Composite cylindrical fuselage of light sports aircraft

Abstract

The invention provides a composite cylindrical fuselage of a light sports aircraft. Comprising a frame I (1), a top reinforcer (2), a frame II (3), a frame III (4) and a frame IV (5) which are arranged from front to back along the course of an aircraft, the frame I (1), the top reinforcer (2), the frame II (3), the frame III (4) and the frame IV (5) are connected with the skin (6) through secondary glue joint to form an integral structure; wherein the frame I (1) is located at the position of a nose, a cockpit is arranged between the frame I (1) and the frame II (3), a fuselage rear section is arranged between the frame II (3) and the frame III (4), and a vertical tail is arranged behind the frame III (4); and the top of the cockpit is reinforced by the top reinforcer (2). The invention has the characteristics of high structural efficiency and low manufacturing and assembling cost.

Description

Technical Field

[0001] This invention belongs to the field of aircraft structural configuration design technology, and specifically relates to a composite material cylindrical fuselage for a light sport aircraft. Background Technology

[0002] The existing fuselage structure of light sport aircraft adopts a conventional design, and the structure is mainly composed of skin, longitudinal beams and frames.

[0003] Since the fuselage structure of conventional light sport aircraft is usually composed of skin, longitudinal beams and frames, this design configuration often has a series of problems such as a large number of fuselage configurations, increased weight, and high cost. It cannot meet the current requirements of "low cost and easy installation and disassembly" for light sport aircraft, which greatly reduces the practicality of light sport aircraft. Summary of the Invention

[0004] The purpose of this invention is to provide a composite material cylindrical fuselage for a lightweight sport aircraft. This invention features high structural efficiency and low manufacturing and assembly costs.

[0005] Technical Solution. A composite material cylindrical fuselage for a light sport aircraft includes a frame I, a top reinforcing member, a frame II, a frame III, and a frame IV arranged from front to rear along the aircraft's flight path; the frame I, top reinforcing member, frame II, frame III, and frame IV are connected into an integral structure by secondary bonding and skinning; wherein, the frame I is located at the nose position, the cockpit is between the frames I and II, the rear fuselage is between the frames II and III, and the vertical tail is located behind the frame III; the top of the cockpit is reinforced by the top reinforcing member.

[0006] In the aforementioned lightweight sport aircraft composite cylindrical fuselage, the I frame is a glass fiber foam sandwich structure, which is connected to the skin through secondary adhesive bonding.

[0007] In the aforementioned lightweight sport aircraft composite cylindrical fuselage, the top reinforcement is a carbon fiber laminate structure, which is connected to the skin through secondary adhesive bonding.

[0008] In the aforementioned lightweight sport aircraft composite cylindrical fuselage, the II frame is a carbon fiber laminate structure, which is connected to the skin through secondary bonding.

[0009] In the aforementioned lightweight sport aircraft composite cylindrical fuselage, frame III is a glass fiber foam sandwich structure, which is connected to the skin through secondary adhesive bonding.

[0010] In the aforementioned lightweight sport aircraft composite cylindrical fuselage, frame IV is a glass fiber foam sandwich structure, which is connected to the skin through secondary bonding.

[0011] In the aforementioned lightweight sport aircraft composite cylindrical fuselage, the skin is a glass fiber foam sandwich structure, divided into left and right skins by a symmetrical central plane, and connected to frame I, top reinforcement, frame II, frame III, and frame IV by secondary adhesive bonding.

[0012] In the aforementioned composite material cylindrical fuselage of the light sport aircraft, the skin of the vertical tail section is integrated with the skin of the cylindrical fuselage.

[0013] Beneficial effects: 1) Compared with the traditional frame-beam fuselage structure of light sport aircraft, the number of parts in this invention can be reduced by about 17%, the structure is simple and the number of parts is small.

[0014] 2) Compared with the traditional frame-beam fuselage structure of light sport aircraft, the weight of the fuselage structure of the present invention can be reduced by at least about 8%, which has a significant weight reduction effect and improves structural efficiency; 3) Compared with the traditional frame-beam fuselage structure of light sport aircraft, the present invention reduces costs by about 30%, thereby reducing the total life cycle cost of the aircraft.

[0015] In summary, this invention provides a composite cylindrical fuselage structure for light sport aircraft with high structural efficiency and low manufacturing and assembly costs. Compared with the traditional frame-beam fuselage structure for light sport aircraft, it can significantly reduce the number of parts, reduce structural weight, and lower aircraft costs. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. The drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 It is a composite material cylindrical fuselage structure arrangement; Figure 2 This is a schematic diagram of the assembly of a composite material cylindrical fuselage structure. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0020] In the description of this invention, it should be noted that the directions or positional relationships indicated by terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" are based on the directions or positional relationships shown in the accompanying drawings and are only for the convenience of describing and simplifying the invention, and should not be construed as limiting the invention. Furthermore, the use of ordinal numbers (e.g., "first and second," etc.) is for distinguishing objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0021] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly, encompassing both direct connection and indirect connection via an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0022] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0023] The present invention will be further described in detail below with reference to the embodiments and accompanying drawings, but the embodiments of the present invention are not limited thereto.

[0024] Example 1. A composite material cylindrical fuselage for a light sport aircraft, see [link to example]. Figures 1-2 It includes frame I 1, top reinforcement 2, frame II 3, frame III 4, and frame IV 5 arranged from front to back along the aircraft's heading; frame I 1, top reinforcement 2, frame II 3, frame III 4, and frame IV 5 are connected into an integral structure by secondary adhesive bonding and skin 6; among them, frame I 1 is located at the nose position, the cockpit is between frame I 1 and frame II 3, the rear section of the fuselage is between frame II 3 and frame III 4, and the vertical tail is behind frame III 4; the top of the cockpit is reinforced by top reinforcement 2.

[0025] The aforementioned frame 1 is a glass fiber foam sandwich structure, which is connected to the skin 6 by secondary adhesive bonding.

[0026] The aforementioned top reinforcement 2 is a carbon fiber laminate structure, which is connected to the skin 6 by secondary adhesive bonding.

[0027] The aforementioned frame 3 is a carbon fiber laminate structure, which is connected to the skin 6 by secondary adhesive bonding.

[0028] The aforementioned frame 4 is a glass fiber foam sandwich structure, which is connected to the skin 6 by secondary adhesive bonding.

[0029] The aforementioned frame 5 is a glass fiber foam sandwich structure, which is connected to the skin 6 by secondary adhesive bonding.

[0030] The aforementioned skin 6 is a glass fiber foam sandwich structure, which is divided into two skins, left and right, by a symmetrical central plane. It is connected to frame I, top reinforcement 2, frame II, frame III, and frame IV by secondary bonding.

[0031] The skin of the aforementioned vertical tail section is integrated with the skin of the cylindrical fuselage.

[0032] The above detailed embodiments are a description of the present invention. It should not be considered that the specific embodiments of the present invention are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present invention, and all of these should be considered to fall within the protection scope of the present invention.

Claims

1. A composite material cylindrical fuselage for a lightweight sport aircraft, characterized in that, It includes a frame I (1), a top reinforcement (2), a frame II (3), a frame III (4), and a frame IV (5) arranged from front to back along the aircraft's heading; the frame I (1), the top reinforcement (2), the frame II (3), the frame III (4), and the frame IV (5) are connected into an integral structure by secondary bonding and skin (6); the frame I (1) is located at the nose position, the cockpit is between the frame I (1) and the frame II (3), the rear section of the fuselage is between the frame II (3) and the frame III (4), and the vertical tail is behind the frame III (4); the top of the cockpit is reinforced by the top reinforcement (2).

2. The composite material cylindrical fuselage of the light sport aircraft according to claim 1, characterized in that, The frame I (1) is a glass fiber foam sandwich structure, which is connected to the skin (6) by secondary bonding.

3. The composite material cylindrical fuselage of the light sport aircraft according to claim 1, characterized in that, The top reinforcement (2) is a carbon fiber laminate structure, which is connected to the skin (6) by secondary bonding.

4. The composite material cylindrical fuselage of the light sport aircraft according to claim 1, characterized in that, The frame II (3) is a carbon fiber laminate structure, which is connected to the skin (6) by secondary bonding.

5. The composite material cylindrical fuselage of the light sport aircraft according to claim 1, characterized in that, The III frame (4) is a glass fiber foam sandwich structure, which is connected to the skin (6) by secondary bonding.

6. The composite material cylindrical fuselage of the light sport aircraft according to claim 1, characterized in that, The IV frame (5) is a glass fiber foam sandwich structure, which is connected to the skin (6) by secondary bonding.

7. The composite material cylindrical fuselage of the light sport aircraft according to claim 1, characterized in that, The skin (6) is a glass fiber foam sandwich structure, which is divided into two skins, left and right, through the symmetrical center plane, and is connected to frame I (1), top reinforcement (2), frame II (3), frame III (4), and frame IV (5) by secondary bonding.

8. The composite material cylindrical fuselage of a light sport aircraft according to claim 1, characterized in that, The skin of the vertical tail section is integrated with the skin of the cylindrical fuselage.

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