阅读说明：本技术 一种飞机安定面盒段对接装置 (Aircraft stable face box section interfacing apparatus ) 是由 高伟 于 2020-12-29 设计创作，主要内容包括：本发明公开一种飞机安定面盒段对接装置,包括：安定面盒段组件、对接接头组件；安定面盒段组件包括壁板,分别设置于壁板前后两侧的前梁和后梁,以及设置于前梁与后梁之间的对接翼肋；对接接头组件包括：设置于前梁与对接翼肋连接位置的I组对接接头组件,以及设置于后梁与对接翼肋连接位置的II组对接接头组件；I组对接接头组件中每个对接接头的连接耳片方向与II组对接接头组件中每个对接接头的连接耳片方向垂直,用于传递航向载荷以及垂直航向的纵向载荷。本发明实施例解决了现有飞机盒段结构,由于结构刚度布置因素,为了使得所有对接接头组有效传递载荷,需要额外增加结构重量的问题。(The invention discloses an aircraft stable surface box section butt joint device, which comprises: a stabilizing surface box section component and a butt joint component; the stabilizing surface box section assembly comprises a wall plate, a front beam and a rear beam which are respectively arranged on the front side and the rear side of the wall plate, and a butt joint rib arranged between the front beam and the rear beam; the butt joint assembly includes: the I-group butt joint component is arranged at the connecting position of the front beam and the butt-joint wing rib, and the II-group butt joint component is arranged at the connecting position of the rear beam and the butt-joint wing rib; the direction of the connecting lug of each butt joint in the I-group butt joint assembly is perpendicular to the direction of the connecting lug of each butt joint in the II-group butt joint assembly, and the I-group butt joint assembly is used for transmitting course load and vertical load. The embodiment of the invention solves the problem that the structural weight needs to be additionally increased for effectively transferring the load of all butt joint groups due to structural rigidity arrangement factors of the conventional airplane box section structure.)

1. An aircraft stable surface box section docking assembly, comprising: a stabilizing surface box section component and a butt joint component;

the stabilizing surface box section assembly comprises a wall plate (1), a front beam and a rear beam (5) which are respectively arranged on the front side and the rear side of the wall plate (1), and a butt joint rib (6) arranged between the front beam and the rear beam (5);

the butt joint assembly includes: the I-shaped butt joint component (7) is arranged at the connecting position of the front beam and the butt joint wing rib (6), and the II-shaped butt joint component (8) is arranged at the connecting position of the rear beam (5) and the butt joint wing rib (6);

the connecting lug direction of each butt joint (9) in the I group of butt joint assemblies (7) is perpendicular to the connecting lug direction of each butt joint (9) in the II group of butt joint assemblies (8) and is used for transmitting course load and vertical load in the vertical direction.

2. An aircraft ballast face box docking arrangement according to claim 1 wherein in the ballast face box assembly the wall panels (1) are provided as a composite stiffened structure with a longitudinal direction through-going structure.

3. An aircraft ballast section docking device according to claim 2 wherein the cross-section of the front beam in the ballast section assembly is a channel or "C" shaped cross-section, the front beam comprising a central front beam (3), a left front beam (2) on one side of the central front beam (3), and a right front beam (4) on the other side of the central front beam (3);

left front beam (2) and right front beam (4) set up to symmetrical structure, and set up to composite material lamination structure, and well front beam (3) set up to the metal material structure, and well front beam (3) connect into whole through overlap joint structure with left front beam (2) and right front beam (4), and the both ends of well front beam (3) are nested in left front beam (2) and right front beam (4) rather than relative terminal surface.

4. An aircraft stabilizer box section docking device according to claim 3, characterized in that in the stabilizer box section assembly, the back beam (5) is provided as a composite laminated structure with a longitudinal direction as a through-going structure.

5. The aircraft stabilizer box docking device of claim 4, comprising in particular: the structure comprises two butt joint wing ribs (6) which are arranged into a metal material structure, wherein each butt joint wing rib (6) is respectively connected with a wall plate (1), a middle front beam (3) and a rear beam (5) into a whole through machinery;

the butt joint rib (6) is nested in the groove of the back beam (5) at the connecting position of the butt joint rib (6) and the back beam (5), so that the butt joint rib (6) and the butt joint rib (6) are respectively and mechanically connected with the web and the edge of the back beam (5); and the connecting position of the butt-joint wing rib (6) and the middle front beam (3) is mechanically connected through the lap joint of the front beam rib and the web of the butt-joint wing rib (6).

6. An aircraft stabilizer box docking device according to any one of claims 1-5, characterized in that the I-group joint assembly (7) is installed at the intersection of the front center sill (3) and the butt rib (6), and the II-group joint assembly (8) is installed at the intersection of the rear center sill (5) and the butt rib (6).

7. An aircraft stabilizer section docking device according to claim 6, characterized in that each docking head (9) of each set of docking head assemblies comprises two L-shaped docking structures arranged side by side, the connecting lug is located on the short side of the docking structure, and the two L-shaped docking structures are mechanically connected to form a whole structure.

8. An aircraft stabilizer box docking device according to any one of claims 7, further comprising: a connection assembly of the cassette section to the butt joint, the connection assembly being provided as a strap (10);

in the butt joint, the long side of the L-shaped butt joint structure is connected with a beam web plate and a butt joint wing rib (6) into a whole and is used for collecting shear force of the beam web plate and shear load of torque conversion of the butt joint wing rib;

the short side of the L-shaped butt joint structure is connected to the wall plate 1 through a belt plate (10), the belt plate (10) is used for collecting tensile load and compressive load converted from bending moment on the wall plate (1), and finally the other side of the butt joint is connected with the butt joint belt plate and the wall plate into a whole.

Technical Field

The invention relates to the technical field of aircraft structure design, in particular to an aircraft stable surface box section butt joint device.

Background

Currently, the in-service aircraft stabilizer box mainly bears the leading edge load, the trailing edge load, the control surface load and the self load, and finally transfers the collected load to the fuselage or other stabilizer structures.

The box section of a certain civil aircraft is of a double-beam single-block structure, three groups of butt joint groups are arranged and are respectively arranged at the intersection of a front beam and a butt joint wing rib, the intersection of a rear beam and the butt joint wing rib and between the front beam and the rear beam, and the box section load is collected and transmitted through 6 joints.

The above-mentioned aircraft box section structure, because of the structural arrangement rigidity problem, needs the additional structural weight in order to make all butt joint groups effectively transmit load.

Disclosure of Invention

The purpose of the invention is as follows: the embodiment of the invention provides an airplane stable surface box section butt joint device, which aims to solve the problem that the structural weight needs to be additionally increased for effectively transferring load by all butt joint groups due to structural rigidity arrangement factors of an existing airplane box section structure.

The technical scheme of the invention is as follows: the embodiment of the invention provides an aircraft stable surface box section butt joint device, which comprises: a stabilizing surface box section component and a butt joint component;

the stabilizing surface box section assembly comprises a wall plate 1, a front beam and a rear beam 5 which are respectively arranged on the front side and the rear side of the wall plate 1, and a butt joint rib 6 arranged between the front beam and the rear beam 5;

the butt joint assembly includes: the I-group butt joint assembly 7 is arranged at the connecting position of the front beam and the butt joint rib 6, and the II-group butt joint assembly 8 is arranged at the connecting position of the rear beam 5 and the butt joint rib 6;

the connecting lug direction of each butt joint 9 in the I-group butt joint assembly 7 is perpendicular to the connecting lug direction of each butt joint 9 in the II-group butt joint assembly 8, and the I-group butt joint assembly is used for transmitting a heading load and a vertical heading load.

Alternatively, in the aircraft ballast face box section alignment apparatus described above, in the ballast face box section assembly, the wall plate 1 is provided as a composite material stiffened structure, with a through structure in the longitudinal direction.

Optionally, in the aircraft ballast plane box section docking device as described above, in the ballast plane box section assembly, the cross section of the front beam is a channel section or a "C" section, and the front beam includes a center front beam 3, a left front beam 2 on one side of the center front beam 3, and a right front beam 4 on the other side of the center front beam 3;

left front beam 2 and right front beam 4 set up to symmetrical structure, and set up to composite material laminated structure, and well front beam 3 sets up to the metal material structure, and well front beam 3 connects into whole through overlap joint structure with left front beam 2 and right front beam 4, and the both ends of well front beam 3 are nested in left front beam 2 and right front beam 4 rather than relative terminal surface.

Optionally, in the aircraft ballast plane box section docking device as described above, in the ballast plane box section assembly, the back beam 5 is provided as a composite laminated structure, and the longitudinal direction is a penetrating structure.

Optionally, in the above-described aircraft stabilizer box section docking device, the method specifically includes: the structure comprises two butt joint wing ribs 6 which are arranged into a metal material structure, wherein each butt joint wing rib 6 is respectively connected with a wall plate 1, a middle front beam 3 and a rear beam 5 into a whole through machinery;

in the connection position of the butt-joint rib 6 and the back beam 5, the butt-joint rib 6 is nested in the groove of the back beam 5, so that the butt-joint rib 6 and the butt-joint rib 6 are respectively mechanically connected with the web plate and the edge strip of the back beam 5; the connecting position of the butt-joint wing rib 6 and the middle front beam 3 is mechanically connected through the lap joint of the front beam rib and the web of the butt-joint wing rib 6.

Optionally, in the aircraft stabilizer box docking device as described above, the I-group docking assembly 7 is installed at a meeting position of the middle front beam 3 and the docking rib 6, and the II-group docking assembly 8 is installed at a meeting position of the rear beam 5 and the docking rib 6.

Optionally, in the aircraft stabilizer section butt joint device as described above, each butt joint 9 in each set of butt joint assemblies includes two L-shaped butt joint structures arranged side by side, the connecting tab is located on one side of a short side of the butt joint structure, and the two L-shaped butt joint structures are mechanically connected to form an integral structure.

Optionally, in the aircraft stabilizer box docking device as described above, further comprising: a connection assembly of cassette sections to a butt joint, the connection assembly being provided as a strap 10;

in the butt joint, the long side of an L-shaped butt joint structure is connected with a beam web plate and a butt joint wing rib 6 into a whole for collecting shear force of the beam web plate and shear load of torque conversion of the butt joint wing rib;

the short side of the L-shaped butt joint structure is connected to the wallboard 1 through a band plate 10, the band plate 10 is used for collecting tensile load and compressive load converted from bending moment on the wallboard 1, and finally the other side of the butt joint is connected with the butt joint band plate and the wallboard into a whole. .

The invention has the beneficial effects that: the embodiment of the invention provides an airplane stable surface box section butt joint device, aiming at the problem that the structural weight needs to be additionally increased for a joint group to effectively transfer load due to the structural arrangement rigidity problem in the existing airplane box section structure, the arrangement and the structural form of butt joint components are changed, specifically, the butt joint components are arranged into two groups and respectively arranged at the intersection positions of a front beam, a rear beam and butt joint wing ribs, so that the box section shear force, bending moment and torque load can be effectively transferred, and meanwhile, the box section side load transfer can be effectively transferred; in addition, the structure of the stable noodle box section butt joint device can effectively reduce the weight of the structure.

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 ballast surface box docking device according to an embodiment of the present invention;

figure 2 is a schematic structural view of the ballast section assembly of the aircraft ballast section docking assembly of figure 1;

FIG. 3 is a partial schematic structural view of a front beam of the ballast surface box assembly provided in the embodiment of FIG. 2;

FIG. 4 is a partial schematic structural view of a back beam of the ballast surface box assembly provided in the embodiment of FIG. 2;

FIG. 5 is a schematic structural diagram of a docking head of the apparatus for docking a stable surface box section of an aircraft according to an embodiment of the present invention;

fig. 6 is a schematic structural diagram of a connection position of a butt joint and a box section in an aircraft ballast surface box section butt-joint device according to an 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.

Fig. 1 is a schematic diagram of a conventional civil aircraft with a double-beam monolithic structure. In fig. 1, 1 is a front beam, 2 is a rear beam, 3 is a normal rib, 4 is a wall plate, and 5 is a butt joint rib, and the aircraft box is provided with three butt joint groups, I6, II 7 and III 8.

The above-mentioned stable surface box section mainly bears shearing force, torque and bending moment load. The shear load is transmitted through the front beam 1 and the rear beam 2 and finally transmitted to other structural members through the I butt joint group 6 and the III butt joint group 8; the torque load is transmitted by a closed chamber formed by the wall plate, the front beam and the rear beam, and is finally transmitted to other structural parts by collecting and diffusing the butt joint joints (comprising I, II and III) through the butt rib 5; bending moment loads are transmitted by the panel, front beam and rear beam together, and loads on the panel near the butt joints (including I, II and III) are given to the spar and finally transmitted to other structural members through the butt joint set.

The advantages of the above described stabilizer box section structure are:

a) and in total, three groups of butt joints can still effectively collect and transmit the load of the stabilizing surface under the condition of one group of failure.

b) The load transmission is direct, and the shearing force, the bending moment and the torque load can be effectively transmitted to the butt joint.

c) The assembly process is simple, and the manufacturing cost is low.

The disadvantages of the above described cassette section structure of the stabilizer are:

a) three groups of butt joints, no wing beam is correspondingly arranged at the position of the butt joint group II, the collecting load capacity is weaker than that of the butt joint group I and the butt joint group III, in order to meet the failure of a single butt joint group, the load can still be effectively transferred, and the structural weight needs to be increased.

b) The butt joint group is connected with the box section in a single-shear mode, and certain eccentricity exists, so that collection and diffusion of loads are not facilitated.

c) The box wall plate and the wing beam are both of composite material structures, and the wall plate and the wing beam are locally thickened at the joint of the box wall plate and the wing beam, so that the manufacturability of the wing beam and the wall plate is not facilitated.

d) The butt joint groups are arranged along the course direction, so that the lateral load cannot be effectively transferred, and the lateral load is the load in the direction vertical to the course load.

Aiming at the problem of structural rigidity arrangement of the existing stabilizer box section structure, the structural weight needs to be additionally increased for effectively transferring load of all butt joint groups at present. Based on the problem, the embodiment of the invention provides an aircraft stabilizer box section butt joint device, which effectively reduces the structural weight and simultaneously aims at improving the lateral load transmission problem of the box section by trying to change the arrangement and the structural form of a joint group.

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 ballast plane box docking device according to an embodiment of the present invention, and fig. 2 is a schematic structural diagram of a ballast plane box assembly in the aircraft ballast plane box docking device shown in fig. 1. The docking device for the aircraft stable surface box section provided by the embodiment of the invention can comprise: a stabilizing surface box section component and a butt joint component.

Referring to fig. 1 and 2, in the structure of the aircraft ballast section docking device, the ballast section assembly comprises a wall plate 1 (the wall plate 1 is not shown in fig. 1), a front beam and a rear beam 5 respectively arranged at the front side and the rear side of the wall plate 1, and a docking rib 6 arranged between the front beam and the rear beam 5.

Based on the structural features of the above ballast surface box assembly, as shown in fig. 1, the butt joint assembly in the embodiment of the present invention includes: an I-group butt joint assembly 7 arranged at the connecting position of the front beam and the butt rib 6, and a II-group butt joint assembly 8 arranged at the connecting position of the rear beam 5 and the butt rib 6.

In the embodiment of the present invention, the connection lug direction of each butt joint 9 in the group I butt joint assembly 7 is perpendicular to the connection lug direction of each butt joint 9 in the group II butt joint assembly 8, and is used for transmitting a heading load and a vertical heading load.

Referring to fig. 2, in the ballast surface box section assembly according to the embodiment of the present invention, the wall plate 1 is provided with a composite material reinforcement structure, and the longitudinal direction is a penetrating structure.

Fig. 3 is a partial structural view of a front beam of the ballast surface box assembly according to the embodiment shown in fig. 2. It can be seen that in the ballast surface box section assembly of the embodiment of the present invention in which the cross section of the front beam is a channel section or a "C" section, with reference to the structure shown in fig. 1 and 2, the front beam in the embodiment of the present invention may include a center front beam 3, a left front beam 2 on one side of the center front beam 3, and right and left front beams 4 on the other side of the center front beam 3.

In the embodiment of the invention, the left front beam 2 and the right front beam 4 are arranged in a symmetrical structure and are arranged in a composite laminated structure, the middle front beam 3 is arranged in a metal material structure, the left front beam 2 and the right front beam 4 are connected into a whole by the middle front beam 3 through a lap joint structure, and two ends of the middle front beam 3 are nested on the left front beam 2 and the right front beam 4 and the opposite end surfaces thereof, as shown in a partial structure of fig. 3.

Fig. 4 is a partial structural view of a back beam in the ballast surface box assembly according to the embodiment shown in fig. 2. It can be seen that in the ballast face box section assembly of the embodiment of the invention, the back beam 5 is provided as a composite laminated structure, the longitudinal direction is a penetrating structure, and the cross section of the back beam is a groove-shaped cross section or a C-shaped cross section.

The structure of the aircraft stabilizer box section docking device shown in fig. 1 and 2 specifically comprises two docking ribs 6 which are arranged in a metal material structure, and each docking rib 6 is mechanically connected with the wall plate 1, the middle front beam 3 and the rear beam 5 into a whole.

In the concrete mechanical connection and temple putting back, the butt-joint wing rib 6 is nested in the groove of the back beam 5 at the connecting position of the butt-joint wing rib 6 and the back beam 5, so that the butt-joint wing rib 6 and the butt-joint wing rib 6 are respectively and mechanically connected with the web plate and the edge strip of the back beam 5; the connecting position of the butt-joint wing rib 6 and the middle front beam 3 is mechanically connected through the lap joint of the front beam rib and the web of the butt-joint wing rib 6.

In practical application, as shown in fig. 1, the pair I of joint assemblies 7 are installed at the intersection of the front center sill 3 and the butt rib 6, and the pair II of joint assemblies 8 are installed at the intersection of the rear sill 5 and the butt rib 6.

As shown in fig. 5, an embodiment of the invention provides a structural schematic diagram of a butt joint in an aircraft ballast surface box butt joint device. Each butt joint 9 in each group of butt joint assemblies comprises two L-shaped butt joint structures arranged side by side, the connecting lug is positioned on one side of the short edge of each butt joint structure, and the two L-shaped butt joint structures are connected into an integral structure through a machine.

As shown in fig. 6, an embodiment of the present invention provides a schematic structural diagram of a connection position between a butt joint and a box section in an aircraft ballast plane box section butt-joint apparatus. The docking device for the aircraft stable surface box section provided by the embodiment of the invention can further comprise: the connection assembly of the cassette section to the butt joint is provided as a strap 10.

In the butt joint of the embodiment of the invention, the long side of the L-shaped butt joint structure is connected with the web plate and the butt joint wing rib 6 into a whole for collecting the shear load of the web plate and the shear load of the butt joint wing rib torque conversion.

The short side of the L-shaped butt joint structure is connected to the wallboard 1 through a band plate 10, the band plate 10 is used for collecting tensile load and compressive load converted from bending moment on the wallboard 1, and finally the other side of the butt joint is connected with the butt joint band plate and the wallboard into a whole.

The aircraft stabilizing surface box section butt joint device provided by the embodiment of the invention aims at the problem that the structural weight needs to be additionally increased for the joint group to effectively transfer the load due to the structural arrangement rigidity problem in the existing aircraft box section structure, and the arrangement and the structural form of butt joint components are changed in the embodiment of the invention, specifically, the butt joint components are arranged into two groups which are respectively arranged at the intersection positions of a front beam, a rear beam and butt joint wing ribs, so that the box section shear force, bending moment and torque load can be effectively transferred, and meanwhile, the box section side load transfer can be effectively transferred; in addition, the structure of the stable noodle box section butt joint device can effectively reduce the weight of the structure.

The following describes in detail an embodiment of an aircraft ballast surface box docking device according to an embodiment of the present invention with an embodiment example.

Referring to fig. 1 to 6, an aircraft ballast surface box docking device in this embodiment includes: a stabilizing surface box section component, a butt joint component and a connecting component of the box section and the butt joint.

The structural design of the stabilizing surface box section component in the embodiment of the invention mainly comprises the following steps: the design of wall plates, front beams, rear beams, butt-joint wing ribs and connection.

(1): the wall plate 1 is of a composite material reinforced structure, the longitudinal direction of the wall plate is of a penetrating structure, and a separating surface is not designed; the longitudinal direction is perpendicular to the heading direction.

(2): the sectional shape of each section of the front beam is designed into a C-shaped section, the section is composed of three parts, namely a left front beam 2, a middle front beam 3 and a right front beam 4, the left front beam 2 and the right front beam 4 are arranged into a composite laminated structure, the middle front beam 3 is arranged into a metal material structure, the left front beam 2 and the right front beam 3 are in a symmetrical structure, the middle front beam 3 connects the left front beam 2 and the right front beam 4 into a whole through a lap joint structure, two ends of the middle front beam 3 are nested on opposite end faces of the front beams on two sides, the connecting fasteners of the middle front beam 3 and the left front beam 2 or the right front beam 4 are arranged in at least one row and at most four rows, and the number of the rows of the fasteners is arranged according to the actual load condition.

(3): the back beam 5 is arranged to be a composite material laminated structure, and a penetrating structure is arranged in the longitudinal direction, so that a separating surface is not designed.

(4): the butt rib 6 (for example, including two portions) is provided as a metal material structure, and is mechanically connected to the wall plate 1, the center front beam 3, and the rear beam 5 to be integrated. The butt-joint wing rib 6 is nested in a groove of the back beam 5 and embedded into the back beam 5 at the position connected with the back beam 5, and the butt-joint wing rib 6 is mechanically connected with a web of the back beam 5 and a rim strip of the back beam; and the positions connected with the front beam are mechanically connected by lapping the front beam ribs and the web plates of the butt-joint wing ribs 6.

(5): the wall plate 1 in the box section assembly is mechanically connected with the front beam, the rear beam and the wing ribs.

The butt joint component in the embodiment of the invention comprises: in the structure, two groups of butt joint assemblies are arranged, and in the two groups of butt joint assemblies, one butt joint in the I group of butt joint assemblies and a butt joint lug corresponding to the position in the II group of butt joint assemblies are vertically arranged. The single butt joint comprises two L-shaped butt joint structures arranged side by side, one side of the short edge of each connecting lug piece, which is positioned on the butt joint structure, is designed into a back-to-back bench-shaped structure, and the two L-shaped butt joint structures are mechanically connected into a whole.

The connecting component of the section and the butt joint in the embodiment of the invention comprises: the docking of the docking head to the cassette requires efficient collection and transfer of cassette loads. The shear load is mainly transmitted by the beam web plate, and the torque load is mainly converted by the butt-joint wing ribs, so that the long side of the butt-joint is connected with the beam web plate and the butt-joint wing ribs into a whole, and the shear load of the beam web plate and the shear load of the butt-joint wing rib torque conversion are effectively collected; bending moment is mainly transmitted through the wall plate, the short side of the butt joint is connected to the wall plate 1 through the belt plate 10, tensile load and compressive load converted from the bending moment on the wall plate are collected through arranging the belt plate (local reinforcing function), and finally the other side of the butt joint is connected with the butt joint belt plate and the wall plate into a whole.

(1): the butt joint group at the front beam side is designed into an L shape, one surface of the butt joint group is connected with a web plate of the middle front beam into a whole, the other surface of the butt joint group is connected with a belt plate 10, a wall plate 1 and a butt joint rib 6 edge strip into a whole, and the row number of the connecting fasteners is specifically determined by the load size.

(2): the butt joint group at the side of the back beam is designed into an L shape, the lug of the butt joint is perpendicular to the front butt joint and arranged, one side of the lug is connected with the web plate of the back beam into a whole, the other side of the lug is connected with the band plate, the wall plate and the butt joint rib edge strip into a whole, and the row number of the connecting fasteners is specifically determined by the load size.

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.