阅读说明：本技术 一种低成本的全复材飞机结构及其制作方法 (Low-cost full-composite aircraft structure and manufacturing method thereof ) 是由 孔德拴 苏昊 侯学佳 胡振球 李仁鹏 谢恺 龚地灵 于 2020-05-26 设计创作，主要内容包括：本发明公开了一种低成本的全复材飞机结构及其制作方法,主要包括平板件及设置在平板件上下两侧端面上的蒙皮,所述平板件主要包括芯材及分别复合设置在芯材上下两侧的铺层；所述平板件的上下两侧端面上分别设置有向内凹陷的第一凹槽和第二凹槽,平板件的上端面通过部分设置在第一凹槽内的第一胶接层与上蒙皮固定连接,平板件的下端面通过设置在第二凹槽内的第二胶接层与下蒙皮固定连接；所述平板件的上侧外壁上设置有采用湿法铺贴设置在平板件与第一胶接层之间的第一胶线层,平板件的下侧外壁上设置有采用湿法铺贴设置在平板件与下蒙皮之间的第二胶线层；具有无需制造零件模具,只需要简单的平板工装就可以完成大板的制造,节省了制造成本等特点。(The invention discloses a low-cost full-composite aircraft structure and a manufacturing method thereof, and the low-cost full-composite aircraft structure mainly comprises a flat piece and skins arranged on the upper and lower end faces of the flat piece, wherein the flat piece mainly comprises a core material and layers which are respectively and compositely arranged on the upper and lower sides of the core material; the upper end face and the lower end face of the flat plate piece are respectively provided with a first concave groove and a second concave groove which are inwards concave, the upper end face of the flat plate piece is fixedly connected with the upper skin through a first glue joint layer which is partially arranged in the first concave groove, and the lower end face of the flat plate piece is fixedly connected with the lower skin through a second glue joint layer which is arranged in the second concave groove; a first adhesive tape layer which is paved and adhered between the flat plate piece and the first adhesive tape layer by adopting a wet method is arranged on the outer wall of the upper side of the flat plate piece, and a second adhesive tape layer which is paved and adhered between the flat plate piece and the lower skin by adopting the wet method is arranged on the outer wall of the lower side of the flat plate piece; the method has the characteristics that the manufacture of the large plate can be completed only by a simple flat plate tool without manufacturing a part die, the manufacturing cost is saved, and the like.)

1. The utility model provides a low-cost full-composite aircraft structure which characterized in that: the composite plate mainly comprises a plate piece and skins vertically arranged on the end faces of the upper side and the lower side of the plate piece, wherein the plate piece mainly comprises a core material and layers which are respectively and compositely arranged on the upper side and the lower side of the core material; the upper end face and the lower end face of the flat plate piece are respectively provided with a first concave groove and a second concave groove which are inwards concave, the upper end face of the flat plate piece is fixedly connected with the upper skin through a first glue joint layer which is partially arranged in the first concave groove, and the lower end face of the flat plate piece is fixedly connected with the lower skin through a second glue joint layer which is arranged in the second concave groove; be provided with on the upside outer wall of dull and stereotyped spare and adopt the wet process to spread the first adhesive tape layer of pasting setting between dull and stereotyped spare and first cementing layer, be provided with on the downside outer wall of dull and stereotyped spare and adopt the wet process to spread the second adhesive tape layer of pasting setting between dull and stereotyped spare and lower covering.

2. The full-composite aircraft structure according to claim 1, wherein: first splice the layer including set up in first recess splice the layer and with interior splice layer integral type is connected and is set up at last covering and the outer layer that splices between the interior layer that splices, be provided with first enhancement on the link terminal surface on dull and stereotyped spare and the outer layer that splices.

3. The full-composite aircraft structure according to claim 2, wherein: and a second reinforced adhesive layer is arranged on the connecting end surface of the flat plate piece and the lower skin.

4. The full-composite aircraft structure according to claim 1, wherein: the depth of the first groove and the depth of the second groove are both 5-10 mm.

5. A method of fabricating a fully composite aircraft structure according to any one of claims 1 to 4, wherein: the method comprises the following steps:

(1) designing a core material according to the joint position and the design typesetting of the flat plate part, wherein the opening of the core material is 0.05mm larger than the size of the embedded part, and positioning the opening position according to the design typesetting; designing a laying layer according to a laying scheme and design typesetting of the flat plate part, wherein the laying layer comprises reinforcing layers designed on the upper surface and the lower surface of the embedded part, the size of each reinforcing layer is 25mm larger than that of the embedded part, and the position of each reinforcing layer is positioned according to the design typesetting;

(2) manufacturing a large plate by paving and pasting core materials and layers designed according to requirements according to a composite material part manufacturing method;

(3) designing the size of a large plate according to the specific width of the prepreg and the size of a flat plate tool, reasonably typesetting flat plate pieces on the large plate, fully utilizing the large plate as far as possible, and keeping the spacing between parts to be two times of the cutting knife seam width at the minimum to finish the design and typesetting;

(4) cutting a flat plate piece on the large plate with the designed typesetting by adopting a water cutting or composite material machine cutting method;

(5) slotting the upper and lower end faces of the flat plate piece, wherein the depth of the slot is 5-10 mm;

(6) one side of the flat plate piece is pre-positioned and glued on the upper skin by adopting a first gluing layer, and a first glue line layer is arranged between the flat plate piece and the first gluing layer by adopting a wet method;

(7) and paving a second adhesive layer on the other side of the flat plate piece by adopting a wet method, and gluing the other end of the flat plate piece on the lower-layer skin by virtue of the second adhesive layer.

6. The method of manufacturing according to claim 5, wherein: positioning holes are arranged on the core material and the laying layer, and the positioning holes are used as reference standards in core material design, laying layer design and typesetting design.

Technical Field

The invention belongs to the field of research and development and manufacturing of complete airplanes, particularly relates to a low-cost full-composite airplane structure and a manufacturing method thereof, and particularly relates to structural design and manufacturing of a concept verification machine for small and light airplanes.

Background

Aircraft design is generally divided into three stages, concept design, preliminary design and detailed design. For risk and cost reasons, small and light aircraft usually make a concept verification machine in the concept design stage, and carry out flight tests after completing necessary static tests, so as to verify the aerodynamic performance, overall parameters, structural strength, system functions and performance of the aircraft proposed in the concept design stage, and additionally, to verify some new technologies, novel and unique designs, new manufacturing technologies or new materials and the like. Therefore, design problems can be exposed at the initial stage of model research and development, the technical maturity of a new technology is evaluated, the design risk is avoided, and data support is provided for technical decision and optimization improvement in the initial design and detailed design stages.

Since the period of the concept design phase is generally short and many of the design solutions and manufacturing techniques proposed in the concept design phase are optimized and modified, it is required that the manufacturing of the concept verifier should be as low cost, efficient and easy to modify as possible. The existing aircraft composite structure manufacturing technology requires that a large number of paving dies are manufactured before parts are produced, and each composite part with a three-dimensional geometric shape corresponds to one paving die. The manufacturing cost of the part die is often much larger than that of a single part, and the cost of modification is large and the manufacturing efficiency is low. If the structure is changed subversively, the mould is redesigned and produced. The development of the general-purpose airplane requires short period, low cost, prominent technical bright point and the like, so the existing airplane composite material structure manufacturing technology cannot adapt to the increasingly strong market requirement of the general-purpose airplane.

Disclosure of Invention

The invention aims to solve the technical problems that aiming at the defects of the prior art, the invention provides the full-composite aircraft structure which is low in cost, high in efficiency and easy to change and the manufacturing method thereof.

The invention aims to complete the low-cost full-composite aircraft structure by adopting the following technical scheme, and the low-cost full-composite aircraft structure mainly comprises a flat plate piece and skins vertically arranged on the upper side end face and the lower side end face of the flat plate piece, wherein the flat plate piece mainly comprises a core material and layers which are respectively and compositely arranged on the upper side and the lower side of the core material; the upper end face and the lower end face of the flat plate piece are respectively provided with a first concave groove and a second concave groove which are inwards concave, the upper end face of the flat plate piece is fixedly connected with the upper skin through a first glue joint layer which is partially arranged in the first concave groove, and the lower end face of the flat plate piece is fixedly connected with the lower skin through a second glue joint layer which is arranged in the second concave groove; be provided with on the upside outer wall of dull and stereotyped spare and adopt the wet process to spread the first adhesive tape layer of pasting setting between dull and stereotyped spare and first cementing layer, be provided with on the downside outer wall of dull and stereotyped spare and adopt the wet process to spread the second adhesive tape layer of pasting setting between dull and stereotyped spare and lower covering.

Further, first glue the layer including setting up the interior glue that splices in first recess and with interior glue layer integral type and connect and set up the outer glue that connects between last covering and interior glue layer and connect the layer, be provided with first enhancement glue the layer on the link terminal surface on dull and stereotyped spare and the outer glue layer of splicing.

And further, a second reinforced adhesive layer is arranged on the connecting end surface of the flat plate piece and the lower skin.

Furthermore, the groove depth of the first groove and the second groove is 5-10 mm.

A method for manufacturing a full-composite aircraft structure comprises the following steps:

(1) designing a core material according to the joint position and the design typesetting of the flat plate part, wherein the opening of the core material is 0.05mm larger than the size of the embedded part, and positioning the opening position according to the design typesetting; designing a laying layer according to a laying scheme and design typesetting of the flat plate part, wherein the laying layer comprises reinforcing layers designed on the upper surface and the lower surface of the embedded part, the size of each reinforcing layer is 25mm larger than that of the embedded part, and the position of each reinforcing layer is positioned according to the design typesetting;

(2) manufacturing a large plate by paving and pasting core materials and layers designed according to requirements according to a composite material part manufacturing method;

(3) designing the size of a large plate according to the specific width of the prepreg and the size of a flat plate tool, reasonably typesetting flat plate pieces on the large plate, fully utilizing the large plate as far as possible, and keeping the spacing between parts to be two times of the cutting knife seam width at the minimum to finish the design and typesetting;

(4) cutting a flat plate piece on the large plate with the designed typesetting by adopting a water cutting or composite material machine cutting method;

(5) slotting the upper and lower end faces of the flat plate piece, wherein the depth of the slot is 5-10 mm;

(6) one side of the flat plate piece is pre-positioned and glued on the upper skin by adopting a first gluing layer, and a first glue line layer is arranged between the flat plate piece and the first gluing layer by adopting a wet method;

(7) and paving a second adhesive layer on the other side of the flat plate piece by adopting a wet method, and gluing the other end of the flat plate piece on the lower-layer skin by virtue of the second adhesive layer.

Furthermore, positioning holes are formed in the core material and the laying layer, and the positioning holes are used as reference standards in core material design, laying layer design and typesetting design.

The invention has the beneficial technical effects that: the manufacturing of the large plate can be completed only by a simple flat plate tool without manufacturing a part die, so that the manufacturing cost is greatly saved; by adopting a water cutting or conventional machining method, parts are quickly machined on the large plate, so that the manufacturing efficiency of the parts is greatly improved; due to the adoption of the flat plate, when the design of the structure is changed, only a large plate needs to be paved again, or a new part is directly added on the original large plate, a mould does not need to be changed, and the design change flow is greatly simplified; the part flanging (wet paving) manufactured by the scheme is solidified and formed along with the actual part appearance, the thickness of the adhesive layer can be well controlled, the gluing quality is improved, and therefore the development progress and the quality of the whole concept design stage are greatly improved.

Drawings

FIG. 1 is a schematic diagram of the design and layout of the large panel according to the present invention;

FIG. 2 is a schematic design of a core material according to the present invention;

FIG. 3 is a schematic design of a ply according to the invention;

fig. 4 is a structural schematic diagram of the gluing of the plate member according to the present invention.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more clearly understood by those skilled in the art, the present invention is further described with reference to the accompanying drawings and examples.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "left", "right", "inside", "outside", "lateral", "vertical", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description of the present invention, and do not indicate or imply that the device or element referred to must have a specific orientation, and thus, should not be construed as limiting the present invention.

The design and manufacture technology of the flat plate part simplifies all internal parts of the airplane except skin, such as a fuselage stringer, a clapboard, a floor structure, a wing shearing beam, a rib and the like, into the flat plate part so as to save the design link and the manufacture cost of a part mould, greatly improve the manufacture efficiency of the part, facilitate the design and the change of the flat plate part and simplify the design and the change process of the structure. The flat plate part gluing design and manufacture technology is a connecting technology of composite material structures, and is a simple, easy and controllable part assembling and manufacturing technology which can glue all flat plate parts on a skin structure, can well control the thickness of a glue layer and manufacture turned edges of parts.

As shown in fig. 1-4, the low-cost full-composite aircraft structure of the present invention mainly comprises a flat plate member 1 and skins vertically disposed on the upper and lower end surfaces of the flat plate member 1, wherein the flat plate member 1 mainly comprises a core material 2 and plies 3 respectively disposed on the upper and lower sides of the core material 2 in a composite manner; the upper side end face and the lower side end face of the flat plate member 1 are respectively provided with a first groove 11 and a second groove 12 which are sunken inwards, and the groove depths of the first groove 11 and the second groove 12 are both 5-10 mm; the upper end face of the flat plate member 1 is fixedly connected with the upper skin 4 through a first adhesive layer 5 partially arranged in the first groove 11, and the lower end face of the flat plate member 1 is fixedly connected with the lower skin 7 through a second adhesive layer 6 arranged in the second groove 12; a first adhesive tape layer 8 which is paved and adhered between the flat plate member 1 and the first adhesive layer 5 by a wet method is arranged on the outer wall of the upper side of the flat plate member 1, and a second adhesive tape layer 9 which is paved and adhered between the flat plate member 1 and the lower skin 7 by the wet method is arranged on the outer wall of the lower side of the flat plate member 1; the first glue line layer 8 and the second glue line layer 9 which are laid by the wet method are used for manufacturing flanges for flat pieces so as to increase the gluing area, and the specific appearance of the first glue line layer and the second glue line layer is manufactured according to the actual appearance of the skin so as to better control the thickness of the glue lines.

Referring to fig. 4, the first adhesive layer 5 includes an inner adhesive layer 51 disposed in the first groove 11 and an outer adhesive layer 52 integrally connected to the inner adhesive layer 51 and disposed between the upper skin 4 and the inner adhesive layer 51, and a first reinforcing adhesive layer 53 is disposed on an end surface of the connection end of the flat plate 1 and the outer adhesive layer 52; and a second reinforced adhesive layer 61 is arranged on the connecting end surface of the flat plate member 1 and the lower skin 7.

A method for manufacturing a full-composite aircraft structure comprises the following steps:

(1) designing a core material 2 according to the joint position and the design typesetting of the flat plate part 1, wherein the opening of the core material is 0.05mm larger than the size of the embedded part, and positioning the opening position according to the design typesetting; designing a laying layer 3 according to a laying scheme and design typesetting of the flat plate part 1, wherein the laying layer comprises reinforcing layers designed on the upper surface and the lower surface of an embedded part, the size of each reinforcing layer is 25mm larger than that of the embedded part, and the position of each reinforcing layer is positioned according to the design typesetting; the core material 2 is designed to be embedded with a hard point of a laminated board for installing a standard part, and the size of the hard point is 0.1mm smaller than that of an opening of the core material; the design requirements of the core material 2 and the ply 3 are determined according to the design and the typesetting of the flat plate 1;

(2) the core material 2 and the layer 3 which are designed according to requirements are paved and pasted according to the composite material part to manufacture the large board 10;

(3) designing the size of a large plate 10 according to the specific width of the prepreg and the size of a flat plate tool, reasonably typesetting the flat plate piece 1 on the large plate 10, fully utilizing the large plate 10 as far as possible, and keeping the spacing between parts to be two times of the cutting knife seam width at the minimum to finish the design and typesetting;

(4) cutting a flat plate part 1 on the large plate 10 with the designed typesetting by adopting a water cutting or compound material machine cutting method;

(5) slotting the upper and lower end faces of the flat plate member 1, wherein the depth of the slot is 5-10 mm;

(6) one side of the flat plate member 1 is pre-positioned and glued on the upper skin 4 by adopting a first gluing layer 5, and a first glue line layer 8 is arranged between the flat plate member 1 and the first gluing layer 5 by adopting a wet method;

(7) a second glue line layer 9 is laid on the other side of the flat plate member 1 by a wet method, and the other end of the flat plate member 1 is glued on the lower skin 7 through a second glue line layer 6.

Referring to fig. 1 to 3, positioning holes 13 are formed in the core material 2 and the ply 3, the positioning holes 13 are used as reference standards in core material design, ply design and layout design, and the positioning holes 13 are standard holes for designing and layout, core material design and ply design.

According to the manufacturing method, a part die does not need to be manufactured, and the large plate can be manufactured only by a simple flat plate tool, so that the manufacturing cost is greatly saved; by adopting a water cutting or conventional machining method, parts are quickly machined on the large plate, so that the manufacturing efficiency of the parts is greatly improved; due to the adoption of the flat plate, when the design of the structure is changed, only a large plate needs to be paved again, or a new part is directly added on the original large plate, a mould does not need to be changed, and the design change flow is greatly simplified; the part flanging (wet paving) manufactured by the scheme is solidified and formed along with the actual part appearance, the thickness of the adhesive layer can be well controlled, the gluing quality is improved, and therefore the development progress and the quality of the whole concept design stage are greatly improved.

The specific embodiments described herein are merely illustrative of the principles and utilities of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or change the above-mentioned embodiments without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which can be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.