Aircraft fuselage assembly and aircraft fuselage

Abstract

The utility model discloses an aircraft fuselage assembly and an aircraft fuselage, and relates to the field of aircrafts, the aircraft fuselage assembly comprises a first supporting piece and a second supporting piece, and the end part of the first supporting piece is provided with a first embedding part; a first matching hole matched with the first embedding part is formed in the second supporting piece; the first embedding part can be embedded into the first matching hole so that the first supporting piece can be connected with the second supporting piece. The structure is simple, installation is convenient, the installation structure is more stable and firm, and reliability is high. The aircraft fuselage comprises a third supporting piece and the fuselage assembly. A second embedding part is arranged at the end, away from the first embedding part, of the first supporting piece, and a second matching hole matched with the second embedding part is formed in the third supporting piece. Installation is simple, the fuselage is light in weight, and stability is high.

Description

Technical Field

[0001] The utility model relates to the field of aircraft, and in particular to an aircraft fuselage component and an aircraft fuselage. Background Art

[0002] At present, the fuselage of existing aircraft / UAVs is mostly made of aluminum alloy plates. Multiple aluminum alloy plates are connected by screws / spirals to form the fuselage frame of the aircraft. This method has poor stability and low reliability for long-term use.

[0003] In view of this, this application is hereby filed. Utility Model Content

[0004] The first purpose of the utility model is to provide an aircraft fuselage assembly, which has a simple structure and is easy to install, and the installation structure is more stable, firm and reliable.

[0005] The second object of the utility model is to provide an aircraft fuselage, which is easy to install, light in weight and strong in stability.

[0006] The embodiment of the utility model is achieved as follows:

[0007] An aircraft fuselage assembly includes: a first support member and a second support member, wherein the first support member has a first embedding portion at the end thereof; the second support member has a first matching hole that matches the first embedding portion; the first embedding portion can be embedded in the first matching hole to connect the first support member to the second support member.

[0008] Furthermore, a plurality of first embedded portions are arranged at intervals at the end of the first support member, and a plurality of first matching holes matching therewith are opened in the second support member.

[0009] Further, when the first embedded portion is embedded in the first matching hole, an angle A between a plane where the first support member is located and a plane where the second support member is located is greater than 0°.

[0010] Furthermore, a central axis of the first embedded portion is parallel to a plane where the first support member is located.

[0011] Further, along the central axis of the first embedded portion and in a direction away from the first support member, the diameter of the first embedded portion decreases.

[0012] Furthermore, the cross section of the first embedded portion is a polygon.

[0013] An aircraft fuselage comprises: a third support member and the above-mentioned fuselage assembly; a second embedding portion is provided at one end of the first support member away from the first embedding portion, and the third support member is provided with a second matching hole matching with the second embedding portion.

[0014] Furthermore, an angle B between a plane where the second support member is located and a plane where the third support member is located is less than 90°.

[0015] Further, along the circumferential direction of the second support member and the third support member, a plurality of first support members are arranged at intervals.

[0016] Furthermore, the first support member, the second support member and the third support member are each provided with a plurality of weight-reducing holes.

[0017] The beneficial effects of the embodiments of the utility model are:

[0018] The aircraft fuselage assembly provided by the embodiment of the utility model can change the traditional contact-type connection method through bolts to a component connection between the first support member and the second support member. Through this mortise and tenon structure, the first support member and the second support member are mutually connected and limited, so that the force is absorbed by the first support member and the second support member, thereby further improving the stability and reliability of the connection between the first support member and the second support member.

[0019] In general, the aircraft fuselage assembly provided by the embodiment of the utility model has a simple structure and is easy to install, and the installation structure is more stable, firm, and reliable. The aircraft fuselage is realized based on the fuselage assembly, which is easy to install, light in weight, and has strong stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the utility model and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying creative work.

[0021] Figure 1 A schematic diagram of the structure of a fuselage assembly provided by an embodiment of the utility model;

[0022] Figure 2 An exploded view of a fuselage assembly provided by an embodiment of the utility model;

[0023] Figure 3 A schematic diagram of the structure of an aircraft fuselage provided by an embodiment of the utility model;

[0024] Figure 4 An exploded view of an aircraft fuselage provided by an embodiment of the utility model;

[0025] Figure 5 A schematic diagram of a portion of the structure of an aircraft fuselage provided in an embodiment of the utility model.

[0026] Icon: 100 - fuselage assembly; 110 - first support member, 111 - first embedded portion, 112 -, second embedded portion, 120 - second support member, 121 - first matching hole;

[0027] 1000 - aircraft fuselage; 200 - third support member, 210 - second matching hole. DETAILED DESCRIPTION

[0028] In order to make the purpose, technical scheme and advantages of the embodiments of the utility model clearer, the technical scheme in the embodiments of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Generally, the components of the embodiments of the utility model described and shown in the drawings here can be arranged and designed in various different configurations.

[0029] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the present invention to be protected, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0030] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0031] In the description of the present utility model, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, or the positions or positional relationships in which the utility model product is usually placed when in use, and are only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific position, be constructed and operated in a specific position, and therefore cannot be understood as a limitation on the present utility model. In addition, the terms "first", "second", "third", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0032] In addition, the terms "parallel", "vertical", etc. do not mean that the components must be absolutely parallel or vertical, but can be slightly tilted. For example, "parallel" only means that its direction is more parallel than "vertical", and does not mean that the structure must be completely parallel, but can be slightly tilted.

[0033] In addition, the terms "horizontal", "vertical", "overhanging" and the like do not mean that the components are required to be absolutely horizontal or overhanging, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0034] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0035] Example

[0036] At present, the existing aircraft fuselages are assembled by connecting multiple aluminum alloy plates through screws / bolts. However, in this way, the force between adjacent support plates is completely applied to the screws / bolts, resulting in a certain lack of stability and firmness of the overall fuselage. In addition, the screws / bolts are easily loosened during long-term use, resulting in a loose state between the supports, which in turn causes the aircraft fuselage to become loose and unstable, thereby affecting normal flight.

[0037] For the reasons above, please refer to Figure 1 , Figure 2 The present embodiment provides an aircraft fuselage 1000 assembly 100, comprising: a first support member 110 and a second support member 120, wherein a first embedding portion 111 is provided at the end of the first support member 110; the second support member 120 is provided with a first matching hole 121 matching with the first embedding portion 111; the first embedding portion 111 can be embedded in the first matching hole 121, so that the first support member 110 is connected to the second support member 120.

[0038] Specifically, a plurality of first embedding portions 111 are spaced apart at the end of the first supporting member 110 , and a plurality of first matching holes 121 matching therewith are formed in the second supporting member 120 .

[0039] It should be noted that the first embedded portion 111 is disposed at one end of the first support member 110 that contacts the second support member 120 , and a plurality of first embedded portions 111 are spaced apart along the central axis of the end surface of the first embedded portion 111 .

[0040] Another thing to be explained is that the position of the first matching hole 121 is set according to the position of the first embedding portion 111 to ensure that the plurality of first embedding portions 111 can be respectively embedded in each first matching hole 121 at the same time.

[0041] It should be noted that the central axis of the first embedded portion 111 is parallel to the plane where the first support member 110 is located.

[0042] Through the above design, the traditional contact-type connection method through bolts can be changed to a component connection between the first support member 110 and the second support member 120. Through this mortise and tenon structure, the first support member 110 and the second support member 120 are mutually connected and limited, so that the force is absorbed by the first support member 110 and the second support member 120, thereby further improving the stability and reliability of the connection between the first support member 110 and the second support member 120.

[0043] In general, the aircraft fuselage 1000 assembly 100 provided by the embodiment of the utility model has a simple structure and is easy to install, and the installation structure is more stable, firm, and reliable.

[0044] In this embodiment, when the first embedded portion 111 is embedded in the first matching hole 121, the angle A between the plane where the first support member 110 is located and the plane where the second support member 120 is located is greater than 0°. In order to better transmit the force between the first support member 110 and the second support member 120, the angle A is preferably 90°.

[0045] In some embodiments, the diameter of the first embedded portion 111 decreases along the central axis of the first embedded portion 111 and away from the first support member 110. The first embedded portion 111 is "conical" or "trapezoidal" as a whole, so that it is more convenient to embed in the first matching hole 121 and have an interference fit with the first matching hole 121.

[0046] In some other embodiments, along the central axis of the first embedding portion 111 and in a direction away from the first supporting member 110 , the diameter of the first embedding portion 111 remains unchanged and is directly embedded in the first matching hole 121 .

[0047] In addition, since the force between the first support member 110 and the second support member 120 mainly acts on the first embedded portion 111, in order to enable the first embedded portion 111 to bear a larger shear force, the cross-section of the first embedded portion 111 is polygonal, preferably rectangular.

[0048] In addition, please refer to Figure 3-Figure 5 In this embodiment, an aircraft fuselage 1000 is also provided, which includes a third support member 200 and the above-mentioned fuselage assembly 100. The first support member 110 is provided with a second embedded portion 112 at one end away from the first embedded portion 111, and the third support member 200 is provided with a second matching hole 210 that matches the second embedded portion 112.

[0049] Specifically, the angle B between the plane where the second support member 120 is located and the plane where the third support member 200 is located is less than 90°; in order to make the fuselage more stable, the angle B is preferably 0°, that is, the plane where the second support member 120 is located is parallel to the plane where the third support member 200 is located.

[0050] In addition, along the circumference of the second support member 120 and the third support member 200, a plurality of first support members 110 are arranged at intervals, thereby further ensuring the reliability and stability of the entire fuselage.

[0051] In addition, in order to further reduce the weight of the fuselage, in this embodiment, the first support member 110, the second support member 120 and the third support member 200 are each provided with a plurality of weight-reducing holes. In order to ensure the balance of the fuselage, the weight-reducing holes are arranged as symmetrically and evenly as possible.

[0052] It should be noted that, in order to further ensure that the plurality of first support members 110 are more firmly connected to the second support member 120 and the third support member 200, screws / bolts / rivets may be used for further fixing after the overall fuselage is installed.

[0053] In summary, the aircraft fuselage 1000 assembly 100 provided by the utility model has a simple structure and is easy to install, and the installation structure is more stable, firm, and reliable. The aircraft fuselage 1000 is realized based on the fuselage assembly 100, which is easy to install, light in weight, and highly stable.

[0054] The above description is only the preferred embodiment of the utility model, and is not intended to limit the utility model. For those skilled in the art, the utility model can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.

Claims

1. An aircraft fuselage assembly, characterized in that: include: A first supporting member, wherein a first embedding portion is provided at an end of the first supporting member; a second supporting member, wherein the second supporting member is provided with a first matching hole matching with the first embedding portion; The first embedding portion can be embedded in the first matching hole to connect the first supporting member with the second supporting member.

2. The aircraft fuselage assembly according to claim 1, characterized in that: A plurality of first embedding portions are arranged at intervals at the end of the first supporting member, and a plurality of first matching holes matching with the first embedding portions are formed in the second supporting member.

3. The aircraft fuselage assembly according to claim 1, characterized in that: When the first embedding portion is embedded in the first matching hole, an angle A between a plane where the first supporting member is located and a plane where the second supporting member is located is greater than 0°.

4. The aircraft fuselage assembly according to claim 1, characterized in that: The central axis of the first embedded portion is parallel to the plane where the first supporting member is located.

5. The aircraft fuselage assembly according to claim 1, characterized in that: Along the central axis of the first embedded portion and in a direction away from the first supporting member, the diameter of the first embedded portion decreases.

6. The aircraft fuselage assembly according to claim 1, characterized in that: The cross section of the first embedding portion is polygonal.

7. An aircraft fuselage, characterized in that: include: A third support member and a fuselage assembly as claimed in any one of claims 1 to 6; A second embedding portion is provided at one end of the first supporting member away from the first embedding portion, and a second matching hole matching with the second embedding portion is formed in the third supporting member.

8. The aircraft fuselage according to claim 7, characterized in that: An angle B between a plane where the second support member is located and a plane where the third support member is located is less than 90°.

9. The aircraft fuselage according to claim 7, characterized in that: A plurality of the first supporting members are arranged at intervals along the circumferential direction of the second supporting member and the third supporting member.

10. The aircraft fuselage according to claim 7, characterized in that: The first support member, the second support member and the third support member are each provided with a plurality of weight-reducing holes.

Images