阅读说明：本技术 一种复合材料转折梁结构 (Composite material turning beam structure ) 是由 巫大秀 林荣欣 张世全 于 2018-07-27 设计创作，主要内容包括：本申请公开了一种复合材料转折梁结构,涉及飞行器机翼机械技术领域。申请包括平直段和左右对称的后掠,所述平直段和后掠均包括上缘铺层、腹板和下缘铺层；所述上缘铺层、腹板和下缘铺层均是由若干层单向带碳纤维复合材料叠合在一起进行铺层的,叠合的角度为0o、-45o、+45o和90o。本申请提供了一种合理的复合材料转折梁的铺层形式,该铺层形式既能满足梁的力学性能,还能满足工艺的要求。(The application discloses combined material turning beam structure relates to aircraft wing machinery technical field. The application comprises a straight section and a left-right symmetrical sweep, wherein the straight section and the sweep respectively comprise an upper edge layer, a web plate and a lower edge layer; the upper edge layer, the web plate and the lower edge layer are all formed by stacking a plurality of layers of unidirectional carbon fiber composite materials with carbon fibers, and the stacking angles are 0 degrees, -45 degrees, +45 degrees and 90 degrees. The application provides a reasonable spreading form of a composite material turning beam, which can meet the mechanical property of the beam and the technological requirement.)

1. A composite material turning beam structure is characterized in that: the transverse-symmetry transverse-sweep combined structure comprises a straight section and a left-right-symmetry sweep, wherein the straight section and the sweep both comprise an upper edge layer, a web plate and a lower edge layer;

the upper edge layer is formed by overlapping a plurality of layers of unidirectional carbon fiber-containing composite materials, and the overlapping angles of the plurality of layers of unidirectional carbon fiber-containing composite materials are 0 degree, -45 degrees, +45 degrees and 90 degrees; the web is formed by overlapping a plurality of layers of unidirectional carbon fiber composite materials, and the overlapping angles are 0 degrees, -45 degrees, +45 degrees and 90 degrees; the lower edge laying layer is formed by stacking a plurality of layers of unidirectional carbon fiber composite materials, and the stacking angles are 0 degrees, -45 degrees, +45 degrees and 90 degrees.

2. A composite breakover beam structure according to claim 1, wherein: the upper edge layer at least comprises 10 layers of unidirectional carbon fiber composite materials with carbon fibers, which are laminated at a laminating angle of 0 degree.

3. A composite material breakover beam structure according to claim 1 or 2, wherein: the lower edge laying layer at least comprises 10 layers of unidirectional carbon fiber composite materials which are laminated at a laminating angle of 0 degree.

4. A composite material breakover beam structure according to claim 1 or 2, wherein: the upper edge layer is formed by sequentially laminating a layer of one-way ribbon carbon fiber composite material which is laminated at an angle of-45 degrees, a layer of one-way ribbon carbon fiber composite material which is laminated at an angle of 45 degrees, three layers of one-way ribbon carbon fiber composite materials which are laminated at an angle of 0 degree, a layer of one-way ribbon carbon fiber composite material which is laminated at an angle of 45 degrees, a layer of one-way ribbon carbon fiber composite material which is laminated at an angle of 90 degrees, a layer of one-way ribbon carbon fiber composite material which is laminated at an angle of-45 degrees, two layers of 0-degree laminated one-way ribbon carbon fiber composite materials, a layer of 45-degree laminated one-way ribbon carbon fiber composite material, a layer of 90-degree laminated one-way ribbon carbon fiber composite material, a layer of one-way ribbon carbon fiber composite material which is laminated at an angle of-45 degrees and.

Technical Field

The application relates to the technical field of aircraft wing machinery, in particular to a composite material turning beam structure.

Background

The weight of the aircraft affects the performance of the aircraft, and the structural weight of unmanned aerial vehicles is increasingly controlled and only accounts for 25% of the total weight of the aircraft. In order to meet the requirement of structural weight, the application of composite materials on airplanes is more and more prominent.

The beam is an important longitudinal force transmission component of the airplane airfoil and participates in transmitting loads such as bending moment, torque, shearing force and the like on the airfoil. The design and manufacture of straight composite beams is now mature, and the lay-up design of composite break beams at the break-over is not a successful precedent. The length of a certain composite material turning beam is 9100mm, the height of the beam is 60-280 mm, the shapes of the upper and lower edge strips are in a hyperboloid saddle shape, the cross section of the beam is Z-shaped, the included angles between the upper and lower edge strips and a web plate are variable, the web plate of the beam is turned twice, a middle straight section and a left-right symmetrical swept-back (9 degree) section are formed, and the shapes of parts are left-right symmetrical along a middle shaft (BL 0).

The state intellectual property office discloses a utility model patent of publication number CN204297055U, title "an whole spar structure" in 2015 year 4 month 29 days, and this utility model patent includes web (1), joining region (2), rim strip (3), transition region (4), the spar structure is whole lamination, web (1) is passed through joining region (2) and is connected with another web (1) in root and point portion orientation, rim strip (3) are in web (1) does not pass through with the both sides that joining region (2) link to each other transition region (4) with web (1) links to each other. The advantage that this application has is that bear and pass and carry efficient, fastener assembly quantity is few, simple process, advantage that production efficiency is high, makes the biography power of aircraft wing beam structure continuous, direct simultaneously, and has realized the assembly of box section and inside inspection through the design of web trompil to realized losing the heavy effect to a certain extent.

The beam is made of unidirectional carbon fiber composite materials, gaps or overlapping of the layers can be generated at the turning positions, a cut design is required, the angle and the area of the cut are related to the sweepback angle and the width of the edge strip of the beam, the processing of the layer and the cut of the turning area on the seam is complex, and the mechanical property of the beam can be influenced. At present, parts with turns of a web plate are generally made of carbon cloth, and turning parts made of unidirectional carbon fiber composite materials are still blank at home.

Disclosure of Invention

In order to overcome the defects and shortcomings in the prior art, the composite material turning beam structure is provided, and the invention aims to provide a reasonable paving form of the composite material turning beam, wherein the paving form can meet the mechanical property of the beam and the technological requirement.

In order to solve the defects in the prior art, the method is realized by the following technical scheme:

a composite material turning beam structure is characterized in that: the transverse-symmetry transverse-sweep combined structure comprises a straight section and a left-right-symmetry sweep, wherein the straight section and the sweep both comprise an upper edge layer, a web plate and a lower edge layer;

the upper edge layer is formed by stacking a plurality of layers of unidirectional carbon fiber composite materials together, and the stacked angles of the plurality of layers of unidirectional carbon fiber composite materials are 0 degree, -45 degrees, +45 degrees and 90 degrees; the web is formed by overlapping a plurality of layers of unidirectional carbon fiber composite materials, and the overlapping angles are 0 degrees, -45 degrees, +45 degrees and 90 degrees; the lower edge laying layer is formed by stacking a plurality of layers of unidirectional carbon fiber composite materials, and the stacking angles are 0 degrees, -45 degrees, +45 degrees and 90 degrees.

The upper edge layer at least comprises 10 layers of unidirectional carbon fiber composite materials with carbon fibers, which are laminated at a laminating angle of 0 degree.

The lower edge laying layer at least comprises 10 layers of unidirectional carbon fiber composite materials which are laminated at a laminating angle of 0 degree.

The upper edge layer is formed by sequentially laminating a layer of one-way ribbon carbon fiber composite material which is laminated at an angle of-45 degrees, a layer of one-way ribbon carbon fiber composite material which is laminated at an angle of 45 degrees, three layers of one-way ribbon carbon fiber composite materials which are laminated at an angle of 0 degree, a layer of one-way ribbon carbon fiber composite material which is laminated at an angle of 45 degrees, a layer of one-way ribbon carbon fiber composite material which is laminated at an angle of 90 degrees, a layer of one-way ribbon carbon fiber composite material which is laminated at an angle of-45 degrees, two layers of 0-degree laminated one-way ribbon carbon fiber composite materials, a layer of 45-degree laminated one-way ribbon carbon fiber composite material, a layer of 90-degree laminated one-way ribbon carbon fiber composite material, a layer of one-way ribbon carbon fiber composite material which is laminated at an angle of-45 degrees and.

Compared with the prior art, the beneficial technical effects brought by the application are shown in that:

1. the composite material is adopted to design the turning beam structure, the blank that the turning beam is made of the unidirectional carbon fiber composite material at home is filled, the design and manufacture requirements are ensured, and the design level of the composite material is greatly improved. In the application, the web pointing direction is an X axis, a Y axis is perpendicular to the X axis, the direction is downward, the superposition angle is relatively speaking relative to the X axis, the layering parameters refer to the layering angle and the layering sequence of the upper edge strip, the lower edge strip and the web of the composite material turning beam, +45 represents that the unidirectional tape is layered along the direction of anticlockwise rotation of the X axis by 45 degrees, -45 represents that the unidirectional tape is layered along the direction of clockwise rotation of the X axis by 45 degrees, 0 represents that the unidirectional tape is layered along the X axis, and 90 represents that the unidirectional tape is layered along the Y axis.

2. The composite material turning beam is made of a unidirectional carbon fiber composite material, and the most part of load transmission is borne by carbon fibers. When the laying design is carried out, the selection of the laying angle is necessary to be beneficial to the transmission of load to the maximum extent and is beneficial to controlling the deformation of the workpiece in the manufacturing process. Therefore, the composite material turning beam laying design selects three laying angles of 90 degrees, 0 degrees and +/-45 degrees. In addition, the composite material turning beam belongs to a component on the airplane wing, and participates in transferring load (including bending moment, shearing force and torque) on the wing, mainly transfers the bending moment in the 0-degree direction, mainly transfers the shearing force in the 90-degree direction, and mainly transfers the torque in the +/-45-degree direction. Therefore, when the laying design of the composite material turning beam is carried out, one of the three laying angles is not available.

3. The range and the area are determined when tearing off the certain layer in a plus 45-degree or minus 45-degree layering mode on the premise that the fibers of the unidirectional tape are not wrinkled, each fiber on the unidirectional tape is naturally attached to the surface of the attaching mold, and layering is carried out along the direction of the fibers; the position of the cut (the seam) is the position where the unidirectional tapes are overlapped when being laid.

4. As can be seen from the layer parameters of the upper edge layer, 0-degree layers close to 10 layers are arranged inside the upper edge layer, the proportion of the 0-degree layers in the layer is larger (up to 50 percent), and the 0-degree layers need to be provided with a shear opening at the turning position of the beam axis. When laid under the same coordinate reference, clipping occurs at the same location. If a 0 deg. layer of 10 layers is cut at the same location, the load-bearing capacity of the beam is greatly impaired. Therefore, the position of the cut needs to be changed by adjusting the reference of the overlay coordinates of each layer. During design, the differential laying, the laying mode and the splicing method of adjacent and close 0-degree layers are specified in detail.

Drawings

FIG. 1 is a schematic diagram of the overall structure of the present application;

FIG. 2 is a ply parameter graph of an upper edge ply in example 3 of the present application;

FIG. 3 is a schematic view of the construction of the flat section and swept back joint of the present application;

reference numerals: 1. a straight section 2, a sweep, 3, an upper edge layer, 4 web plates and 5 a lower edge layer.

Detailed Description