CN211766254U

CN211766254U - Control surface structure with sealing edge

Info

Publication number: CN211766254U
Application number: CN201922217013.5U
Authority: CN
Inventors: 方宜武; 陈修贤; 周龙超; 汤晓明; 黄雍威
Original assignee: Hubei Jili Taili Flying Car Co ltd; Zhejiang Geely Holding Group Co Ltd
Current assignee: Chengdu Wofeitianyu Technology Co ltd; Zhejiang Geely Holding Group Co Ltd
Priority date: 2019-12-11
Filing date: 2019-12-11
Publication date: 2020-10-27
Anticipated expiration: 2029-12-11

Abstract

The utility model discloses a take control surface structure of banding relates to aircraft technical field. The control surface structure with the edge sealing of the utility model comprises a sandwich element, an edge sealing element and a plugging element; the sandwich element has a first side facing away from the airfoil, the edge banding has a joint face having a shape matching the shape of the first side, the joint face being adhesively bonded to the first side; the end of the core clamping piece and the end of the edge sealing piece are sleeved with the plugging piece, and the end of the core clamping piece and the end of the edge sealing piece are both glued to the inner surface of the plugging piece. Compared with the prior art, the utility model discloses have the structural seal nature of preferred, can prevent effectively that liquid from getting into inside the control surface structure, be favorable to reducing maintenance cost and replacement cost, and seal through structure self, it is obvious to subtract heavy effect.

Description

Control surface structure with sealing edge

Technical Field

The utility model relates to an aircraft technical field especially relates to a take control surface structure of banding.

Background

In order to realize the weight reduction effect, the control surface structure of the aircraft adopts core materials and continuous fiber reinforced resin matrix composite materials, such as carbon fiber-epoxy composite materials and the like, and can meet the rigorous requirements of the aircraft on light weight, strength, rigidity and the like. The core material is sensitive to moisture, liquid and other environments, and the sealing performance of the core material is extremely critical. In the prior art, a special sealing element is designed for a core material, but the additional sealing element can increase the weight of a control surface, reduce the weight reduction effect of a composite material and be not beneficial to the light weight design of an aircraft.

Therefore, it is necessary to provide a control surface structure with a sealing edge to solve the above technical problems.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a take control surface structure of banding to solve the technical problem that the control surface in the background art exists.

The utility model discloses a realize through following technical scheme:

the utility model provides a control surface structure with a sealing edge, which comprises a sandwich component, a sealing edge component and a plugging component; the sandwich element has a first side facing away from the airfoil, the edge banding has a joint face having a shape matching the shape of the first side, the joint face being adhesively bonded to the first side; the end of the core clamping piece and the end of the edge sealing piece are sleeved with the plugging piece, and the end of the core clamping piece and the end of the edge sealing piece are both glued to the inner surface of the plugging piece.

Furthermore, the sandwich element is provided with a sandwich element middle part, and the end part of the sandwich element is lower than the sandwich element middle part to form a first step part; the sandwich element has a second side opposite to the first side, the first step has a distance from the first side to the second side that is smaller than a distance from the first side to the second side in the middle of the sandwich element, and the sandwich element forms an "L" -shaped surface at each end of the first side.

Furthermore, the upper surface of the edge sealing piece comprises a pneumatic surface, a skin connecting surface and a transition surface, wherein the pneumatic surface, the skin connecting surface and the transition surface sequentially descend from the outer side of the edge sealing piece in a step shape; the end of the edge sealing piece is provided with a boss matched with the shape of the L-shaped surface.

Further, the boss is arranged at two ends of the connecting surface, the boss is glued to the L-shaped surface, and the boss is glued to the first step portion and then is provided with a flat plane.

Further, a main beam having one side bonded to the second side of the core sandwich member; the girder includes girder middle part and locates the second step portion at girder middle part both ends, second step portion is less than the girder middle part, second step portion with it levels the plane to have after first step portion splices.

Further, the closure has a bottom surface, second step portion first step portion with the boss certainly the bottom surface in proper order the glue joint in closure's internal surface, closure with the girder middle part with clip spare middle part butt joint department all has level and smooth plane.

Furthermore, the end opening surface of the plugging piece close to the edge sealing piece is glued with the connecting surface.

Further, the edge sealing piece, the plugging piece and the main beam are all made of continuous fiber reinforced resin matrix composite materials.

Further, the control surface structure with the edge sealing further comprises a skin, the skin covers the upper surface and the lower surface of a framework formed by the main beam, the core clamping piece, the plugging piece and the edge sealing piece, and the skin is made of a continuous fiber reinforced resin matrix composite material.

Further, the control surface structure with the seal edge further comprises joints, wherein the joints are symmetrically arranged at two ends of the middle part of the main beam, and the joints are used for connecting the main beam to the airfoil.

Implement the utility model discloses, following beneficial effect has:

(1) the utility model discloses a take control surface structure of banding seals through self structure, compares and adopts extra sealing member to seal the double-layered chipware among the prior art, and the heavy effect that subtracts of control surface is obvious, is favorable to the lightweight design of aircraft.

(2) The utility model discloses a take control surface structure of banding utilizes self structure to seal, and structural seal nature is splendid, can prevent effectively that liquid from getting into the control surface structure in, is favorable to reducing the maintenance cost and the replacement cost of control surface.

Drawings

In order to more clearly illustrate the technical solutions and advantages of the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without inventive work.

FIG. 1 is an exploded schematic view of a control surface with an edge seal according to an embodiment of the present invention;

FIG. 2 is a schematic view of the assembly of the edge banding and the sandwich element according to the embodiment of the present invention;

fig. 3 is a schematic structural view of a closure according to an embodiment of the present invention;

FIG. 4 is a schematic view of the assembly of the closeout, sandwich element, and closure of an embodiment of the present invention;

fig. 5 is a schematic view of the assembly of the main beam and the block piece according to the embodiment of the present invention;

FIG. 6 is a schematic view of the assembly of the main beam, the plugging member, the sandwich member and the edge sealing member according to the embodiment of the present invention;

fig. 7 is a schematic structural view of a control surface with a sealing edge according to an embodiment of the present invention.

Wherein the reference numerals in the figures correspond to: 1-sandwich element, 11-first side face, 12-sandwich element middle part, 13-first step part, 2-edge sealing element, 21-pneumatic face, 22-skin connecting face, 23-transition face, 24-connecting face, 25-boss, 3-sealing element, 31-port face, 32-bottom face, 4-girder, 41-girder middle part, 42-second step part, 5-skin and 6-joint.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention clearer, the present invention will be described in further detail with reference to the accompanying drawings. It is obvious that the described embodiments are only some of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative efforts belong to the protection scope of the present invention.

In the description of the present invention, it is to be understood that the terms "first," "second," and the like are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the invention described herein are capable of operation in sequences other than those illustrated or otherwise described herein.

In the present invention, unless otherwise expressly stated or limited, the terms "connected" and "connecting" are to be construed broadly, e.g., as meaning a fixed connection, a removable connection, or an integral part; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.

Examples

The present embodiment provides a control surface structure with edge sealing, see fig. 1-2, comprising a core member 1, an edge sealing member 2 and a closure member 3; the sandwich element 1 has a first side 11 facing away from the airfoil, the edge seal 2 has a connecting surface 24, the shape of the connecting surface 24 matches the shape of the first side 11 of the sandwich element 1, and the connecting surface 24 is glued to the first side 11; the end part of the sandwich element 1 and the end part of the edge sealing element 2 are sleeved with the plugging element 3, and the end parts of the sandwich element 1 and the edge sealing element 2 are both glued with the inner surface of the plugging element 3. The control surface with the sealing edge of the embodiment is sealed by using the structure of the control surface, and compared with the prior art in which an additional sealing element is adopted to seal the sandwich element, the control surface has an obvious weight reduction effect and is beneficial to the lightweight design of an airplane.

As a specific embodiment, the sandwich element 1 has a sandwich element middle portion 12, and the end portion of the sandwich element 1 is lower than the sandwich element middle portion 12 to form a first step portion 13; the sandwich element 1 has a second side opposite to the first side 11, the first step 13 being located at a distance from the first side 11 to the second side which is smaller than the distance from the first side 11 to the second side of the sandwich element 12, the sandwich element 1 forming an "L" -shaped surface at each end of the first side 11.

As a specific embodiment, the upper surface of the edge sealing member 2 comprises a pneumatic surface 21, a skin connecting surface 22 and a transition surface 23 which descend from the outer side of the edge sealing member 2 in a step-like manner in sequence, and the pneumatic surface 21 is used as a part of a pneumatic outer surface and meets the aerodynamic characteristics; the skin connecting surface 22 is used for being glued with the skin, and the transition surface 23 is adjacent to the connecting surface 24; the end of the edge banding 2 is provided with a boss 25 matching the shape of the "L" shaped surface.

In a specific embodiment, the bosses 25 are disposed at two ends of the connecting surface 24, the bosses 25 are glued to the "L" -shaped surface, and the bosses 25 are glued to the first step portion 13 to form a flat surface, so as to facilitate the flatness of the subsequent skin surface.

As a specific implementation, the control surface structure in this embodiment further includes a main beam 4, one side of the main beam 4 is glued to the second side of the sandwich element 1; the girder 4 includes girder middle part 41 and locates the second step portion 42 at girder middle part 41 both ends, and second step portion 42 is less than girder middle part 41, and second step portion 42 has smooth plane after gluing with first step portion 13 to do benefit to the roughness of follow-up skin face.

As a specific embodiment, the plugging member 3 has a bottom surface 32, and the shape of the second step portion 42, the first step portion 13 and the boss 25 after being glued is matched with the cavity shape of the plugging member 3, so that the plugging member 3 is clamped at the end portions of the main beam 4, the core member 1 and the edge sealing member 2, and the second step portion 42, the first step portion 13 and the boss 25 are sequentially glued to the inner surface of the plugging member 3 from the bottom surface 32, so that the main beam 4, the core member 1, the edge sealing member 2 and the plugging member 3 are stably connected, and the sealing property of the core member 1 is ensured. The joints of the plugging piece 3, the main beam middle part 41 and the sandwich piece middle part 12 are provided with flat planes, so that the flatness of the subsequent skin surface is facilitated.

In a specific embodiment, the end of the sealing member 3 close to the edge banding member 2 is opened to form an end surface 31, and the end surface 31 is glued to the connecting surface 24 around the boss 25, so that no gap is left between the sealing member 3 and the edge banding member 2, thereby ensuring the sealing performance of the core material 1.

As a specific implementation mode, the edge sealing piece 2, the plugging piece 3 and the main beam 4 are all made of continuous fiber reinforced resin matrix composite materials, and the composite materials have the characteristics of light weight and high strength, so that the weight of the airplane is greatly reduced, and the lightweight design of the airplane is facilitated.

As a specific implementation manner, the control surface structure in this embodiment further includes a skin 5, the skin 5 covers upper and lower surfaces of a framework formed by the main beam 4, the sandwich element 1, the plugging element 3 and the edge sealing element 2, a flat plane is formed on the main beam middle portion 41, the sandwich element middle portion 12, the plugging element 3 and the skin connecting surface 22, and the skin 5 is made of a continuous fiber reinforced resin-based composite material, which has the characteristics of light weight and high strength, so that the weight of the aircraft is greatly reduced, and the lightweight design of the aircraft is facilitated.

As a specific implementation, the control surface structure in this embodiment further includes joints 6, the joints 6 are symmetrically disposed at two ends of the main beam middle portion 41, and the joints 6 are used for connecting the main beam 4 to the airfoil.

As a specific embodiment, the joint 6 is a metal joint to ensure the stable and reliable connection of the main beam 4 to the airfoil.

The control surface structure with the sealing edge in the embodiment utilizes the structure of the control surface structure to seal, so that the weight of the control surface is greatly reduced, and the lightweight design of an airplane is facilitated; the control surface structure in this embodiment utilizes banding spare and shutoff spare to seal up the foam core, and structural seal nature is splendid, can prevent effectively that liquid from getting into the control surface structure in, is favorable to reducing the maintenance cost and the replacement cost of control surface.

The above embodiment of the utility model has following beneficial effect:

(1) the utility model discloses a take control surface structure of banding seals through structure self, compares and adopts extra sealing member to seal the double-layered chipware among the prior art, and the heavy effect that subtracts of control surface is obvious, is favorable to the lightweight design of aircraft.

(2) The utility model discloses a take control surface structure of banding utilizes structure self to seal, and structural seal nature is splendid, can prevent effectively that liquid from getting into the control surface structure in, is favorable to reducing the maintenance cost and the replacement cost of control surface.

The foregoing is a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of improvements and decorations can be made without departing from the principle of the present invention, and these improvements and decorations are also considered as the protection scope of the present invention.

Claims

1. A control surface structure with a sealing edge is characterized by comprising a core clamping component (1), a sealing edge component (2) and a plugging component (3);

the sandwich element (1) has a first side surface (11) away from the airfoil, the binder element (2) has a joint surface (24), the shape of the joint surface (24) matches the shape of the first side surface (11), and the joint surface (24) is glued to the first side surface (11);

the end of clamp core spare (1) with the tip of banding piece (2) is located to shutoff piece (3) cover, the end of clamp core spare (1) with the tip of banding piece (2) all with the internal surface cementing of shutoff piece (3).

2. The control surface structure with edge seal according to claim 1, wherein the core member (1) has a core member center portion (12), and the end portion of the core member (1) is lower than the core member center portion (12) to form a first step portion (13);

the core piece (1) has a second side opposite to the first side (11), the first step (13) being located at a distance from the first side (11) to the second side that is smaller than the distance from the first side (11) to the second side of the core piece middle (12), the core piece (1) forming an "L" -shaped surface at each of the two ends of the first side (11).

3. A control surface structure with edge seal according to claim 2, characterized in that the upper surface of the edge seal (2) comprises an air surface (21), a skin connecting surface (22) and a transition surface (23) descending in a stepped manner from the outside of the edge seal (2), the skin connecting surface (22) being intended for gluing to a skin, the transition surface (23) being adjacent to the connecting surface (24); the end part of the edge sealing piece (2) is provided with a boss (25) matched with the shape of the L-shaped surface.

4. The control surface structure with the edge seal according to claim 3, wherein the bosses (25) are arranged at two ends of the connecting surface (24), the bosses (25) are glued to the L-shaped surface, and the bosses (25) are glued to the first step portion (13) to form a flat surface.

5. The edge-sealed control surface structure according to claim 3, further comprising a main beam (4), one side of the main beam (4) being glued to the second side of the core sandwich component (1);

girder (4) include girder middle part (41) and locate second step portion (42) at girder middle part (41) both ends, second step portion (42) are less than girder middle part (41), second step portion (42) with first step portion (13) have after gluing and level the plane.

6. A control surface structure with edge sealing according to claim 5, characterized in that the closure (3) has a bottom surface (32), the second step (42), the first step (13) and the boss (25) are glued to the inner surface of the closure (3) in the order from the bottom surface (32), and the joints of the closure (3) with the main beam middle part (41) and the sandwich element middle part (12) are flat and planar.

7. A control surface structure with edge seal according to claim 6, characterized in that the closure member (3) is glued to the attachment surface (24) close to the port surface (31) of the edge seal (2).

8. A control surface structure with edge sealing according to claim 5, characterized in that the edge sealing member (2), the closure member (3) and the main beams (4) are made of a continuous fibre reinforced resin based composite material.

9. A control surface structure with edge banding according to claim 5, characterized in that it further comprises a skin (5), said skin (5) covering the upper and lower surfaces of the skeleton formed by said main beam (4), said core-clamping member (1), said obturating member (3) and said edge banding (2), said skin (5) being made of a continuous fiber reinforced resin based composite material.

10. The edge-sealed control surface structure according to claim 5, further comprising joints (6), wherein the joints (6) are symmetrically arranged at two ends of the main beam middle part (41), and the joints (6) are used for connecting the main beam (4) to an airfoil.