CN211568288U - Aircraft and composite material airfoil thereof - Google Patents

Abstract

An embodiment of the utility model provides an aircraft and combined material airfoil thereof. The composite airfoil includes: the skin-protecting frame comprises a framework, and an upper skin and a lower skin which are integrally formed with the framework; the upper skin is located above the framework, the lower skin is located below the framework, and the upper skin and the lower skin are both carbon fiber composite material skins. The utility model discloses an airfoil simple structure, rigidity are big, intensity is high, light in weight.

Description

Aircraft and composite material airfoil thereof

Technical Field

The utility model relates to an airfoil technical field of space flight vehicle's fuel tank especially indicates an aircraft and combined material airfoil thereof.

Background

The auxiliary fuel tank is a fuel tank which is hung below the fuselage or wing of the aerospace craft, is thick in the middle and has two sharp ends in a streamline shape. The auxiliary fuel tank is hung, so that the voyage and the endurance time of the airplane can be increased, and the auxiliary fuel tank can be thrown away when the airplane is in necessary air battle, so that the airplane can be put into battle with better maneuverability.

In addition to the non-disposable fuel reservoir designed to match the shape of the fuselage in the early days, the fuel reservoir has a streamlined exterior design as the main design direction, so as to reduce the generated drag, negatively affect the mobility and stability of the aircraft, and reduce the impact on other carrying equipment or fuselage structures when the fuel reservoir is separated from the aircraft. Some auxiliary fuel tanks have small fixed wing surfaces (stabilizing surfaces) at the tail for balancing, and the purpose of the auxiliary fuel tanks is to achieve the above purpose.

According to the scheme of the stabilizing surface metal skin stringer, the internal reinforcing stringer and the box are machined by milling, so that the weight is heavy, the rigidity is low, the assembly is complex, the quality consistency is difficult to guarantee, and the manufacturing period is long.

SUMMERY OF THE UTILITY MODEL

The utility model provides an aircraft and combined material airfoil thereof. Simple structure, high rigidity, high strength and light weight.

In order to solve the above technical problem, an embodiment of the present invention provides the following solutions:

a composite airfoil for an aircraft, comprising: the skin-protecting frame comprises a framework, and an upper skin and a lower skin which are integrally formed with the framework;

the upper skin is located above the framework, the lower skin is located below the framework, and the upper skin and the lower skin are both carbon fiber composite material skins.

Optionally, the scaffold has a plurality of linkers.

Optionally, each of the connectors has a plurality of through-penetrating connection holes.

Optionally, a fiber rib plate is arranged on the framework, and a plurality of fiber ribs are arranged on the fiber rib plate along the first direction.

Optionally, the fiber rib includes: a first fiber rib, a second fiber rib, a third fiber rib, and a fourth fiber rib;

the first fiber ribs, the second fiber ribs and the third fiber ribs are arranged at intervals along the first direction;

the fourth fiber rib is perpendicular to the first fiber rib, the second fiber rib and the third fiber rib, respectively.

Optionally, the second direction of the framework is provided with solid fiber ribs corresponding to the joints one by one, and the second direction intersects with the first direction to form a preset angle.

Optionally, the network formed by the solid fiber ribs and the fiber ribs in a crossed manner is filled with a foam material.

Optionally, the joints include a first joint, a second joint, and a third joint;

the plurality of solid fiber tendons comprises: the first solid fiber rib corresponding to the first joint, the second solid fiber rib corresponding to the second joint and the third solid fiber rib corresponding to the third joint.

Optionally, the number of the penetrating connecting holes is three, and the three penetrating connecting holes are distributed in a triangular shape; the preset angle is less than or equal to 90 degrees.

An embodiment of the utility model provides an aircraft is still provided, including the fuselage and with the airfoil that the fuselage is connected, its characterized in that, the airfoil is as above the combined material airfoil, the combined material airfoil passes through connect on the skeleton with fuselage fixed connection.

The above technical scheme of the utility model at least include following beneficial effect:

the utility model discloses an above-mentioned combined material airfoil of aircraft, include: the skin-protecting frame comprises a framework, and an upper skin and a lower skin which are integrally formed with the framework; the upper skin is located above the framework, the lower skin is located below the framework, and the upper skin and the lower skin are both carbon fiber composite material skins. Simple structure, high rigidity, high strength, light weight, low cost and quick manufacture.

Drawings

FIG. 1 is a frame diagram of a composite airfoil of the present invention;

FIG. 2 is a perspective view of the composite airfoil of the present invention;

FIG. 3 is a plan view of the composite airfoil of the present invention;

FIG. 4 is a plan view of the composite airfoil of the present invention;

FIG. 5 is a schematic of grid ribbing of a composite airfoil of the present invention;

fig. 6 is a perspective view of the grid reinforcement of the composite airfoil of the present invention.

Description of reference numerals:

30-a framework; 31-upper skin; 32-a lower skin;

11-a first joint; 12-a second linker; 13-a third linker;

21-a first solid fiber rib; 22-second solid fiber ribs; 23-a third solid fiber rib;

2-a penetrating connection hole;

3-a foam material;

41-fiber rib plate; 42-first fiber ribs; 43-second fiber ribs; 44-third fiber ribs; 45-fourth fiber ribs.

Detailed Description

Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

As shown in fig. 1-6, embodiments of the present invention provide a composite airfoil for an aircraft, comprising: a skeleton 30, and an upper skin 31 and a lower skin 32 integrally formed with the skeleton 30;

the upper skin 31 is located above the framework 30, the lower skin 32 is located below the framework 30, and both the upper skin 31 and the lower skin 32 are carbon fiber composite skins.

The full-composite-material integrally-formed high-rigidity airfoil comprises a variable-section composite-material grid framework 30, an upper composite material skin 31 and a lower composite material skin 32, and is integrally formed, so that a large number of connecting pieces are omitted, the assembly workload is effectively reduced, and the production efficiency is improved. The composite material skin adopts a compression molding manufacturing scheme, the middle framework adopts a one-way fiber laying preforming scheme, the molding efficiency is high, and the composite material skin is suitable for rapid manufacturing.

In an alternative embodiment of the present invention, the frame 30 has a plurality of joints, each joint having a penetrating attachment hole 2. The joint has a plurality of through-penetrating connection holes 2. The through-going connection holes may here be bolt holes. Optionally, three penetrating connection holes 2 are distributed in a triangular shape; this airfoil and fuselage adopt to be three-point type articulate, and every joint has 3 penetrability bolt holes 2, has 9 penetrability bolt holes 2 altogether, adopts bolt and fuselage firm connection, easily final assembly.

In an optional embodiment of the present invention, the skeleton 30 is provided with a fiber rib plate 11, and the fiber rib plate 41 is provided with a plurality of fiber rib plates along a first direction.

Optionally, the fiber rib includes: a first fiber rib 42, a second fiber rib 43, a third fiber rib 44, and a fourth fiber rib 45;

the first fiber ribs 42, the second fiber ribs 43 and the third fiber ribs 44 are arranged at intervals along the first direction;

the fourth fiber rib (45) is perpendicular to the first fiber rib (42), the second fiber rib (43), and the third fiber rib (44), respectively. Of course, the fourth fiber rib (45) is crossed with the first fiber rib (42), the second fiber rib (43) and the third fiber rib (44), and may be a predetermined angle, for example, the predetermined angle is less than or equal to 90 degrees, and may be greater than 90 degrees.

In an optional embodiment of the present invention, the frame 30 is provided with solid fiber ribs corresponding to the joints in a one-to-one manner in the second direction, and the second direction intersects with the first direction to form a predetermined angle. The preset angle is less than or equal to 90 degrees.

Optionally, the joints include a first joint 11, a second joint 12 and a third joint 13;

the plurality of solid fiber tendons comprises: a first solid fiber rib 21 corresponding to the first joint 11, a second solid fiber rib 22 corresponding to the second joint 12, and a third solid fiber rib 23 corresponding to the third joint 13.

The embodiment of the utility model provides an in, skeleton 30 can be variable cross section net adds the muscle skeleton, and variable cross section is as shown in FIG. 4, is the variable dimension structure of the non-uniform cross section of adaptation aerodynamic configuration, confirms by the product demand side.

In an alternative embodiment of the present invention, the solid fiber ribs and the fiber ribs cross to form a network, which is filled with a foam material 3. The grid is filled with the reinforced foam material, so that the weight is effectively reduced on the premise of ensuring high rigidity, and the weight is reduced by 50% compared with the traditional structure. The airfoil of the network structure is suitable for the transmission of concentrated force and bending moment at the joint of the airfoil and the machine body, and the airfoil is guaranteed not to be damaged under the action of transverse pneumatic large load.

The airfoil fiber directions here are: the predominant fiber direction was transverse to the airfoil, with a fiber volume content of 70% (direction a in fig. 1) and longitudinal fiber volume of 30% (direction B in fig. 1).

The above embodiment of the utility model the combined material airfoil wholly become by the variable cross section net with muscle skeleton, upper and lower compound material covering, whole integrated into one piece, simple structure effectively reduces assembly work load, improves production efficiency. Adopt co-curing integrated into one piece between skeleton and the upper and lower covering, set up 1 in interface department: 50 in the structure of the transition. The composite grid reinforcement and skin co-curing integrated forming technology is adopted inside (a large number of connecting pieces are saved), the grid is filled with the reinforcing foam, the weight is effectively reduced on the premise of ensuring high rigidity, and the weight is reduced by 50% compared with the traditional structure. High rigidity, high strength and light weight. The three solid fiber ribs of the framework structure are particularly suitable for the transmission of concentrated force and bending moment at the joint of the wing and the machine body, and the wing surface is not damaged under the action of large transverse pneumatic load. The composite material skin adopts a compression molding manufacturing scheme, the middle framework adopts a one-way fiber laying preforming scheme, the molding efficiency is high, the composite material skin is suitable for rapid manufacturing, and the cost is low. The connection interface is 9 penetrability bolt holes, simple to operate, easily final assembly.

An embodiment of the utility model provides an aircraft is still provided, including the fuselage and with the airfoil that the fuselage is connected, its characterized in that, the airfoil is as above the combined material airfoil, the combined material airfoil passes through joint on the skeleton 30 with fuselage fixed connection. The stable connection of the airfoil and the machine body is realized, and the final assembly is easy.

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 should also be regarded as the protection scope of the present invention.

Claims (10)

1. A composite airfoil for an aircraft, comprising: a skeleton (30) and an upper skin (31) and a lower skin (32) integrally formed with the skeleton (30);

the upper skin (31) is located above the framework (30), the lower skin (32) is located below the framework (30), and the upper skin (31) and the lower skin (32) are both carbon fiber composite skins.

2. The composite airfoil of the aircraft of claim 1 wherein the skeleton (30) has a plurality of joints.

3. The composite material airfoil of the aircraft as claimed in claim 2, characterized in that each of said joints has a plurality of through-penetrating connection holes (2).

4. The composite airfoil of the aircraft of claim 3, characterized in that the skeleton (30) is provided with a fiber rib (41), the fiber rib (41) being provided with a plurality of fiber ribs in a first direction.

5. The composite airfoil of the aircraft of claim 4, wherein the fiber rib comprises: a first fiber rib (42), a second fiber rib (43), a third fiber rib (44), and a fourth fiber rib (45);

the first fiber ribs (42), the second fiber ribs (43) and the third fiber ribs (44) are arranged at intervals along the first direction;

the fourth fiber rib (45) is perpendicular to the first fiber rib (42), the second fiber rib (43), and the third fiber rib (44), respectively.

6. The composite airfoil of the aircraft as claimed in claim 5, characterized in that the skeleton (30) is provided with solid fiber ribs in a one-to-one correspondence with the plurality of joints in a second direction, the second direction intersecting the first direction at a predetermined angle.

7. The composite airfoil of the aircraft as claimed in claim 6, characterized in that the network of solid fiber ribs and the fiber ribs crosswise is filled with a foam material (3).

8. The composite airfoil of the aircraft of claim 6,

the joints comprise a first joint (11), a second joint (12) and a third joint (13);

the plurality of solid fiber tendons comprises: a first solid fiber rib (21) corresponding to the first joint (11), a second solid fiber rib (22) corresponding to the second joint (12), and a third solid fiber rib (23) corresponding to the third joint (13).

9. The composite airfoil of the aircraft as claimed in claim 6, characterised in that the number of through-penetrating attachment holes (2) is three, distributed triangularly; the preset angle is less than or equal to 90 degrees.

10. An aircraft comprising a fuselage and an airfoil connected to the fuselage, characterized in that the airfoil is a composite airfoil according to any one of claims 1 to 9, which is fixedly connected to the fuselage by means of a joint on the skeleton (30).

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