CN108216570B

CN108216570B - Main wing surface structure of high aspect ratio wing

Info

Publication number: CN108216570B
Application number: CN201711340922.7A
Authority: CN
Inventors: 徐荣欣; 杨军; 刘健; 孔斌; 刘衍腾; 常楠
Original assignee: Avic Chengdu Uav System Co ltd
Current assignee: Avic Chengdu Uav System Co ltd
Priority date: 2017-12-14
Filing date: 2017-12-14
Publication date: 2023-08-18
Anticipated expiration: 2037-12-14
Also published as: CN108216570A

Abstract

The invention relates to a main wing surface structure of a high aspect ratio wing, and belongs to the field of aviation. The honeycomb sandwich upper wall plate 1 is of a carbon fiber composite material inner and outer panel and light paper honeycomb co-curing forming sandwich structure. The cap-shaped reinforced lower wall plate 2 is of a cap-shaped reinforced structure formed by integrally solidifying a carbon fiber composite material skin and a foam core. The box main beam 3 is an integrated structure formed by gluing and co-curing carbon fiber composite materials. The rear wall 4, the front edge skin 5 and the ribs 6 are of a carbon fiber composite material pressing plate structure. The adhesive 7 is a paste-like adhesive cured at normal temperature. According to the bearing characteristics of each component, the corresponding structural form is adopted, the weight reduction advantage of the composite material is fully exerted, and the contradiction between high bearing and light weight of the main wing surface structure of the large-aspect-ratio wing is effectively solved.

Description

Main wing surface structure of high aspect ratio wing

Technical Field

The invention belongs to the field of aviation, and particularly relates to a main wing surface structure of a high aspect ratio wing.

Background

Because of the harsh requirements on range, endurance and economy, long-endurance unmanned aerial vehicles generally employ high aspect ratio wings to obtain a large lift-drag ratio. The main wing surface structure is a main bearing structure of the high aspect ratio wing, and is used for bearing local aerodynamic load and transmitting total bending moment and torque of the whole aircraft. In order to further increase voyage and extend endurance, the structural weight is required to be as light as possible. High load and light weight are a pair of contradictions, which bring difficulty to structural design. For a middle-low-speed high-aspect-ratio unmanned aerial vehicle, the wing is generally in a beam type thin skin structure, and the upper skin and the lower skin of the wing are thinner and are mainly used for pneumatic dimension; the main beams are mostly I-shaped beams and are used for transmitting overall bending moment and shearing force; the upper and lower skins and the internal skeletons are generally assembled into a whole by mechanical connection, see fig. 1. This form is mature, but suffers from the following drawbacks:

(1) The high aspect ratio wing has the stress characteristics that the upper surface is severely stressed and the lower surface is mainly pulled, the stability problem of the upper skin is outstanding, the thin skin has poor shape maintaining effect, more ribs are required for collecting pneumatic load and auxiliary shape maintaining, and great weight cost is paid;

(2) The wing box formed by the I-shaped main beam and the thin skin has poor torsion resistance and is not beneficial to torque transmission;

(3) The mechanical connection assembly form has low integration level, large assembly workload, long period and high cost, and a large number of connecting pieces occupy a large amount of weight.

Disclosure of Invention

The technical scheme is as follows:

the main wing surface structure of the high aspect ratio wing consists of a honeycomb interlayer upper wall plate (1), a cap-shaped reinforced lower wall plate (2), a box-type main beam (3), a rear wall (4), a front edge skin (5), ribs (6) and an adhesive (7), wherein the honeycomb interlayer upper wall plate (1) is a sandwich structure formed by co-curing carbon fiber composite material inner and outer panels and light paper honeycomb; the cap-shaped reinforced lower wall plate (2) is of a cap-shaped reinforced structure formed by integrally solidifying a carbon fiber composite material skin and a foam core.

The honeycomb interlayer upper wall plate (1), the cap-shaped reinforced lower wall plate (2) and the inner framework are integrally bonded and assembled by adopting an adhesive (7).

The box type main beam (3) is of an integrated structure formed by cementing and co-curing carbon fiber composite materials; the rear wall (4), the front edge skin (5) and the ribs (6) are of a carbon fiber composite material pressing plate structure.

The adhesive (7) is a paste adhesive cured at normal temperature.

Technical effects and advantages

(1) The honeycomb sandwich upper wall plate has the characteristics of high bending rigidity and light weight, and is beneficial to improving the compression stability and the dimensional effect of the upper airfoil surface;

(2) The lower wall plate mainly bears tensile load, so that the dimensional effect can be increased by adopting a cap-shaped reinforcement structure, and the weight reduction advantage of the thin composite material skin can be fully exerted;

(3) The better dimensional capacity of the upper wall plate and the lower wall plate can greatly reduce the number of ribs and the weight of the structure;

(4) The box-type main beam is integrally formed by co-curing, is used for bearing most of total bending moment, torque and shearing force, and has good bending and torsion resistance;

(5) The full-cementing assembly mode improves the structural integration level, reduces the assembly workload, is beneficial to shortening the development period, reduces the cost and further reduces the weight;

(6) According to the bearing characteristics of each component, the corresponding structural form is adopted, the weight reduction advantage of the composite material is fully exerted, and the contradiction between high bearing and light weight of the main wing surface structure of the large-aspect-ratio wing is effectively solved.

Drawings

FIG. 1 is a schematic diagram of a main wing surface structure of a traditional middle-low speed large aspect ratio unmanned aerial vehicle wing;

FIG. 2 is a cross-sectional view of a main airfoil of a high aspect ratio wing of the present invention;

FIG. 3 is a schematic view of a high aspect ratio airfoil of the present invention;

FIG. 4 is a schematic view of an assembly of a main airfoil of a high aspect ratio wing of the present invention;

FIG. 5 is a final schematic of the assembled high aspect ratio wing main wing panel structure of the present invention.

In the figure, the upper wall plate of the 1-honeycomb interlayer, the lower wall plate of the 2-cap-shaped reinforced rib, the 3-box type main beam, the 4-rear wall, the 5-front edge skin, the 6-rib and the 7-adhesive are shown;

Detailed Description

The main wing surface structure of the large-aspect-ratio wing is recommended to manufacture and assemble parts according to the following steps, and the parts are shown in fig. 4 and 5:

(1) The components are solidified and formed respectively;

(2) The box main beam 3, the rear wall 4, the front edge skin 5 and the ribs 6 are assembled into an internal integral framework through a tool;

(3) Uniformly coating an adhesive 7 on the upper surface of the inner integral framework, and finishing the bonding with the honeycomb sandwich upper wall plate 1 in the construction period of the adhesive 7;

(4) Uniformly coating an adhesive 7 on the lower surface of the inner integral framework, and finishing the bonding with the cap-shaped reinforced lower wall plate 2 in the construction period of the adhesive 7;

(5) And applying contact pressure required by curing the adhesive through a tooling clamping plate or a die assembly, and waiting for the adhesive to finish curing.

Claims

1. The utility model provides a high aspect ratio wing main wing face structure, comprises honeycomb intermediate layer upper wall board (1), cap type stiffened lower wall board (2), box girder (3), back wall (4), leading edge covering (5), rib (6) and gluing agent (7), its characterized in that: the honeycomb interlayer upper wall plate (1) is a carbon fiber composite material inner and outer panel and a light paper honeycomb co-curing forming sandwich structure; the novel reinforced rib type steel plate is characterized in that the cap-shaped reinforced rib lower wall plate (2) is of a carbon fiber composite material skin and foam core integrally cured and formed into a cap-shaped reinforced structure, the box-type main beam (3), the rear wall (4), the front edge skin (5) and the ribs (6) are assembled into an inner framework through a tool, and the honeycomb interlayer upper wall plate (1), the cap-shaped reinforced rib lower wall plate (2) and the inner framework are assembled through integral gluing by adopting an adhesive (7).

2. A high aspect ratio wing main wing structure according to claim 1, wherein: the box type main beam (3) is of an integrated structure formed by cementing and co-curing carbon fiber composite materials; the rear wall (4), the front edge skin (5) and the ribs (6) are of a carbon fiber composite material pressing plate structure.

3. A high aspect ratio wing main wing structure according to claim 1, wherein: the adhesive (7) is a paste adhesive cured at normal temperature.