CN113883272B

CN113883272B - Light civil aircraft slat sealing member

Info

Publication number: CN113883272B
Application number: CN202111026146.XA
Authority: CN
Inventors: 姚学锋; 闫涵; 徐逍遥
Original assignee: Tsinghua University
Current assignee: Tsinghua University
Priority date: 2021-09-02
Filing date: 2021-09-02
Publication date: 2022-09-23
Anticipated expiration: 2041-09-02
Also published as: CN113883272A

Abstract

The invention discloses a light civil aircraft slat sealing element, which comprises an inverted U-shaped bulge part, an arc-shaped side wall and a strip-shaped clamping part, wherein the arc-shaped side wall is provided with a convex part; the bulge comprises a first side wall, an arc-shaped top end and a second side wall, and the first side wall, the arc-shaped top end and the second side wall are connected in sequence and are in smooth transition; the second side wall of the bulge is connected with the arc-shaped side wall, the joint of the second side wall and the arc-shaped side wall is in smooth transition, and the arc-shaped side wall and the bulge enclose a hollow area; the arc lateral wall links to each other with bar clamping part end, and the first lateral wall rounding off of bar clamping part end and bellying links to each other, and the composite material strip has been inlayed to the middle of the bar clamping part. The invention can eliminate the clearance between civil aircraft slat structures, prevent the airflow from passing through the seam channel in the flight process of the aircraft, play a role in pneumatic sealing, and simultaneously solve the problems of overlarge compression deformation and heavy mass of the traditional slat sealing element.

Description

Light civil aircraft slat sealing member

Technical Field

The invention relates to a structure of a sealing element, in particular to a lightweight civil aircraft slat sealing element, and belongs to the technical field of pneumatic sealing.

Background

Modern high performance civilian aircraft employ slat seals to eliminate the gap between the leading edge slat and the fixed wing structure. The slat seal is typically mounted in a slot between the lower slat skin and the fixed leading edge to prevent airflow through the slot and to act as a pneumatic seal. The slat sealing element can enhance the smoothness of the aerodynamic surface, and can form pressure difference between the upper wing surface and the lower wing surface, thereby improving the flight performance of the airplane and saving fuel.

During flight of the aircraft, the leading-edge slats are retracted and lowered to adjust the aircraft critical angle of attack. When the slat is folded, the slat sealing element arranged on the inner layer of the slat is pressed by the fixed leading edge to generate larger deformation, and the sealing of the slot passage is realized by the resilience force generated by the compression of rubber. Because the slat sealing element is generally made of rubber materials, the sealing element is damaged due to large deformation in the process of being extruded for many times, and the flight safety of the airplane is threatened.

At present, most of common slat sealing elements on civil aircraft are olive-shaped sealing elements, and although the sealing elements can bear larger compression rate and have better sealing performance in the service process, airflow is uneven at the position due to the branch structure, and the maximum strain is very large in the deformation process. Other slat seals, such as "P-seals", are not able to be used stably on slats for long periods of time due to low tolerable compression rates and poor sealing properties. In order to meet the purpose of long-term reliable use of the slat sealing element on an airplane, the slat sealing element has the characteristics of high compression ratio, small deformation, good sealing performance, light weight and the like.

Disclosure of Invention

The invention aims to overcome the defects of the prior art and provide a lightweight civil aircraft slat sealing element, which solves the problems of overlarge deformation, heavy mass and the like of the traditional sealing element by combining the actual service condition of the slat sealing element.

The purpose of the invention is realized by the following technical scheme:

a light civil aircraft slat sealing element is characterized in that the sealing element comprises a strip-shaped clamping part, an inverted U-shaped bulge and an arc-shaped side wall; the convex part comprises a first side wall, an arc-shaped top end and a second side wall, the first side wall is connected with the second side wall through the arc-shaped top end, and the connection part of the first side wall and the second side wall is in smooth transition; the second side wall of the bulge part is connected with one end of the arc-shaped side wall, the joint of the second side wall and the arc-shaped side wall is in smooth transition, and the other end of the arc-shaped side wall is connected with the first side wall of the bulge part and the tail end of the strip-shaped clamping part respectively and is in smooth transition; the arc-shaped side wall and the convex part form a hollow area; the composite material strip is embedded in the middle of the strip-shaped clamping part.

Further, the composite material strips are made of carbon fiber composite materials.

Furthermore, the first side wall of the convex part is an arc surface which is concave towards the hollow area, and the curvature radius is 25-35 mm. The arc top end of the convex part is an arc surface which is convex towards the outside of the hollow area, and the curvature radius is 3-4 mm. The second lateral wall of bellying is "s" shape curved surface, and the curved surface that is close to the arc top is to the indent, and radius of curvature is between 25 ~ 35mm, and the curved surface of keeping away from the arc top is outwards protruding, and radius of curvature is between 25 ~ 35mm, rounding off between two curved surfaces.

Preferably, the included angle between the first side wall of the protruding part and the joint of the tail end of the strip-shaped clamping part is 90-160 degrees.

Preferably, the arc-shaped side wall is an arc surface protruding out of the hollow area, and the curvature radius is 20-25 mm. The included angle between the arc-shaped side wall and the first side wall of the protruding portion at the joint of the tail ends of the strip-shaped clamping portions is an acute angle.

Preferably, the wall thickness of the convex part and the wall thickness of the arc-shaped side wall are the same, and the wall thickness is 1.3-1.5 mm; the wall thickness of the strip-shaped clamping part is 3-4 mm.

Preferably, the slat sealing element is made of fabric rubber material, the inner side and the outer side of the sealing element are rubber layers, and the middle part of the sealing element is a fabric layer.

Compared with the existing slat sealing element, the invention has the following advantages and outstanding effects: when receiving under the slat skin and fixed leading edge's extrusion, bellying and arc lateral wall receive the extrusion force simultaneously and produce and warp, and the resilience force that produces through rubber compression afterwards realizes sealedly, and wherein the arc top of bellying can be at first with under the slat skin contact and take place to warp, along with the continuous increase of extrusion force, the arc top of bellying can outwards expand, makes the arc lateral wall fully contact with fixed leading edge realize sealedly simultaneously. Under the effect simultaneously of bellying and arc lateral wall, can realize that the slat slot is sealed, can bear 50% compression ratio simultaneously, solve traditional slat sealing member and warp greatly, the quality is heavy, can bear the compression ratio not high, and the centre gripping part is perishable, can't be for a long time the stable problem of using on the slat.

Drawings

Fig. 1 is a schematic perspective view of the present invention.

Fig. 2 is a front view of fig. 1.

Fig. 3 is a right side view of fig. 1.

In the figure: 10-a boss; 20-an arcuate sidewall; 30-a strip-shaped clamping part; 40-a hollow region; 101-a first side wall; 102-a curved tip; 103-a second side wall; 301-strips of composite material.

Detailed Description

Specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings. As shown in fig. 1, the lightweight civil aircraft slat sealing element of the present invention includes a strip-shaped clamping portion 30, an inverted "U" -shaped protruding portion 10, and an arc-shaped side wall 20; the boss comprises a first side wall 101, an arcuate tip 102 and a second side wall 103; the first side wall 101 is connected with the second side wall 103 through the arc-shaped top end 102, and the connection part is in smooth transition, wherein the first side wall 101 is an arc surface which is concave towards the hollow area 40, and the curvature radius is 25-35 mm; the arc top end 102 is an arc surface protruding outwards towards the hollow area 40, and the curvature radius is 3-4 mm; the second side wall 103 is an s-shaped curved surface, the curved surface close to the arc top end 102 is concave inwards, the curvature radius is 25-35 mm, the curved surface far away from the arc top end 102 is convex outwards, the curvature radius is 25-35 mm, and the two curved surfaces are in smooth transition. The second side wall 103 of the protruding portion 10 is connected to the arc-shaped side wall 20, and the included angle at the connection point is an acute angle and is in smooth transition. The arc-shaped side wall 20 is an arc surface protruding outwards the hollow area 40, the curvature radius is 20-25 mm, and the arc-shaped side wall 20 and the convex part 10 form the hollow area 40 in a surrounding mode. The included angle of the joint of the first side wall of the convex part and the tail end of the strip-shaped clamping part is 90-160 degrees. The arc-shaped side wall 20 is connected with the tail end of the strip-shaped clamping part 30, and the arc-shaped side wall 20 is intersected with the first side wall 101 of the bulge part 10 at the tail end of the strip-shaped clamping part 30, wherein the included angle is an acute angle. The strip clamp 30 is elongate with a strip of composite material 301 embedded in the middle, preferably of carbon fibre composite material, to reduce the mass of the overall slat seal. The wall thickness of the bulge part 10 is the same as that of the arc-shaped side wall 20, and the wall thickness is preferably 1.3-1.5 mm; the thickness of the strip-shaped clamping part 30 is preferably 3-4 mm. The slat sealing element is made of fabric rubber materials through extrusion of a die, the inner side and the outer side of the sealing element are rubber layers, and the middle of the sealing element is a fabric layer.

The composite material slat sealing element is arranged on a lower skin of a slat through a strip-shaped clamping portion 30, wherein the whole strip-shaped clamping portion 30 is connected with a clamping device through a rivet, and a composite material strip 301 in the strip-shaped clamping portion 30 is used for increasing the rigidity of the strip-shaped clamping portion so as to prevent the slat sealing element from falling off in a service process. During flight of the aircraft, the slats are stowed and deployed to adjust the critical angle of attack of the aircraft. The curved side wall 20 of the slat seal first contacts the fixed leading edge and undergoes compressive deformation as the slat is stowed. As the leading edge slat continues to retract, the compressive force increases and the curved tip 102 of the boss 10 expands outwardly until it contacts the slat lower skin. The convex part 10 and the arc-shaped side wall 20 are simultaneously extruded to generate deformation and are fully contacted with the lower skin and the fixed leading edge of the slat, and the slat gap is sealed by resilience force generated by rubber compression. Due to the existence of the convex part, the sealing element can bear 50% compression rate, the service life of the sealing element is greatly prolonged, and the manufacturing cost is low.

Claims

1. A lightweight civil aircraft slat sealing element, characterized in that it comprises a strip-shaped clamping portion (30), an inverted U-shaped raised portion (10) and an arcuate side wall (20); the bulge (10) comprises a first side wall (101), an arc-shaped top end (102) and a second side wall (103), wherein the first side wall (101) is connected with the second side wall (103) through the arc-shaped top end (102), and the connection part is in smooth transition; the second side wall (103) of the lug boss is connected with one end of the arc-shaped side wall (20) and the joint of the two side walls is in smooth transition, and the other end of the arc-shaped side wall (20) is connected with the first side wall (101) of the lug boss and the tail end of the strip-shaped clamping part (30) respectively and is in smooth transition; the arc-shaped side wall (20) and the convex part (10) enclose a hollow area (40); a composite material strip (301) is embedded in the middle of the strip-shaped clamping part (30);

the second side wall (103) of the convex part is an S-shaped curved surface, the curved surface close to the arc top end (102) is inwards concave, the curvature radius is 25-35 mm, the curved surface far away from the arc top end (102) is outwards convex, the curvature radius is 25-35 mm, and the two curved surfaces are in smooth transition.

2. A lightweight civil aircraft slat seal according to claim 1, characterised in that the composite material strips (301) are of carbon fibre composite material.

3. A lightweight civil aircraft slat seal according to claim 1, characterised in that the first side wall (101) of the raised portion is a cambered surface that is concave towards the hollow region (40), with a radius of curvature of between 25 and 35 mm.

4. A lightweight civil aircraft slat seal according to claim 1, characterised in that the curved apex (102) of the raised portion is a curved surface convex towards the hollow region (40), with a radius of curvature of between 3 and 4 mm.

5. A lightweight civil aircraft slat seal according to claim 1, characterised in that the angle at which the first side wall (101) of the raised portion joins the end of the strip-shaped retaining portion (30) is between 90 ° and 160 °.

6. A lightweight civil aircraft slat seal according to claim 1, characterised in that the curved side walls are convexly curved towards the hollow region (40), with a radius of curvature of between 20 and 25 mm.

7. A lightweight civil aircraft slat seal according to claim 1, characterised in that the angle between the curved side wall (20) and the first side wall (101) of the raised portion at the junction of the distal ends of the strip-shaped retaining portion (30) is acute.

8. A lightweight civil aircraft slat seal according to claim 1, characterised in that the raised portion (10) and the curved side wall (20) have the same wall thickness, the wall thickness being 1.3 to 1.5 mm; the wall thickness of the strip-shaped clamping part (30) is 3-4 mm.

9. A lightweight civil aircraft slat seal according to any of claims 1 to 8, wherein the slat seal is of fabric rubber material, with rubber layers on both the inside and outside of the seal, and a fabric layer in the middle of the seal.