CN214190076U

CN214190076U - Plane stabilizer

Info

Publication number: CN214190076U
Application number: CN202023281056.9U
Authority: CN
Inventors: 高伟
Original assignee: AVIC First Aircraft Institute
Current assignee: Xian Aircraft Design and Research Institute of AVIC; AVIC First Aircraft Institute
Priority date: 2020-12-29
Filing date: 2020-12-29
Publication date: 2021-09-14
Anticipated expiration: 2030-12-29

Abstract

The utility model discloses an aircraft stabilizer device, including leading edge and box section, wherein: partition plates are arranged inside the front edge at intervals in the unfolding direction, and panels are wrapped outside the partition plates; the box section comprises an upper wall plate, a lower wall plate, a main beam, an auxiliary beam and wing ribs, wherein the upper wall plate and the lower wall plate are respectively arranged at the upper side and the lower side of the box section; the wing ribs are distributed inside the box section in the unfolding direction, and the wing ribs are fixedly connected with the main beam, the auxiliary beam, the upper wall plate and the lower wall plate. The utility model discloses can solve the less problem of traditional stabilizer device box section load, improve structural efficiency.

Description

Plane stabilizer

Technical Field

The utility model relates to an aircraft structural design field, concretely relates to aircraft stabilizer device.

Background

The front edge and the rear edge of the conventional plane stabilizer are connected with the box section into a whole through metal strips; the structure is mature in form and simple in manufacturing and assembling process, but has the following problems:

1. one side of the box section wallboard bears a main bearing compression load, the other side of the box section wallboard bears a tensile load, the problem of skin stability of the compression load wallboard is obvious, the maintenance effect of a thin skin is poor, more wing ribs are needed for collecting pneumatic load and assisting in maintaining shape, and the larger weight cost is paid;

2. the front beam and the back beam are both C-shaped sections, the effect of bearing torque load is poor, and the efficiency of transferring torque load is not high for a thin skin structure.

3. The box sections are connected to both the leading and trailing edges by metal straps, and the presence of the difference in the coefficients of thermal expansion of the composite and metal materials tends to create additional compressive loads on the box section wall panels, thereby causing an increase in weight.

4. The mechanical connection has the advantages of low integration level of the assembly form, large assembly workload, long period, high cost and considerable weight of a large number of connecting pieces.

5. In order to meet the requirement of fastener countersink, the thickness of the thin-wall plate skin needs to be locally increased at the joint of the fastener, so that the process difficulty and the weight are increased.

Disclosure of Invention

The utility model aims at providing an aircraft stabilizer device for solve the less problem of traditional stabilizer device box section load, improve structural efficiency.

In order to realize the task, the utility model discloses a following technical scheme:

an aircraft stabilizer device comprising a leading edge and a box section, wherein:

partition plates are arranged inside the front edge at intervals in the unfolding direction, and panels are wrapped outside the partition plates;

the box section comprises an upper wall plate, a lower wall plate, a main beam, an auxiliary beam and wing ribs, wherein the upper wall plate and the lower wall plate are respectively arranged at the upper side and the lower side of the box section; the wing ribs are distributed inside the box section in the unfolding direction, and the wing ribs are fixedly connected with the main beam, the auxiliary beam, the upper wall plate and the lower wall plate.

Further, when the arrangement distance between the partition boards in the front edge is smaller than N, the front edge is in a partition board sparse configuration, and the panel is in a laminated structure; when the arrangement distance between the partition plates in the front edge is larger than N, the partition plates are in a close partition plate configuration, the panel is in a sandwich structure, and the panel and the partition plates are in an adhesive joint form to form an integral structure.

Furthermore, the partition plate is of a semi-elliptical structure, and the larger end of the partition plate is close to the main beam; the edge of the partition board is provided with a circle of connecting edge used for connecting the panel.

Furthermore, the cross section of the main beam is a rectangular section, and the structural forms of the main beam are two, wherein one structural form is a sandwich structure, and the other structural form is a laminated structure.

Furthermore, the cross section of the auxiliary beam is in a C-shaped cross section form, and the structural form is a laminated plate structural form or a sandwich structural form.

Furthermore, the rib is made of a foam structure, the forming process is mechanical processing, and the outer surface is adhered with a glass cloth layer through an adhesive bonding process.

Furthermore, the partition boards and the panels in the front edge are all of composite material structures, and the upper wall boards, the lower wall boards, the main beams, the auxiliary beams and the wing ribs in the box section are all of composite material structures.

Furthermore, the upper wall plate and the lower wall plate are of a composite material sandwich structure.

Further, the front edge and the box section are overlapped with the edge of the panel in the front edge through grooves in the edges of the upper wall plate and the lower wall plate and then are connected into a whole through machinery.

Compared with the prior art, the utility model has the following technical characteristics:

1. the traditional front beam and the traditional rear beam are combined and designed into a rectangular square beam, the rectangular square beam forms a closed structure, box section torque load can be effectively transmitted, and meanwhile, the characteristics of the rectangular square beam can still transmit shearing force and bending moment load of a stabilizing surface.

2. The front edge and the box section are integrated by gluing the structural components, and are not connected by fasteners, so that the risk of mechanical connection damage is reduced, and the superiority of the composite material is fully exerted.

3. The front edge and the box section are connected into a whole through overlapping, so that conventional metal butt joint parts are reduced, and the additional compression load of the wall plate caused by the difference of thermal expansion coefficients of metal and composite materials is avoided, so that the weight of the wall plate structure is reduced.

Drawings

Fig. 1 is a schematic view of the overall structure of the present invention;

fig. 2 is a schematic view of the structure of the present invention;

the reference numbers in the figures illustrate: 1 panel, 2 clapboards, 3 lower wall boards, 4 upper wall boards, 5 main beams, 6 auxiliary beams and 7 ribs.

Detailed Description

Referring to fig. 1 and 2, the utility model discloses an aircraft stabilizer device, including leading edge and box section, wherein: partition plates 2 are arranged inside the front edge at intervals in the unfolding direction, and panels 1 are wrapped outside the partition plates 2; the box section comprises an upper wall plate 4, a lower wall plate 3, a main beam 5, an auxiliary beam 6 and wing ribs 7, wherein the upper wall plate 4 and the lower wall plate 3 are respectively arranged at the upper side and the lower side of the box section, the main beam 5 and the auxiliary beam 6 are respectively arranged at two sides of the upper wall plate 4 and the lower wall plate 3 along the unfolding direction, and the main beam 5 is positioned between the front edge and the upper wall plate 4 and the lower wall plate 3; the wing ribs 7 are distributed inside the box section along the unfolding direction, and the wing ribs 7 are fixedly connected with the main beam 5, the auxiliary beam 6, the upper wall plate 4 and the lower wall plate 3.

In the embodiment of the application, the front panel 1 and the partition board 2 of the front edge are both designed into composite material structures; when the arrangement distance between the partition boards 2 in the front edge is smaller than N, the front edge is in a sparse partition board configuration, and the panel 1 adopts a laminated structure; when the arrangement distance between the partition boards 2 in the front edge is larger than N, the front edge is in a close partition board configuration, the panel 1 adopts a sandwich structure, and the panel 1 and the partition boards 2 form an integral structure in a gluing mode; wherein the specific value of N is determined according to actual requirements; the partition plate 2 is of a semi-elliptical structure, and the larger end of the partition plate 2 is close to the main beam 5; a circle of connecting edge used for connecting the panel 1 is arranged at the edge of the clapboard 2; the panels 1 and the partitions 2 are glued to form a unitary structure.

The upper wall plate 4, the lower wall plate 3, the main beam 5, the auxiliary beam 6 and the wing ribs 7 in the box section are all made of composite materials. The upper wall plate 4 and the lower wall plate 3 are designed into a composite material sandwich structure; the cross section of the main beam 5 is a rectangular section, the structural forms can be two, one is a sandwich structure, the other is a laminated structure, and the main beam 5 is determined to be in a sandwich structural form or a laminated structural form according to the actual situation of the wing-shaped height; the section of the auxiliary beam 6 is in a C-shaped section form, the structural form can be a laminated plate structural form or a sandwich structural form, and the laminated plate structural form is preferably selected; the rib 7 is made of foam structure, the forming process is mechanical processing, and the outer surface is glued with a glass cloth layer through a glue joint process. The ribs 7 are integrated with the main beams 5 and the auxiliary beams 6 by gluing, and the upper and lower wall plates 3 are integrated with the spars and the ribs 7 by gluing.

The front edge and the box section are overlapped with the edge of the panel 1 of the front edge by manufacturing a lower groove on an upper wall plate 4 and a lower wall plate 3 of the box section, and then are connected into a whole by a machine. The grooves on the upper wall plate 4 and the lower wall plate 3 can be formed at one time through a forming die, or the grooves can be processed through numerical control, and the grooves are preferably formed at one time through the die.

The above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equally replaced; such modifications and substitutions do not substantially depart from the spirit and scope of the embodiments of the present application, and are intended to be included within the scope of the present application.

Claims

1. An aircraft stabilizer device, comprising a leading edge and a box section, wherein:

the partition boards (2) are arranged inside the front edge at intervals in the spanwise direction, and the panels (1) are wrapped outside the partition boards (2);

the box section comprises an upper wall plate (4), a lower wall plate (3), a main beam (5), an auxiliary beam (6) and wing ribs (7), wherein the upper wall plate (4) and the lower wall plate (3) are respectively arranged at the upper side and the lower side of the box section, the main beam (5) and the auxiliary beam (6) are respectively arranged at two sides of the upper wall plate (4) and the lower wall plate (3) along the unfolding direction, and the main beam (5) is positioned between the front edge and the upper wall plate (4) and the lower wall plate (3); the wing ribs (7) are distributed inside the box section along the unfolding direction, and the wing ribs (7) are fixedly connected with the main beam (5), the auxiliary beam (6), the upper wall plate (4) and the lower wall plate (3).

2. The aircraft stabilizer device according to claim 1, characterized in that when the arrangement distance between the internal partitions (2) of the leading edge is smaller than N, the front edge is of a sparse partition configuration, and the panel (1) is of a laminated structure; when the arrangement distance between the partition plates (2) in the front edge is larger than N, the partition plates are of a dense partition plate configuration, the panel (1) is of a sandwich structure, and the panel (1) and the partition plates (2) form an integral structure in a gluing mode.

3. An aircraft stabilizer device according to claim 1, characterized in that said partition (2) is of a semi-elliptical configuration, the larger end of the partition (2) being close to said main beam (5); the edge of the clapboard (2) is provided with a circle of connecting edge for connecting the panel (1).

4. An aircraft stabilizer arrangement according to claim 1, characterized in that the cross section of the main beam (5) is rectangular and the structural form is two, one being a sandwich structure and the other being a laminate structure.

5. Aircraft stabilizer arrangement according to claim 1, characterized in that the cross-section of the auxiliary beam (6) is selected from the form of a "C" section, either in the form of a laminate or in the form of a sandwich structure.

6. An aircraft stabilizer device according to claim 1, characterized in that the material of said ribs (7) is a foam structure, the forming process is a mechanical process, and the outer surface is glued with a glass cloth layer by a gluing process.

7. An aircraft stabilizer device according to claim 1, characterized in that the partition (2) and the panel (1) in the leading edge are of composite material construction, and the upper panel (4), the lower panel (3), the main beam (5), the auxiliary beam (6) and the ribs (7) in the box section are of composite material construction.

8. An aircraft stabilizer device according to claim 1, characterized in that said upper and lower panels (4, 3) are of composite sandwich construction.

9. An aircraft stabilizer device according to claim 1, characterized in that the leading edge, box section, overlaps the panel (1) edge in the leading edge by means of a groove at the edge of the upper (4) and lower (3) wall panels and is then connected integrally by means of a mechanical connection.