, which aims to solve various problems of the existing large-scale wing surface box section wall plate butt joint structure and the existing process separation surface structure, provides a good installation and disassembly mode, and realizes effective maintenance of a force transmission path and force transmission characteristics of the wall plate.
The technical scheme of the invention is as follows: the embodiment of the invention provides an aircraft wallboard butt joint structure, which comprises: the method comprises the following steps: the butt joint device comprises an aircraft wall plate 3 to be butted, a first dispersed double-layer toothed butt joint belt plate 1 which is arranged at the butt joint position of the aircraft wall plate 3 in a matching way, a fixed butt joint component 4 and a second dispersed double-layer toothed butt joint belt plate 2 which is arranged at the butt joint position of the fixed butt joint component 4 in a matching way;
the first dispersed double-layer toothed butt-joint belt plate 1 and the second dispersed double-layer toothed butt-joint belt plate 2 are respectively provided with two groups of double-layer toothed single lug groups which are arranged in an internal-external staggered manner, and the first dispersed double-layer toothed butt-joint belt plate and the second dispersed double-layer toothed butt-joint belt plate are used for butt-jointing the aircraft wall plate 3 on the fixed butt-joint part 4 through staggered butt-joint and fit of the inner surface and the outer surface of the two groups of double-layer toothed single lug groups which are arranged in an internal-external staggered manner and are arranged on the aircraft wall plate 3 and two groups of.
Alternatively, in the aircraft panel docking structure as described above,
the first dispersed double-layer toothed butt-joint belt plate 1 and the second dispersed double-layer toothed butt-joint belt plate 2 both comprise: the machine body connecting plate 5, the outer side tooth-shaped butt-joint lug group 6 and the inner side tooth-shaped butt-joint lug group 7 which is arranged inside and outside the outer side tooth-shaped butt-joint lug group in a staggered manner;
the aircraft wall plate 3 is butted with a second dispersed double-layer toothed butt joint belt plate 2 installed on a fixed butt joint part 4 through a first dispersed double-layer toothed butt joint belt plate 1, so that the inner surface of an outer side toothed butt joint lug group 6 in the first dispersed double-layer toothed butt joint belt plate 1 is jointed with the outer surface of an inner side toothed butt joint lug group 7 in the second dispersed double-layer toothed butt joint belt plate 2, and the outer surface of an inner side toothed butt joint lug group 7 in the first dispersed double-layer toothed butt joint belt plate 1 is jointed with the inner surface of the outer side toothed butt joint lug group 6 in the second dispersed double-layer toothed butt joint belt plate 2.
Alternatively, in the aircraft panel docking structure as described above,
the machine body connecting plate on the first dispersed double-layer toothed butt joint belt plate 1 is used for being directly connected with an aircraft wall plate 3 through a fastener;
the machine body connecting plate on the second dispersed double-layer toothed butt joint belt plate 2 is used for being directly connected with the fixed butt joint part 4 through a fastener;
the fastener connecting mode is a single-row connecting mode or a multi-row connecting mode, and a single-shear connecting mode or a double-shear connecting mode.
Alternatively, in the aircraft panel docking structure as described above,
outside profile of tooth butt joint auricle group 6 and inboard profile of tooth butt joint auricle group 7 all include: a plurality of continuous lugs which are arranged at equal intervals and have regular shapes.
Alternatively, in the aircraft panel docking structure as described above,
the outer surface of the outer side tooth-shaped butt-joint lug group 6 is a theoretical outer surface, and the inner surface is a taper curved surface for butt-joint installation; the inner side tooth-shaped butt joint lug group 7 and the outer side tooth-shaped butt joint lug group are arranged in a staggered mode, the inner surface of the inner side tooth-shaped butt joint lug group is parallel to the theoretical outer surface, and the outer surface of the inner side tooth-shaped butt joint lug group is a taper curved surface and used for butt joint installation.
Alternatively, in the aircraft panel docking structure as described above,
the outer side tooth-shaped butt joint lug group 6 and the inner side tooth-shaped butt joint lug group 7 both have installation guiding and limiting functions in 4 directions.
Optionally, in the aircraft panel docking structure as described above, the aircraft panel docking structure includes: the butt joint structure formed by the multiple groups of the first dispersed double-layer tooth-shaped butt joint belt plates 1 and the second dispersed double-layer tooth-shaped butt joint belt plates 2 is used for carrying out sectional butt joint installation on multiple wall plates of an airplane through the multiple groups of butt joint structures.
Alternatively, in the aircraft panel docking structure as described above,
the first dispersed double-layer toothed butt-joint belt plate 1 and the second dispersed double-layer toothed butt-joint belt plate 2 are both formed by a thick metal plate through a double-faced machine;
in the butt joint structure of the first dispersed double-layer toothed butt joint belt plate 1 and the second dispersed double-layer toothed butt joint belt plate 2, coaxial butt joint holes corresponding in position are formed in the outer-side toothed butt joint lug group 6 in the first dispersed double-layer toothed butt joint belt plate 1 and the inner-side toothed butt joint lug group 7 in the second dispersed double-layer toothed butt joint belt plate 2, coaxial butt joint holes corresponding in position are formed in the inner-side toothed butt joint lug group 7 in the first dispersed double-layer toothed butt joint belt plate 1 and the outer-side toothed butt joint lug group 6 in the second dispersed double-layer toothed butt joint belt plate 2, and the first dispersed double-layer toothed butt joint belt plate 1 and the second dispersed double-layer toothed butt joint belt plate 2 are fastened and fixed through toothed bolts penetrating through the coaxial butt joint holes.
The invention has the beneficial effects that: the embodiment of the invention provides an aircraft wallboard butt joint structure, which has the following advantages:
(1) the butt joint of the airplane wall plates is realized by adopting a butt joint form of double-layer toothed butt joint belt plates distributed in a staggered manner, the multidirectional limiting effect is realized, a good pneumatic surface can be ensured, and a rectifying device and the like are not required to be additionally arranged; the structure of the double-layer tooth-shaped single lug group which is arranged in a staggered mode can effectively limit lateral displacement, chordwise displacement and vertical displacement, the inner fit taper surface can effectively limit lateral displacement and vertical displacement, meanwhile, the outer surface of a butt joint area of the butt joint belt plate adopts a straight-line shape-modifying curved surface, and the pneumatic surface quality of the comprehensive effect is better;
(2) the butt joint of the airplane wall plates is realized by adopting a butt joint form of double-layer tooth-shaped lug plates which are distributed in a staggered mode and butt joint belt plates, the bearing performance of a single-piece wall plate can be effectively exerted, the butt joint bolts adopt a single-shear bearing mode, a certain inhibiting effect is exerted on eccentric bending of butt joint bolt groups, and the eccentric bending bearing directions of adjacent butt joint bolts are opposite, so that the local rigidity of a butt joint is relatively good, bad deformation is not easily generated, and the like;
(3) the double-layer tooth-shaped lug butt-joint belt plate in distributed staggered arrangement has good structural openness, is convenient for high-precision machining, can be used for machining a single-side wing surface and can also be used as a double-side wing surface joint for integral design and manufacture, the single-side wing surface joint can be adopted for machining a large-sized airplane wall plate, and the double-side wing surface joint can be adopted for integral design and manufacture of a small-sized airplane, so that better manufacturing precision can be achieved;
(4) by adopting the butt joint structure, the installation is convenient and accurate, and the disassembly and maintenance are good; the staggered double-layer tooth-shaped lug butt joint is adopted, and the taper surface is arranged on the butt joint binding surface, so that the installation process has good guidance, the limit arrangement has a more accurate installation function, and in addition, the single-row shear-receiving butt joint bolt is adopted, so that the precision reaming, the installation, the disassembly and the like are facilitated; and the butt joint structure is ensured to have certain tension-compression bending shear bearing capacity.
Drawings
The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the example serve to explain the principles of the invention and not to limit the invention.
Fig. 1 is a schematic structural diagram of an aircraft wall panel butt joint structure according to an embodiment of the present invention;
fig. 2 is a schematic structural view of a dispersed double-layer toothed butt-joint belt plate in an aircraft wall plate butt-joint structure according to an embodiment of the present invention;
fig. 3 is a schematic view of a process of butt-joint installation of an aircraft panel by using an aircraft panel butt-joint structure provided by an embodiment of the invention;
fig. 4 is a schematic view of a butt joint structure of first and second discrete double-layer toothed butt joint belt plates in an aircraft wall plate butt joint structure provided by an embodiment of the invention;
fig. 5 is a schematic view illustrating an installation direction of inner and outer tooth-shaped butt-joint lug groups in an aircraft wall plate butt-joint structure according to an embodiment of the present invention;
fig. 6 is a schematic structural diagram of an application of an aircraft wall panel butt joint structure according to an embodiment of the present invention;
fig. 7 is a schematic structural diagram of another application of the aircraft wall panel butt joint structure provided by the embodiment of the invention.
DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.
For the wing surface structure, the most critical part is root butt joint, including butt joint of left and right wing surfaces, butt joint of wing surfaces and a machine body, and the butt joint of other structural types mainly includes butt joint of wall plates, butt joint of beams/walls and the like except for a beam structure. The butt joint of beams is relatively simple, the butt joint of wall plates is relatively complex, and particularly the butt joint of the wall plates with the requirements of interchange or quick disassembly is more difficult.
The above background art has provided various docking structures for existing wall panels, as well as various disadvantages associated with docking structures. The embodiment of the invention provides an aircraft wall plate butt joint structure, aiming at the problems of the existing wall plate butt joint structure.
The following specific embodiments of the present invention may be combined, and the same or similar concepts or processes may not be described in detail in some embodiments.
Fig. 1 is a schematic structural diagram of an aircraft wall panel docking structure according to an embodiment of the present invention. The aircraft wallboard butt joint structure provided by the embodiment of the invention can comprise: the butt joint device comprises an aircraft wall plate 3 to be butted, a first dispersed double-layer toothed butt joint belt plate 1 arranged at the butt joint position of the aircraft wall plate 3 in a matching mode, a fixed butt joint component 4 and a second dispersed double-layer toothed butt joint belt plate 2 arranged at the butt joint position of the fixed butt joint component 4 in a matching mode.
In the aircraft wall plate butt-joint structure shown in fig. 1, two sets of double-layer tooth-shaped single lug groups staggered inside and outside are respectively arranged in a first dispersed double-layer tooth-shaped butt-joint belt plate 1 and a second dispersed double-layer tooth-shaped butt-joint belt plate 2, and the aircraft wall plate 3 is butt-jointed to a fixed butt-joint component 4 through staggered butt-joint and inner and outer surface joint of the two sets of double-layer tooth-shaped single lug groups staggered inside and outside and mounted on the aircraft wall plate 3 and the two sets of double-layer tooth-shaped single lug groups staggered inside and outside and mounted on the fixed butt-joint component 4.
Fig. 2 is a schematic structural diagram of a dispersed double-layer toothed butt-joint belt plate in an aircraft wall plate butt-joint structure according to an embodiment of the present invention. As shown in fig. 2, the first and second dispersed double-layer toothed butt- jointed belt plates 1 and 2 in the embodiment of the present invention have substantially the same structure, and both of them include: the machine body connecting plate 5, the outer side tooth-shaped butt-joint lug group 6 and the inner side tooth-shaped butt-joint lug group 7 which is arranged inside and outside the outer side tooth-shaped butt-joint lug group in a staggered manner; the upper drawing in fig. 2 is a front view of the distributed double-layer toothed butt-jointed belt plate, the middle drawing is a sectional view of the upper drawing along A-A, and the lower drawing is a sectional view of the upper drawing along F-F.
Fig. 3 is a schematic diagram illustrating a process of butt-joint installation of an aircraft panel by using an aircraft panel butt-joint structure according to an embodiment of the present invention. According to the embodiment of the invention, the aircraft wall plate 3 is butted with a second dispersed double-layer toothed butt joint belt plate 2 installed on a fixed butt joint part 4 through a first dispersed double-layer toothed butt joint belt plate 1, so that the inner surface of an outer side toothed butt joint lug group 6 in the first dispersed double-layer toothed butt joint belt plate 1 is jointed with the outer surface of an inner side toothed butt joint lug group 7 in the second dispersed double-layer toothed butt joint belt plate 2, and the outer surface of the inner side toothed butt joint lug group 7 in the first dispersed double-layer toothed butt joint belt plate 1 is jointed with the inner surface of the outer side toothed butt joint lug group 6 in the second dispersed double-layer toothed butt joint belt plate 2.
In fig. 3, the direction of the arrow is the mounting direction, the D region shown by the dotted line is a fixed partial structure, and the E region shown by the dotted line is a partial structure for performing butt mounting during mounting.
Based on the specific structure of the first dispersed double-layer toothed butt-joint belt plate 1 and the second dispersed double-layer toothed butt-joint belt plate 2 installed on the fixed butt-joint component 4, the machine body connecting plate on the first dispersed double-layer toothed butt-joint belt plate 1 is used for being directly connected with the aircraft wall plate 3 through a fastener; the machine body connecting plate on the second dispersed double-layer toothed butt joint belt plate 2 is used for being directly connected with the fixed butt joint component 4 through a fastener.
In practical application, the fastener connection mode is set to be a single-row connection mode or a multi-row connection mode, a single-shear connection mode or a double-shear connection mode and the like.
As shown in fig. 1 to 3, the outer tooth butt tab group and the inner tooth butt tab group in the embodiment of the present invention each include: a plurality of continuous lugs which are arranged at equal intervals and have regular shapes.
Fig. 4 is a schematic view of a butt joint structure of first and second discrete double-layer toothed butt joint belt plates in an aircraft panel butt joint structure according to an embodiment of the present invention. The right drawing in fig. 4 is a front view of the docking structure, the lower drawing is a sectional view of the front view taken along E-E, the left drawing is a sectional view of the front view taken along C-C, and the middle drawing is a sectional view of the front view taken along D-D.
With the structure shown in fig. 2 and 4, in the distributed double-layer toothed butt-joint band plate according to the embodiment of the present invention, the outer surface of the outer toothed butt-joint lug group 6 is a theoretical outer surface, and the inner surface is a tapered surface for butt-joint installation; the inner side tooth-shaped butt joint lug group 7 and the outer side tooth-shaped butt joint lug group are arranged in a staggered mode, the inner surface of the inner side tooth-shaped butt joint lug group is parallel to the theoretical outer surface, and the outer surface of the inner side tooth-shaped butt joint lug group is a taper curved surface and used for butt joint installation.
The aircraft wall plate butt joint structure provided by the embodiment of the invention adopts a structural form of paired distributed double-layer toothed butt joint belt plates to realize butt joint of main box section wall plates; the wallboard butt joint structure is formed by matching at least one pair of distributed double-layer tooth-shaped butt joint belt plates; each butt joint plate is machined by a thick metal plate double-sided machine to form an upper and lower double-layer tooth-shaped butt joint lug group which are arranged in a staggered mode; the main butt joint structure is formed by connecting a plurality of groups of lugs, and each group of lugs are in butt joint in a single lap joint mode, so that the lap joint surfaces of the lug groups are attached to be coaxial with the butt joint holes; the butt joint installation and the disassembly of the aircraft wall plate adopt a direct insertion/direct pulling mode, and the tooth-shaped lug plates have certain taper and can play a role in installation guide. The wallboard butt joint structure can ensure the advantages of smooth pneumatic surface, good force transmission route, convenient disassembly and installation process and the like.
In practical application, the outer side tooth form butt joint lug group 6 and the inner side tooth form butt joint lug group 7 both have installation guiding and limiting functions in 4 directions. Fig. 5 is a schematic view illustrating an installation direction of inner and outer tooth-shaped butt-joint lug groups in an aircraft panel butt-joint structure according to an embodiment of the present invention. Fig. 5 is a partially enlarged view showing a region F shown by a broken line in fig. 3, and "1", "2", "3", and "4" in fig. 5 indicate 4 directions.
In one implementation of the embodiment of the present invention, an aircraft panel docking structure may include: the butt joint structure formed by the multiple groups of the first dispersed double-layer tooth-shaped butt joint belt plates 1 and the second dispersed double-layer tooth-shaped butt joint belt plates 2 is used for carrying out sectional butt joint installation on multiple wall plates of an airplane through the multiple groups of butt joint structures.
For example, as shown in fig. 6, an application structure of an aircraft panel butt-joint structure according to an embodiment of the present invention is schematically shown, and 2 sets of first and second discrete double-layer toothed butt-joint belt plates are used in the butt-joint structure shown in fig. 6.
For example, as shown in fig. 7, which is a schematic view of another application structure of an aircraft panel butt joint structure provided in an embodiment of the present invention, fig. 7 shows an example of butt joint of root portions of wing panels with ribs, a first discrete double-layer toothed butt joint strip plate 1 in fig. 7 has a limiting structure perpendicular to a butt joint lug group, the limiting structure abuts against a wing root rib 9, fig. 7 shows an airfoil profile C, and a theoretical outer profile in the butt joint structure includes, for example, a butt joint straight-line modified surface a and an inner tapered surface B.
The aircraft wallboard butt joint structure provided by the embodiment of the invention has the following advantages:
(1) the butt joint of the airplane wall plates is realized by adopting a butt joint form of double-layer toothed butt joint belt plates distributed in a staggered manner, the multidirectional limiting effect is realized, a good pneumatic surface can be ensured, and a rectifying device and the like are not required to be additionally arranged; the structure of the double-layer tooth-shaped single lug group which is arranged in a staggered mode can effectively limit lateral displacement, chordwise displacement and vertical displacement, the inner fit taper surface can effectively limit lateral displacement and vertical displacement, meanwhile, the outer surface of a butt joint area of the butt joint belt plate adopts a straight-line shape-modifying curved surface, and the pneumatic surface quality of the comprehensive effect is better;
(2) the butt joint of the airplane wall plates is realized by adopting a butt joint form of double-layer tooth-shaped lug plates which are distributed in a staggered mode and butt joint belt plates, the bearing performance of a single-piece wall plate can be effectively exerted, the butt joint bolts adopt a single-shear bearing mode, a certain inhibiting effect is exerted on eccentric bending of butt joint bolt groups, and the eccentric bending bearing directions of adjacent butt joint bolts are opposite, so that the local rigidity of a butt joint is relatively good, bad deformation is not easily generated, and the like;
(3) the double-layer tooth-shaped lug butt-joint belt plate in distributed staggered arrangement has good structural openness, is convenient for high-precision machining, can be used for machining a single-side wing surface and can also be used as a double-side wing surface joint for integral design and manufacture, the single-side wing surface joint can be adopted for machining a large-sized airplane wall plate, and the double-side wing surface joint can be adopted for integral design and manufacture of a small-sized airplane, so that better manufacturing precision can be achieved;
(4) by adopting the butt joint structure, the installation is convenient and accurate, and the disassembly and maintenance are good; the staggered double-layer tooth-shaped lug butt joint is adopted, and the taper surface is arranged on the butt joint binding surface, so that the installation process has good guidance, the limit arrangement has a more accurate installation function, and in addition, the single-row shear-receiving butt joint bolt is adopted, so that the precision reaming, the installation, the disassembly and the like are facilitated; and the butt joint structure is ensured to have certain tension-compression bending shear bearing capacity.
The following describes in detail an embodiment of an aircraft wall panel docking structure provided by an embodiment of the present invention with an implementation example.
Referring to fig. 1 to 5, an aircraft panel docking structure includes: the device comprises a first dispersed double-layer toothed butt joint belt plate 1, a second dispersed double-layer toothed butt joint belt plate 2, an airplane wall plate 3, a fixed butt joint component 4 and the like. The method is characterized in that: the first dispersed double-layer tooth-shaped butt joint belt plate 1 and the second dispersed double-layer tooth-shaped butt joint belt plate 2 realize butt joint of a segmented structure through respective multiple groups of staggered double-layer tooth-shaped single lug groups and fasteners;
the first and second dispersed double-layer toothed butt-joint band plates are composed of a machine body connecting plate 5, an outer side toothed butt-joint lug group 6, an inner side toothed lug group 7 and the like; in a group of butt joint structures, the outer surface of one outer side tooth-shaped butt joint lug 6 can be a straight-line profile, the inner surface (the joint surface with the other butt joint belt plate) is a taper curved surface, and the butt joint structure has 4-direction installation guiding and limiting functions (taking 1 as an example, the butt joint structure comprises four-direction limiting in the front direction, the rear direction, the outer direction and the upper direction, taking 2 as an example, the butt joint structure comprises four-direction limiting in the front direction, the rear direction, the outer direction and the upper direction); the inner surface of the inner side tooth-shaped butt joint lug plate is a straight-line modified surface, the outer surface (a binding surface with the other butt joint belt plate) is a taper curved surface, and the installation guide and limit function in 4 directions is realized (taking 1 as an example, the limit function comprises limit in four directions of front, back, inner and lower, and taking 2 as an example, the limit function comprises limit in four directions of front, back, inner and upper).
During installation, according to the installation direction shown in fig. 3, the respective belt-dispersed double-layer toothed butt-joint belt plate 1 of the upper and lower wing surfaces is connected with the aircraft wall plate structure 3 into a whole through a fastener (such as a moving structure E in fig. 3), and in order to ensure the installation precision, a corresponding tool is required to ensure the installation position of a butt joint; connecting the corresponding second dispersed double-layer toothed butt-joint belt plate 2 and the fixed butt-joint component 4 into a whole through a fastener on a matched tool (such as a fixed structure D in fig. 3); and (3) oppositely closing the moving structure E along the installation direction to enable the moving structure E to be in butt joint with the fixing structure D, so that meshing of the butt joint lug pieces of the pair of distributed double-layer toothed butt joint belt plates is realized, after the belt plate reaches a design position, a necessary process pin shaft is installed, a fastener hole is hinged step by step, and a fastener is installed.
When the movable structure E needs to be disassembled, all the fasteners are disassembled firstly, and then the movable structure E is pulled out in the opposite direction of installation, so that the structural disassembly is realized.
Although the embodiments of the present invention have been described above, the above description is only for the convenience of understanding the present invention, and is not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (8)
1. An aircraft panel docking structure, comprising: the butt joint device comprises an aircraft wallboard (3) to be butted, a first dispersed double-layer toothed butt joint belt plate (1) which is arranged at the butt joint position of the aircraft wallboard (3) in a matching way, a fixed butt joint component (4) and a second dispersed double-layer toothed butt joint belt plate (2) which is arranged at the butt joint position of the fixed butt joint component (4) in a matching way;
the first dispersed double-layer toothed butt joint belt plate (1) and the second dispersed double-layer toothed butt joint belt plate (2) are respectively provided with two groups of double-layer toothed single lug groups which are arranged in an internal-external staggered mode, and the first dispersed double-layer toothed butt joint belt plate and the second dispersed double-layer toothed single lug groups are used for butting the airplane wallboard (3) on the fixed butt joint component (4) through staggered butt joint of the two groups of double-layer toothed single lug groups which are arranged in the internal-external staggered mode and installed on the fixed butt joint component (4) and the fit of.
2. An aircraft panel docking structure according to claim 1,
the first dispersed double-layer toothed butt-joint belt plate (1) and the second dispersed double-layer toothed butt-joint belt plate (2) both comprise: the machine body connecting plate (5), the outer side tooth-shaped butt-joint lug group (6) and the inner side tooth-shaped butt-joint lug group (7) which is arranged inside and outside the outer side tooth-shaped butt-joint lug group in a staggered manner;
the aircraft wall plate (3) is butted with a second dispersed double-layer toothed butt joint belt plate (2) installed on the fixed butt joint component (4) through a first dispersed double-layer toothed butt joint belt plate (1), so that the inner shape surface of an outer side toothed butt joint lug group (6) in the first dispersed double-layer toothed butt joint belt plate (1) is jointed with the outer shape surface of an inner side toothed butt joint lug group (7) in the second dispersed double-layer toothed butt joint belt plate (2), and the outer shape surface of the inner side toothed butt joint lug group (7) in the first dispersed double-layer toothed butt joint belt plate (1) is jointed with the inner shape surface of the outer side toothed butt joint lug group (6) in the second dispersed double-layer toothed butt joint belt plate (2).
3. An aircraft panel docking structure according to claim 2,
the machine body connecting plate on the first dispersed double-layer toothed butt joint belt plate (1) is used for being directly connected with an aircraft wall plate (3) through a fastener;
the machine body connecting plate on the second dispersed double-layer toothed butt joint belt plate (2) is used for being directly connected with the fixed butt joint component (4) through a fastener;
the fastener connecting mode is a single-row connecting mode or a multi-row connecting mode, and a single-shear connecting mode or a double-shear connecting mode.
4. An aircraft panel docking structure according to claim 2,
outside profile of tooth butt joint auricle group (6) and inboard profile of tooth butt joint auricle group (7) all include: a plurality of continuous lugs which are arranged at equal intervals and have regular shapes.
5. An aircraft panel docking structure according to claim 4,
the outer surface of the outer side tooth-shaped butt joint lug group (6) is a theoretical outer surface, and the inner surface is set to be a taper curved surface and used for butt joint installation; the inner side tooth-shaped butt joint lug group (7) and the outer side tooth-shaped butt joint lug group are arranged in a staggered mode, the inner surface of the inner side tooth-shaped butt joint lug group is parallel to the theoretical outer surface, and the outer surface of the inner side tooth-shaped butt joint lug group is a taper curved surface and used for butt joint installation.
6. An aircraft panel docking structure according to claim 4,
the outer side tooth-shaped butt joint lug group (6) and the inner side tooth-shaped butt joint lug group (7) both have installation guiding and limiting functions in 4 directions.
7. An aircraft panel docking structure according to any one of claims 1 to 6, comprising: the butt joint structure formed by the multiple groups of the first dispersed double-layer tooth-shaped butt joint belt plates (1) and the second dispersed double-layer tooth-shaped butt joint belt plates (2) is used for carrying out sectional butt joint installation on multiple wall plates of an airplane through the multiple groups of butt joint structures.
8. An aircraft panel docking structure according to any one of claims 2 to 6,
the first dispersed double-layer toothed butt-joint belt plate (1) and the second dispersed double-layer toothed butt-joint belt plate (2) are both formed by a thick metal plate through addition by a double-faced machine;
in the butt joint structure of the first dispersed double-layer toothed butt joint belt plate (1) and the second dispersed double-layer toothed butt joint belt plate (2), coaxial butt joint holes corresponding in position are formed in an outer-side toothed butt joint lug group (6) in the first dispersed double-layer toothed butt joint belt plate (1) and an inner-side toothed butt joint lug group (7) in the second dispersed double-layer toothed butt joint belt plate (2), coaxial butt joint holes corresponding in position are formed in the inner-side toothed butt joint lug group (7) in the first dispersed double-layer toothed butt joint belt plate (1) and the outer-side toothed butt joint lug group (6) in the second dispersed double-layer toothed butt joint belt plate (2), and the first dispersed double-layer toothed butt joint belt plate (1) and the second dispersed double-layer toothed butt joint belt plate (2) are fastened and fixed through bolts penetrating through the coaxial butt joint holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011598153.2A CN112606990A (en) | 2020-12-29 | 2020-12-29 | Aircraft wallboard butt-joint structural |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011598153.2A CN112606990A (en) | 2020-12-29 | 2020-12-29 | Aircraft wallboard butt-joint structural |
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| Publication Number | Publication Date |
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| CN112606990A true CN112606990A (en) | 2021-04-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202011598153.2A Pending CN112606990A (en) | 2020-12-29 | 2020-12-29 | Aircraft wallboard butt-joint structural |
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| CN (1) | CN112606990A (en) |
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| EP4431381A1 (en) * | 2023-03-16 | 2024-09-18 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | A structurally bonded arrangement |
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Application publication date: 20210406 |