Reinforcing structure for protruding component outside fuselage

Abstract

The utility model belongs to the technical field of aviation structure design, and relates to a fuselage external protruding component reinforcing structure which is characterized in that two combined frames and two combined longitudinal pieces form a box section combined piece; and the box section assembly is fixedly connected with the fuselage skin. The reinforcing structure is used for the fuselage external protruding component fuselage, and overcomes the defects that a traditional supporting structure is poor in bearing capacity, low in rigidity, large in weight, poor in manufacturability and the like.

Description

Technical Field

[0001] The utility model belongs to the technical field of aviation technical structure design, and relates to a reinforcing structure for external protruding components of the fuselage. Background Art

[0002] The body support structure of the external device of the aircraft. In the body structure, it mainly participates in the overall load bearing of the installation part, bears the additional local load of the external device of the aircraft during flight and ground conditions, and provides stiffness support for the conventional body structure. It usually includes two parts: a basic part and a reinforcing assembly. At present, for the body support structure of the external device of the aircraft, most of them adopt adding reinforcing plates at the body structure part, adding longer internal profiles or plate-bent auxiliary frames within the installation boundary, and using profiles of the same specification for the stringers. The strengthening method is not standardized, the targeted reinforcement is poor, the stiffness changes greatly, and the weight is relatively heavy. Content of the Utility Model

[0003] 1. Technical Problem to be Solved

[0004] The utility model overcomes the deficiencies in the prior art and provides a body internal support structure for the external device of the aircraft with strong bearing capacity, large support stiffness, light weight, and good installation processability.

[0005] 2. Technical Solution

[0006] A reinforcing structure for external protruding components of the fuselage, wherein the reinforcing structure is composed of two combined frames and two combined longitudinal members to form a box-section combined component; the box-section combined component is fixedly connected to the fuselage skin.

[0007] Furthermore, the combined frame is successively composed of a T-shaped angle section perpendicular to the skin, a first connecting plate, a first L-shaped angle section, and a reinforcing angle piece; wherein, the T-shaped angle section includes a horizontal section and a vertical section, the vertical section is connected to the upper half of the first connecting plate, the lower half of the first connecting plate is respectively connected to the first L-shaped angle section and the reinforcing angle piece, and the lower horizontal section of the first L-shaped angle section is connected to the combined frame; the lower straight section of the reinforcing angle piece is connected to the skin.

[0008] Furthermore, the combined longitudinal member is arranged perpendicular to the combined frame and includes a second L-shaped angle section, a second connecting plate, and a longitudinal support member; wherein, the second L-shaped angle section is connected to the upper half of the second connecting plate, the lower half of the second connecting plate is connected to the upper section of the longitudinal support member, and the lower straight section of the longitudinal support member is connected to the skin.

[0009] Furthermore, two grooves are provided in the middle of the reinforcing angle piece to ensure that the reinforcing angle pieces span two longitudinal support members, and at the same time, the grooves also serve as the passing space for the longitudinal members.

[0010] Furthermore, grooves for inserting the combined frame are provided on both the second connecting plate and the longitudinal support member.

[0011] Furthermore, the longitudinal support member is of an L-shaped structure, and a number of reinforcing plates are arranged on the side surface.

[0012] Furthermore, joints are symmetrically arranged on both sides of the combination frame along the two combined longitudinal members. The joint includes a straight section and vertical sections distributed at both ends of the straight section. The straight section is connected to the combination frame, and the vertical sections are connected to the second connecting plate and the longitudinal support member.

[0013] 3. Beneficial technical effects

[0014] The utility model provides a body support structure for an external device of an aircraft. It is positioned on a conventional tooling. The frame edge assembly is an L-shaped profile and a flat plate, which are positioned on the tooling and riveted to the skin and the reinforcing gusset. It is convenient to install and has good processability. The longitudinal member is an L-shaped profile, a flat plate and a longitudinal support member, which are riveted together. It has good processability, strong load-bearing capacity, large support stiffness and light weight. It is convenient to install and has good processability. Description of the drawings

[0015] Figure 1 It is a structural reinforcement diagram of a prominent component on the outer part of the fuselage;

[0016] Figure 2 It is a drawing of the skin 1;

[0017] Figure 3 It is a drawing of the T-shaped angle bar 2;

[0018] Figure 4 It is a drawing of the bending plate 3;

[0019] Figure 5 It is a drawing of the L-shaped angle bar 4;

[0020] Figure 6 It is a drawing of the reinforcing gusset 5;

[0021] Figure 7 It is a drawing of the L-shaped angle bar 6;

[0022] Figure 8 It is a drawing of the bending plate 7;

[0023] Figure 9 It is a drawing of the longitudinal support member 8;

[0024] Figure 10 It is a drawing of the joint 9;

[0025] Figure 11 It is a drawing of a single frame edge assembly;

[0026] Figure 12 It is a drawing of a single combined longitudinal member.

[0027] Among them, the skin 1, T-shaped angle member 2, first bending plate 3, first L-shaped angle member 4, reinforcing angle piece 5, second L-shaped angle member 6, second bending plate 7, longitudinal support member 8, and joint 9. Specific embodiments

[0028] A detailed description of a reinforced structure for external protruding members of the fuselage of the present utility model is given in conjunction with the accompanying drawings: The present utility model specifically designs a body support structure for an aircraft external device, including 1 skin 1, 2 T-shaped angle members 2, 2 bending plates 3, 2 L-shaped angle members 4, 2 reinforcing angle pieces 5, 2 L-shaped angle members 6, 2 bending plates 7, 2 longitudinal support members 8, and 4 joints 9;

[0029] Each frame edge assembly includes: 1 set of L-shaped angle members 2, 1 set of bending plates 3, and 1 set of reinforcing angle pieces 4, for a total of 2 sets of frame edge assemblies;

[0030] Each combined longitudinal member includes: 1 set of L-shaped angle members 5, 1 set of bending plates 6, and 1 set of longitudinal support members, for a total of 2 sets of longitudinal assemblies;

[0031] A single frame edge assembly and a single longitudinal member are connected by 2 joints 9.

[0032] As Figure 1 shown, the body support structure of the aircraft external device includes: 2 combined frames and 2 combined longitudinal members. The two combined frames have the same combination form, and the combined longitudinal members also have the same combination form.

[0033] A single combined frame includes: 1 T-shaped angle member 2, 1 bending plate 3, 1 L-shaped angle member 4, and 1 reinforcing angle piece 5. The components are assembled together by riveting, for a total of 1 set of frame edge assembly;

[0034] A single combined longitudinal member: 1 L-shaped angle member 6, 1 bending plate 7, and 1 longitudinal support member 8. The components are assembled together by riveting, for a total of 1 set of longitudinal member.

[0035] Finally, it should be noted that: The above embodiments or implementation cases are only used to illustrate the technical solutions of the present utility model, and the unelaborated parts are regarded as conventional technical means or common general knowledge in the art; It should be understood that the protection scope of the present utility model is not limited to the above specific implementation forms. Any person skilled in the art can easily think of various equivalent modifications or replacements within the technical scope disclosed by the present utility model, and these modifications or replacements should all be covered within the protection scope of the present utility model.

Claims

1. An external protruding member strengthening structure of a fuselage, characterized in that The reinforcing structure is composed of two combined frames and two combined longitudinal members to form a box-section assembly; the box-section assembly is fixedly connected to the fuselage skin. The combined frame is successively composed of a T-shaped angle bar perpendicular to the skin, a first connecting plate, a first L-shaped angle bar, and a reinforcing angle piece. Among them, the T-shaped angle bar includes a horizontal section and a vertical section. The vertical section is connected to the upper half of the first connecting plate. The lower half of the first connecting plate is respectively connected to the first L-shaped angle bar and the reinforcing angle piece. The lower horizontal section of the first L-shaped angle bar is connected to the combined frame. The lower straight section of the reinforcing angle piece is connected to the skin. The combined longitudinal member is arranged perpendicular to the combined frame and includes a second L-shaped angle bar, a second connecting plate, and a longitudinal support member. Among them, the second L-shaped angle bar is connected to the upper half of the second connecting plate. The lower half of the second connecting plate is connected to the upper section of the longitudinal support member. The lower straight section of the longitudinal support member is connected to the skin.

2. The reinforcing structure for an externally protruding member of the fuselage according to claim 1, characterized in that, There are two grooves provided in the middle of the reinforcing angle piece to ensure that the reinforcing angle pieces span across two combined longitudinal members.

3. The strengthening structure of an externally protruding member of the fuselage according to claim 1, characterized in that, Joints are symmetrically arranged along both sides of the combined frame between the two sections of the combined longitudinal member. The joint includes a straight section and vertical sections distributed at both ends of the straight section. The straight section is connected to the combined frame, and the vertical sections are connected to the second connecting plate and the longitudinal support member.

4. The reinforcing structure for an externally protruding member of a fuselage according to claim 1, wherein, Grooves for inserting the combined frame are provided on both the second connecting plate and the longitudinal support member.

5. The reinforcing structure for an externally protruding member of a fuselage according to claim 4, characterized in that, The longitudinal support member is of an L-shaped structure, and several reinforcing plates are arranged on the side.

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