CN210681136U

CN210681136U - Control surface combined wing beam structure

Info

Publication number: CN210681136U
Application number: CN201921735250.4U
Authority: CN
Inventors: 刘豫; 王远芳; 郑青泉
Original assignee: Xian Aircraft Design and Research Institute of AVIC
Current assignee: Xian Aircraft Design and Research Institute of AVIC
Priority date: 2019-10-16
Filing date: 2019-10-16
Publication date: 2020-06-05
Anticipated expiration: 2029-10-16

Abstract

The application belongs to aircraft structural design field, in particular to control surface combination wing spar structure includes: the support body is integrally formed by metal materials and comprises a web plate, a suspension connecting piece and an operation connecting piece, wherein the suspension connecting piece is vertically arranged on the web plate; the spar body of combined material, two spar bodies are fixed connection respectively to the both ends tip of web. According to the control surface combined wing beam structure, the suspension connecting pieces and the control connecting pieces which are densely arranged are designed to be a metal integrated piece, so that the excellent mechanical property of a metal material is fully utilized, and a great concentrated load can be borne; meanwhile, the assembly workload of a plurality of metal suspension supports is reduced, the assembly precision is improved, and the assembly fixture can be simplified; in addition, areas of the spar structure that are less loaded are manufactured using composite material designs to reduce the weight of the structure.

Description

Control surface combined wing beam structure

Technical Field

The application belongs to the field of aircraft structural design, and particularly relates to a control surface combined wing beam structure.

Background

The wing beam structure of the airplane control surface is used as a main bearing component for transferring concentrated load, and a suspension support is arranged on the wing beam and used for connecting the control surface and the control system. The spar structure is typically manufactured from a composite material to reduce the weight of the structure, and the suspension mounts are typically manufactured from a metal structure and assembled to the spar. For the condition that the suspension supports are densely arranged, the composite material wing beam is generally designed to have larger thickness for bearing larger concentrated load, so that the weight of the structure is too heavy; if the whole spar structure is made of metal, the problem of heavy structure is also caused.

SUMMERY OF THE UTILITY MODEL

In order to solve at least one of the above technical problems, the present application provides a control surface composite spar structure.

The application discloses control surface combination spar structure includes:

the support comprises a support body, a support body and a support body, wherein the support body is an integrally formed component made of a metal material and comprises a web plate, a suspension connecting piece and a control connecting piece, wherein the suspension connecting piece and the control connecting piece are vertically arranged on the web plate;

the wing beam body is a plate-shaped wing beam body, the wing beam body is a composite material plate, and the two wing beam bodies are fixedly connected to the end parts of the two ends of the web plate of the support body along the length direction respectively.

According to at least one embodiment of the application, the upper side and the lower side of the width direction of the support body are convexly provided with the edge strips along the direction vertical to the web plate.

According to at least one embodiment of the present application, the cross-sectional shape of the spar body in the width direction is substantially C-shaped, as is the cross-sectional shape of the entire member formed by the web and the upper and lower flanges.

According to at least one embodiment of the present application, the web and the upper and lower flanges are integrally formed with a spar body, and the spar body is fitted to the web and the upper and lower flanges.

According to at least one embodiment of the application, the suspension connection and the steering connection are each of a binaural structure, with an inner stiffener disposed between the ears of the binaural structure.

According to at least one embodiment of the application, outer reinforcing ribs are arranged on the outer sides of the two lugs of the suspension connector double-lug structure.

According to at least one embodiment of the present application, the mount body is an aluminum alloy integrally molded member.

The application has at least the following beneficial technical effects:

according to the control surface combined wing beam structure, the wing beam structure comprises the support body and the composite wing beam body which are integrally formed by metal materials, the suspension connecting pieces and the control connecting pieces which are densely arranged are designed to be metal integrated pieces, the excellent mechanical property of the metal materials is fully utilized, and great concentrated load can be borne; meanwhile, the assembly workload of a plurality of metal suspension supports is reduced, the assembly precision is improved, and the assembly fixture can be simplified; in addition, areas of the spar structure that are less loaded are manufactured using composite material designs to reduce the weight of the structure.

Drawings

FIG. 1 is a schematic view of a control surface composite spar structure of the present application;

FIG. 2 is a schematic structural view of a spar body in the control surface composite spar structure of the present application;

FIG. 3 is a schematic structural diagram of a support body in the control surface composite spar structure of the present application;

FIG. 4 is a front view of the support body in the control surface composite spar structure of the present application.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

In the description of the present application, it is to be understood that if the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., are used to indicate an orientation or positional relationship based on that shown in the drawings, that this is for convenience and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the present application.

The present application is described in further detail below with reference to fig. 1-4.

The application discloses control surface combination spar structure can include support body 2 and spar body 1.

Specifically, as shown in fig. 3, the holder body 2 is a metal material integrally molded member, and in the present embodiment, an aluminum alloy integrally molded member is further preferable; may include a web 3, a suspension link 6 vertically disposed on the web 3, and a manipulation link 7; the number and position of the suspension connections 6 and the actuation connections 7 can be set appropriately according to the number of suspension points and actuation points.

Further, preferably, the upper side and the lower side of the support body 2 in the width direction are convexly provided with the edge strips 4 along the direction perpendicular to the web 3, so that the cross section of the integral piece formed by the web 3 and the upper edge strips and the lower edge strips 4 in the width direction is approximately C-shaped, and the structural strength is increased.

The spar body 1 is a plate-shaped composite material plate made of a composite material, and preferably has a cross-sectional shape in the width direction that is the same as the cross-sectional shape in the width direction of the entire member made of the web 3 and the upper and lower flanges 4, that is, a substantially C-shape, and similarly can increase the structural strength.

Further, two wing spar bodies 1 are respectively and fixedly connected to the end parts of two ends of a web 3 of the support body 2 along the length direction. In addition, various suitable fixing manners can be adopted according to needs, in this embodiment, it is preferable that the end portions of both ends of the integral piece formed by the web 3 and the upper and lower flanges 4 are provided with the sunken portions 5, and the spar bodies 1 at both ends are fittingly installed (sleeved) at the sunken portions 5 and fixedly connected through fasteners such as bolts, so that the connection is more stable.

Further, the control surface composite spar structure of the present application may also comprise outer and inner

stiffening ribs

8, 9 to enhance the structural stability of the overall structure, in particular of the suspension and

steering connections

6, 7.

Specifically, the inner reinforcing rib 9 is disposed on the inner side of the suspension link 6 and the double lugs of the steering link 7 according to the load distribution, and the outer reinforcing rib 8 is disposed on the outer side of the double lugs of the suspension link 6 which receives the inertial load of the control surface.

In summary, the control surface combined wing beam structure comprises the support body and the composite wing beam body which are integrally formed by metal materials, and the suspension connecting pieces and the control connecting pieces which are densely arranged are designed into a metal integrated piece, so that the excellent mechanical property of the metal materials is fully utilized, and the great concentrated load can be borne; meanwhile, the assembly workload of a plurality of metal suspension supports is reduced, the assembly precision is improved, and the assembly fixture can be simplified; in addition, areas of the spar structure that are less loaded are manufactured using composite material designs to reduce the weight of the structure.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A control surface composite spar structure comprising:

the support comprises a support body (2), wherein the support body (2) is a metal material integrally formed component and comprises a web plate (3), a suspension connecting piece (6) and a control connecting piece (7), wherein the suspension connecting piece (6) is vertically arranged on the web plate (3);

the wing beam comprises plate-shaped wing beam bodies (1), the wing beam bodies (1) are composite plates, and the two wing beam bodies (1) are fixedly connected to the end parts of the two ends of a web plate (3) of the support body (2) along the length direction respectively.

2. Rudder surface built-up spar structure according to claim 1, characterised in that on both sides in the width direction of the carrier body (2) there are projecting flanges (4) in a direction perpendicular to the web (3).

3. Rudder surface built-up spar structure according to claim 2, characterised in that the cross-sectional shape in the width direction of the spar body (1) is approximately C-shaped, the same as the cross-sectional shape in the width direction of the whole formed by the web (3) and the upper and lower flanges (4).

4. Rudder surface built-up spar structure according to claim 3, characterised in that undercuts (5) are provided at both end parts of the whole piece of web (3) and upper and lower flanges (4), the spar bodies (1) at both ends being fitted at the position of the undercuts (5).

5. Control surface built-up spar structure according to claim 1, wherein the suspension connection (6) and the steering connection (7) are each of a binaural structure, with an inner stiffening rib (9) arranged between the ears of the binaural structure.

6. Rudder surface built-up spar structure according to claim 5, characterised in that outside stiffening ribs (8) are provided outside the two lugs of the binaural structure of the suspension connection (6).

7. Rudder surface built-up spar structure according to claim 1, characterised in that the carrier body (2) is an aluminium alloy one-piece component.