阅读说明：本技术 一种飞行器燃料箱吊装位置的轻质扩散结构 (Light diffusion structure of aircraft fuel tank hoisting position ) 是由 季宝锋 王志勇 王非 刘发杰 刘含洋 张鹏 万孝军 陈朋 郑玉田 李益民 姚志强 于 2020-06-18 设计创作，主要内容包括：本发明的实施例提供一种飞行器燃料箱吊装位置的轻质扩散结构,包括：安装在燃料箱的壳体上,并与所述壳体环向固定连接的第一环框以及第二环框；安装在所述壳体上,并与所述壳体固定连接的第一横梁以及第二横梁；以及设置于所述壳体上的连接头；其中,所述第一横梁与所述第一环框固定连接；所述第二横梁分别与所述第一环框和所述第二环框固定连接,所述连接头位于所述第一横梁与所述第一环框围成的空间中。本发明的方案能够满足航空燃料箱特大集中力分散传递的使用需求。(An embodiment of the present invention provides a lightweight diffusion structure for an aircraft fuel tank lifting location, comprising: the first ring frame and the second ring frame are arranged on a shell of the fuel tank and are fixedly connected with the shell in the circumferential direction; the first cross beam and the second cross beam are arranged on the shell and fixedly connected with the shell; and a connector arranged on the shell; the first cross beam is fixedly connected with the first ring frame; the second cross beam is fixedly connected with the first ring frame and the second ring frame respectively, and the connector is located in a space surrounded by the first cross beam and the first ring frame. The scheme of the invention can meet the use requirement of the dispersion and transmission of the extra-large concentrated force of the aviation fuel tank.)

1. A lightweight diffusion structure for aircraft fuel tank lifting locations, comprising:

the first ring frame and the second ring frame are arranged on a shell (1) of the fuel tank and are fixedly connected with the shell (1) in the circumferential direction;

the first cross beam and the second cross beam are arranged on the shell (1) and fixedly connected with the shell (1); and

a connector (12) arranged on the shell (1);

the first cross beam is fixedly connected with the first ring frame; the second cross beam is fixedly connected with the first ring frame and the second ring frame respectively, and the connector (12) is located in a space surrounded by the first cross beam and the first ring frame.

2. The aircraft fuel tank lifting location lightweight diffusion structure of claim 1 wherein said first ring frame comprises: a first n-shaped ring frame (2) and a second n-shaped ring frame (3);

the first n-shaped ring frame (2) is fixedly connected with the shell (1) in the circumferential direction;

the second n-shaped ring frame (3) is fixedly connected with the shell (1) in the circumferential direction;

the first n-shaped ring frame (2) and the second n-shaped ring frame (3) are arranged side by side and are separated by a preset distance;

the connector (12) is positioned between the first n-shaped ring frame (2) and the second n-shaped ring frame (3).

3. The aircraft fuel tank lifting location lightweight diffusion structure of claim 2, wherein the second ring frame comprises: a third V-shaped ring frame (4) and a fourth V-shaped ring frame (5);

the third n-shaped ring frame (4) is fixedly connected with the shell (1) in the circumferential direction;

the fourth n-shaped ring frame (5) is fixedly connected with the shell (1) in the circumferential direction;

the third n-shaped ring frame (4) and the first n-shaped ring frame (2) are arranged side by side and are separated by a preset distance;

the fourth n-shaped ring frame (5) and the second n-shaped ring frame (3) are arranged side by side and are separated by a preset distance.

4. The aircraft fuel tank lifting location lightweight diffusion structure of claim 3 wherein said first cross-beam comprises: a first I-beam (6) and a second I-beam (7);

one end of the first I-shaped beam (6) is fixedly connected with the first n-shaped ring frame (2), the other end of the first I-shaped beam is fixedly connected with the second n-shaped ring frame (3), and the back of the first I-shaped beam (6) is fixedly connected with the shell (1);

one end of the second I-shaped beam (7) is fixedly connected with the first n-shaped ring frame (2), the other end of the second I-shaped beam is fixedly connected with the second n-shaped ring frame (3), and the back of the second I-shaped beam (7) is fixedly connected with the shell (1);

the first I-shaped beam (6) and the second I-shaped beam (7) are arranged side by side and are separated by a preset distance;

the connector (12) is located in a square cavity surrounded by the first I-shaped ring frame (2), the second I-shaped ring frame (3), the first I-shaped beam (6) and the second I-shaped beam (7).

5. The aircraft fuel tank lifting location lightweight diffusion structure of claim 4 wherein said second cross-beam comprises: a third I-beam (8), a fourth I-beam (9), a fifth I-beam (10) and a sixth I-beam (11);

one end of the third I-shaped beam (8) is fixedly connected with the first n-shaped ring frame (2), the other end of the third I-shaped beam is fixedly connected with the third n-shaped ring frame (4), and the back of the third I-shaped beam (8) is fixedly connected with the shell (1);

one end of the fourth I-shaped beam (9) is fixedly connected with the first N-shaped ring frame (2), the other end of the fourth I-shaped beam is fixedly connected with the third N-shaped ring frame (4), and the back of the fourth I-shaped beam (9) is fixedly connected with the shell (1);

one end of the fifth I-beam (10) is fixedly connected with the second n-shaped ring frame (3), the other end of the fifth I-beam is fixedly connected with the fourth n-shaped ring frame (5), and the back of the fifth I-beam (10) is fixedly connected with the shell (1);

one end of the sixth I-shaped beam (11) is fixedly connected with the second n-shaped ring frame (3), the other end of the sixth I-shaped beam is fixedly connected with the fourth n-shaped ring frame (5), and the back of the sixth I-shaped beam (11) is fixedly connected with the shell (1).

6. The aircraft fuel tank lifting position light weight diffusion structure according to claim 5, characterized in that the shell (1) is made of carbon fiber composite material, the shell wall of the shell (1) has a thickness smaller than a preset thickness and is of a solid of revolution structure.

7. Light weight diffusion structure for aircraft fuel tank lifting locations according to claim 6,

the first N-shaped ring frame (2) and the second N-shaped ring frame (3) are respectively provided with a first thickened area (N) at the connecting position with the shell (1);

second thickened areas (M) are respectively arranged at the connecting positions of the third n-shaped ring frame (4) and the fourth n-shaped ring frame (5) and the shell (1);

the thickness of the first thickened region is greater than the thickness of the second thickened region (M).

8. The lightweight diffusion structure for aircraft fuel tank lifting locations according to claim 7, characterized in that the back of the first I-beam (6) and the second I-beam (7) are fixedly connected with the first thickened area (N) of the shell (1), and the back of the first I-beam (6) and the back of the second I-beam (7) are both arc structures.

9. The lightweight diffusion structure for aircraft fuel tank lifting locations of claim 8,

the back parts of the third I-shaped beam (8), the fourth I-shaped beam (9), the fifth I-shaped beam (10) and the sixth I-shaped beam (11) are respectively and fixedly connected with the first thickened area (N) and the second thickened area (M) of the shell (1);

the back parts of the third I-shaped beam (8), the fourth I-shaped beam (9), the fifth I-shaped beam (10) and the sixth I-shaped beam (11) are all of special-shaped transition structures.

10. Light weight diffusion structure for aircraft fuel tank lifting locations according to claim 9,

the connector (12) is of a metal box-shaped structure and is provided with a plurality of step surfaces which are matched with each other in an installing way, and the connector is inserted into the square-shaped cavity through the step surfaces;

the connector (12) is fixedly connected with the first n-shaped ring frame (2), the second n-shaped ring frame (3), the first I-shaped beam (6) and the second I-shaped beam (7) respectively;

the back of the connector (12) is fixedly connected with the first thickening area (N) of the shell (1).

Technical Field

The invention relates to the technical field of hoisting structures of fuel tanks of aviation and aerospace aircrafts, in particular to a light diffusion structure at a hoisting position of a fuel tank of an aircraft.

Background

The aviation fuel tank is a thin-wall box structure hung below a fuselage or a wing of an aviation and aerospace aircraft, the thin-wall box structure is a streamline structure with a thick middle part and two sharp ends, and a thin-wall skin stringer structure or a bare shell structure is generally adopted. For the requirement of aircraft hanging, the aviation fuel tank generally has 2 or 3 points with the hanging connection structure of the aviation and aerospace aircraft, wherein one of the points is the most main hanging point, and the aviation fuel tank generally bears more than 80% of the overload load of the aviation fuel tank according to the overload load requirement of the tank body.

In the process of developing a certain aviation fuel tank, the lifting point load reaches 27t, and the wall thickness of a thin-wall shell connected with the lifting point load is 2mm, so that a structure capable of effectively diffusing an overlarge concentrated force is required to be designed, and the thin-wall shell fuel tank is guaranteed to have the required bearing capacity under the condition of light weight.

In the traditional technology, the similar concentrated force diffusion structure generally adopts the structural design scheme of two ring frames and a large casting box body, the concentrated force is transmitted to a large casting metal box through a hanging joint and then is transmitted and diffused to the large ring frames on two sides through the large casting metal box, and the large ring frames on two sides are transmitted to the thin-wall shell structure. The structural scheme is suitable for load transmission of metal aviation fuel tanks, but is not suitable for load transmission of composite aviation fuel tanks, and the load requirement of product use cannot be met.

Disclosure of Invention

The invention aims to provide a light diffusion structure for a lifting position of an aircraft fuel tank, which can meet the use requirement of dispersion and transmission of extra-large concentrated force of an aviation fuel tank.

In order to solve the technical problems, the technical scheme of the invention is as follows:

a lightweight diffusion structure for aircraft fuel tank lifting locations, comprising:

the first ring frame and the second ring frame are arranged on a shell of the fuel tank and are fixedly connected with the shell in the circumferential direction; the first cross beam and the second cross beam are arranged on the shell and fixedly connected with the shell; and a connector arranged on the shell; the first cross beam is fixedly connected with the first ring frame; the second beam is respectively fixedly connected with the first ring frame and the second ring frame, and the connector 12 is located in a space surrounded by the first beam and the first ring frame.

Optionally, the first ring frame includes: a first n-shaped ring frame and a second n-shaped ring frame; the first n-shaped ring frame is fixedly connected with the shell in the circumferential direction; the second n-shaped ring frame is fixedly connected with the shell in the circumferential direction; the first n-shaped ring frame and the second n-shaped ring frame are arranged side by side and are separated by a preset distance; the connector is located first style of calligraphy ring frame with between the second style of calligraphy ring frame.

Optionally, the second ring frame includes: a third n-shaped ring frame and a fourth n-shaped ring frame; the third n-shaped ring frame is fixedly connected with the shell in an annular direction; the fourth n-shaped ring frame is fixedly connected with the shell in an annular direction; the third n-shaped ring frame and the first n-shaped ring frame are arranged side by side and are separated by a preset distance; the fourth n-shaped ring frame and the second n-shaped ring frame are arranged side by side and are separated by a preset distance.

Optionally, the first beam includes: a first I-beam and a second I-beam; one end of the first I-shaped beam is fixedly connected with the first n-shaped ring frame, the other end of the first I-shaped beam is fixedly connected with the second n-shaped ring frame, and the back of the first I-shaped beam is fixedly connected with the shell; one end of the second I-shaped beam is fixedly connected with the first n-shaped ring frame, the other end of the second I-shaped beam is fixedly connected with the second n-shaped ring frame, and the back of the second I-shaped beam is fixedly connected with the shell; the first I-beam and the second I-beam are arranged side by side and are separated by a preset distance; the connector is located in the square cavity defined by the first I-shaped ring frame, the second I-shaped ring frame, the first I-shaped beam and the second I-shaped beam.

Optionally, the second beam includes: the third I-beam, the fourth I-beam, the fifth I-beam and the sixth I-beam; one end of the third I-beam is fixedly connected with the first n-shaped ring frame, the other end of the third I-beam is fixedly connected with the third n-shaped ring frame, and the back of the third I-beam is fixedly connected with the shell; one end of the fourth I-shaped beam is fixedly connected with the first inverted V-shaped ring frame, the other end of the fourth I-shaped beam is fixedly connected with the third inverted V-shaped ring frame, and the back of the fourth I-shaped beam is fixedly connected with the shell; one end of the fifth I-beam is fixedly connected with the second n-shaped ring frame, the other end of the fifth I-beam is fixedly connected with the fourth n-shaped ring frame, and the back of the fifth I-beam is fixedly connected with the shell; one end of the sixth I-beam is fixedly connected with the second n-shaped ring frame, the other end of the sixth I-beam is fixedly connected with the fourth n-shaped ring frame, and the back of the sixth I-beam is fixedly connected with the shell.

Optionally, the shell is made of a carbon fiber composite material, and a shell wall of the shell has a thickness smaller than a preset thickness and is of a revolving body structure.

Optionally, the first n-shaped ring frame and the second n-shaped ring frame are respectively provided with a first thickened area at the connecting position with the shell; second thickened areas are respectively arranged at the connecting positions of the third inverted-V-shaped ring frame and the fourth inverted-V-shaped ring frame and the shell; the thickness of the first thickened area is larger than that of the second thickened area.

Optionally, the back portions of the first i-beam and the second i-beam are fixedly connected with the first thickened area of the shell, and the back portions of the first i-beam and the second i-beam are both of arc structures.

Optionally, the back parts of the third i-beam, the fourth i-beam, the fifth i-beam and the sixth i-beam are respectively and fixedly connected with the first thickened area and the second thickened area of the shell; and the backs of the third I-shaped beam, the fourth I-shaped beam, the fifth I-shaped beam and the sixth I-shaped beam are all in special-shaped transition structures.

Optionally, the connector is of a metal box structure, and has a plurality of step surfaces which are installed and matched with each other, and the connector is inserted into the mouth-shaped cavity through the step surfaces; the connector is respectively fixedly connected with the first n-shaped ring frame, the second n-shaped ring frame, the first I-shaped beam and the second I-shaped beam; the back of the connector is fixedly connected with the first thickened area of the shell.

The scheme of the invention at least comprises the following beneficial effects:

according to the scheme of the invention, the light diffusion structure of the aircraft fuel tank hoisting position comprises: the first ring frame and the second ring frame are arranged on a shell of the fuel tank and are fixedly connected with the shell in the circumferential direction; the first cross beam and the second cross beam are arranged on the shell and fixedly connected with the shell; and a connector arranged on the shell; the first cross beam is fixedly connected with the first ring frame; the second cross beam is fixedly connected with the first ring frame and the second ring frame respectively. The connector is located in a space defined by the first cross beam and the first ring frame, and can effectively diffuse and decompose extra-large concentrated force borne by the connector in the radial direction of the tank body, finally diffuse the radial tensile force of the connector to the ring frame, and then transmit the extra-large concentrated force to the thin-wall shell through the ring frame, so that the dispersion and decomposition transfer of the extra-large concentrated force are realized, the use requirement of the dispersion and transfer of the extra-large concentrated force of the aviation fuel tank can be met, and the aviation fuel tank has the advantages of light weight, simple structure, capability of being integrally manufactured with the thin-wall structure, easiness in ensuring the sealing property of the tank.

Drawings

FIG. 1 is a perspective view of a lightweight diffusion structure of the aircraft fuel tank lifting location of the present invention;

FIG. 2 is a schematic view of the internal structure of the housing of the structure shown in FIG. 1;

FIG. 3 is a block diagram of a housing of the structure shown in FIG. 1;

FIG. 4 is a block diagram of a first inverted V-shaped ring frame and a second inverted V-shaped ring frame of the structure shown in FIG. 1;

FIG. 5 is a block diagram of a third chevron ring and a fourth chevron ring of the structure shown in FIG. 1;

FIG. 6 is a block diagram of a first I-beam and a second I-beam of the structure shown in FIG. 1;

FIG. 7 is a block diagram of a third I-beam, a fourth I-beam, a fifth I-beam, and a sixth I-beam of the structure shown in FIG. 1;

FIG. 8 is a block diagram of a connecting head of the structure shown in FIG. 1;

fig. 9 is a structural view of a connection head of the structure shown in fig. 1.

The reference numbers illustrate:

1-a shell; 2-a first n-shaped ring frame; 3-a second n-shaped ring frame; 4-a third n-shaped ring frame; 5-fourth n-shaped ring frame; 6-a first i-beam; 7-a second i-beam; 8-a third i-beam; 9-fourth I-beam; 10-a fifth i-beam; 11-sixth i-beam; 12-a connector.

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 and 2, an embodiment of the present invention provides a lightweight diffusion structure for an aircraft fuel tank lifting position, including:

the first ring frame and the second ring frame are arranged on a shell 1 of the fuel tank and are fixedly connected with the shell 1 in a circumferential direction;

the first cross beam and the second cross beam are arranged on the shell 1 and fixedly connected with the shell 1; and a connector 12 disposed on the housing 1;

the first cross beam is fixedly connected with the first ring frame; the second beam is respectively fixedly connected with the first ring frame and the second ring frame, and the connector 12 is located in a space surrounded by the first beam and the first ring frame.

The housing 1 of the fuel tank here is a thin-walled composite housing, which housing 1 is the integral structure of the fuel tank. In this embodiment, the first beam is fixedly connected with the first ring frame through the first ring frame and the second ring frame, the first beam and the second beam which are arranged on the housing 1; the second crossbeam respectively with first ring frame and second ring frame fixed connection, connector 12 are located in the space that first crossbeam with first ring frame encloses to can effectively diffuse and decompose the especially big concentrated power that connector 12 radially receives at the box, finally spread connector 12 radial tension to the ring frame, transmit to the thin wall casing by the ring frame again on, realized the dispersion of especially big concentrated power, decomposed the biography, thereby can satisfy the user demand of aviation fuel tank especially big concentrated power dispersion transmission.

In an alternative embodiment of the present invention, as shown in fig. 1, the first ring frame includes: a first n-shaped ring frame 2 and a second n-shaped ring frame 3; the first n-shaped ring frame 2 is fixedly connected with the shell 1 in an annular direction; the second n-shaped ring frame 3 is fixedly connected with the shell 1 in an annular direction; the first n-shaped ring frame 2 and the second n-shaped ring frame 3 are arranged side by side and are separated by a preset distance; the connector 12 is located between the first inverted-V-shaped ring frame 2 and the second inverted-V-shaped ring frame 3.

Here, the first n-shaped ring frame 2 is fixedly connected to the housing 1 in a circumferential direction by a fastening member, and the second n-shaped ring frame 3 is fixedly connected to the housing 1 in a circumferential direction by a fastening member; the fastening elements can be bolts and other fastening elements, so that the extra-large concentrated force borne by the connector 12 in the radial direction of the tank body can be effectively diffused and decomposed, the radial tensile force of the connector 12 is finally diffused to the ring frame and then transmitted to the thin-wall shell through the ring frame, the dispersion, decomposition and transfer of the extra-large concentrated force are realized, and the use requirement of the dispersion and transfer of the extra-large concentrated force of the aviation fuel tank can be met.

As shown in fig. 1, in an alternative embodiment of the present invention, the second ring frame includes: a third V-shaped ring frame 4 and a fourth V-shaped ring frame 5; the third n-shaped ring frame 4 is fixedly connected with the shell 1 in an annular direction; the fourth n-shaped ring frame 5 is fixedly connected with the shell 1 in an annular direction; the third n-shaped ring frame 4 and the first n-shaped ring frame 2 are arranged side by side and are separated by a preset distance; the fourth n-shaped ring frame 5 and the second n-shaped ring frame 3 are arranged side by side and separated by a preset distance.

Here, the third n-shaped ring frame 4 is fixedly connected with the housing 1 in a circumferential direction by a fastener, and the fourth n-shaped ring frame 5 is fixedly connected with the housing 1 in a circumferential direction by a fastener; and are respectively arranged at the two sides of the first n-shaped ring frame 2 and the second n-shaped ring frame 3, and the fastening pieces can be bolts and the like, so that the hoisting position of the fuel tank of the aircraft is firmer under the condition of meeting the requirement of light weight of the fuel tank.

As shown in fig. 4, the first n-shaped ring frame 2 and the second n-shaped ring frame 3 are annular composite material structures with n-shaped cross sections, and the first n-shaped ring frame 2 and the second n-shaped ring frame 3 are large n-shaped ring frames;

as shown in fig. 5, the third n-shaped ring frame 4 and the fourth n-shaped ring frame 5 are also in the form of a ring-shaped composite material structure with n-shaped cross sections, and the third n-shaped ring frame 4 and the fourth n-shaped ring frame 5 are small n-shaped ring frames;

the thickness of the small n-shaped ring frame is slightly smaller than that of the large n-shaped ring frame, and specifically, the thickness of the third n-shaped ring frame 4 and the thickness of the fourth n-shaped ring frame 5 are smaller than the thickness of the first n-shaped ring frame 2 and the thickness of the second n-shaped ring frame 3 by a preset thickness.

In an alternative embodiment of the present invention, as shown in fig. 1, the first beam includes: a first i-beam 6 and a second i-beam 7; one end of the first I-shaped beam 6 is fixedly connected with the first n-shaped ring frame 2, the other end of the first I-shaped beam is fixedly connected with the second n-shaped ring frame 3, and the back of the first I-shaped beam 6 is fixedly connected with the shell 1; one end of the second I-shaped beam 7 is fixedly connected with the first n-shaped ring frame 2, the other end of the second I-shaped beam is fixedly connected with the second n-shaped ring frame 3, and the back of the second I-shaped beam 7 is fixedly connected with the shell 1; the first I-beam 6 and the second I-beam 7 are arranged side by side and are separated by a preset distance; the connector 12 is located in the square cavity enclosed by the first n-shaped ring frame 2, the second n-shaped ring frame 3, the first I-shaped beam 6 and the second I-shaped beam 7.

As shown in fig. 6, the first i-beam 6 and the second i-beam 7 are large i-beams, one end of the first i-beam 6 is fixedly connected to the first n-shaped ring frame 2 through a fastener, the other end of the first i-beam is fixedly connected to the second n-shaped ring frame 3 through a fastener, and the back of the first i-beam 6 is fixedly connected to the housing 1 through a fastener, where the fastener may be a bolt or the like; therefore, the first n-shaped ring frame 2, the second n-shaped ring frame 3, the first I-shaped beam 6 and the second I-shaped beam 7 enclose a square cavity, the connector 12 is located in the square cavity, under the condition that the connector 12 is connected with an aircraft, the radial tension of the connector 12 can be diffused to the ring frame and then transmitted to the thin-wall shell through the ring frame, and the dispersion and decomposition transfer of the extra-large concentration force are realized, so that the use requirement of the dispersion and transfer of the extra-large concentration force of the aviation fuel tank can be met.

In an alternative embodiment of the present invention, as shown in fig. 1, the second beam includes: a third I-beam 8, a fourth I-beam 9, a fifth I-beam 10 and a sixth I-beam 11; one end of the third I-beam 8 is fixedly connected with the first n-shaped ring frame 2, the other end of the third I-beam is fixedly connected with the third n-shaped ring frame 4, and the back of the third I-beam 8 is fixedly connected with the shell 1; one end of the fourth I-shaped beam 9 is fixedly connected with the first N-shaped annular frame 2, the other end of the fourth I-shaped beam is fixedly connected with the third N-shaped annular frame 4, and the back of the fourth I-shaped beam 9 is fixedly connected with the shell 1; one end of the fifth I-beam 10 is fixedly connected with the second n-shaped ring frame 3, the other end of the fifth I-beam is fixedly connected with the fourth n-shaped ring frame 5, and the back of the fifth I-beam 10 is fixedly connected with the shell 1; one end of the sixth I-beam 11 is fixedly connected with the second n-shaped ring frame 3, the other end of the sixth I-beam is fixedly connected with the fourth n-shaped ring frame 5, and the back of the sixth I-beam 11 is fixedly connected with the shell 1.

As shown in fig. 7, a third i-beam 8, a fourth i-beam 9, a fifth i-beam 10 and a sixth i-beam 11 are small i-beams, one end of the third i-beam 8 is fixedly connected with the first n-shaped ring frame 2 through a fastener, the other end of the third i-beam is fixedly connected with the third n-shaped ring frame 4 through a fastener, and the back of the third i-beam 8 is fixedly connected with the shell 1 through a fastener; one end of the fourth I-shaped beam 9 is fixedly connected with the first n-shaped ring frame 2 through a fastener, the other end of the fourth I-shaped beam is fixedly connected with the third n-shaped ring frame 4 through a fastener, and the back of the fourth I-shaped beam 9 is fixedly connected with the shell 1 through a fastener; one end of the fifth I-beam 10 is fixedly connected with the second n-shaped ring frame 3 through a fastener, the other end of the fifth I-beam is fixedly connected with the fourth n-shaped ring frame 5 through a fastener, and the back of the fifth I-beam 10 is fixedly connected with the shell 1 through a fastener; one end of the sixth I-shaped beam 11 is fixedly connected with the second n-shaped ring frame 3 through a fastener, the other end of the sixth I-shaped beam is fixedly connected with the fourth n-shaped ring frame 5 through a fastener, and the back of the sixth I-shaped beam 11 is fixedly connected with the shell 1 through a fastener. The fasteners may be bolts or the like; in this embodiment, through the small i-beam between the big few style of calligraphy ring frame and the little few style of calligraphy ring frame, guaranteed the firm and stability of the hoist and mount position that connector 12 is located, satisfied the requirement of light simultaneously.

In an alternative embodiment of the present invention, as shown in fig. 3, the housing 1 is made of a carbon fiber composite material, and a thickness of a housing wall of the housing 1 is smaller than a predetermined thickness and is a solid of revolution.

Here, the first N-shaped ring frame 2 and the second N-shaped ring frame 3 are respectively provided with a first thickened region N at the connecting position with the housing 1; second thickened areas M are respectively arranged at the connecting positions of the third n-shaped ring frame 4 and the fourth n-shaped ring frame 5 and the shell 1; the thickness of the first thickened region N is larger than that of the second thickened region M.

Here, the first N-shaped ring frame 2 and the second N-shaped ring frame 3 are installed at the thickened region N of the thin-walled composite material shell 1 of 1, and are arranged at both sides of the connecting holes of the connecting heads 12 on the shell 1. Through the arrangement of the thickened area, the firmness and the stability of the hoisting position where the connector 12 is located are ensured.

As shown in fig. 3 and 6, in an alternative embodiment of the present invention, the back portions of the first i-beam 6 and the second i-beam 7 are fixedly connected to the first thickened region N of the shell 1, and the back portions of the first i-beam 6 and the second i-beam 7 are both arc structures.

Here, the first i-beam 6 and the second i-beam 7 are integrally formed in a metal box-shaped structure having an i-shaped section, and the back portions thereof are formed in a circular arc structure in order to accommodate the structure of the first thickened region N of the casing 1. The first I-shaped beam 6 and the second I-shaped beam 7 are fixedly connected with the first N-shaped ring frame 2 and the second N-shaped ring frame 3 through fasteners respectively, and the backs P of the first I-shaped beam 6 and the second I-shaped beam 7 are fixedly connected with the first thickened area N of the shell 1 through fasteners. The fasteners may be bolts or the like.

As shown in fig. 3 and 7, in an alternative embodiment of the present invention, the back portions of the third i-beam 8, the fourth i-beam 9, the fifth i-beam 10 and the sixth i-beam 11 are respectively and fixedly connected to the first thickened region N and the second thickened region M of the shell 1; and the backs of the third I-shaped beam 8, the fourth I-shaped beam 9, the fifth I-shaped beam 10 and the sixth I-shaped beam 11 are all in special-shaped transition structures.

Here, the third i-beam 8, the fourth i-beam 9, the fifth i-beam 10, and the sixth i-beam 11 are all of a metal box structure with an i-shaped cross section, and the back surfaces thereof are configured to be a special-shaped transition structure in order to adapt to the structures of the first thickened region N and the second thickened region M of the shell 1. The back O of the third I-beam 8, the fourth I-beam 9, the fifth I-beam 10 and the sixth I-beam 11 is fixedly connected with the first thickened area N and the second thickened area M of the shell 1 through fasteners. The fasteners may be bolts or the like.

As shown in fig. 1, 8 and 9, in an alternative embodiment of the present invention, the connecting head 12 is a metal box structure, and has a plurality of step surfaces for installation and matching, and the step surfaces are inserted into the square-shaped cavity; the connector 12 is fixedly connected with the first n-shaped ring frame 2, the second n-shaped ring frame 3, the first i-shaped beam 6 and the second i-shaped beam 7 respectively; the back of the connector 12 is fixedly connected with the first thickened area N of the housing 1.

Here, the whole structure of the connector 12 is a metal box structure, and has a plurality of step surfaces which are installed and matched, and the step surfaces are inserted into a square cavity which is embedded in the square cavity and is composed of a large inverted-V-shaped ring frame and a large H-shaped beam, the periphery of the connector 12 is fixedly connected with the adjacent large inverted-V-shaped ring frame and the large H-shaped beam through fasteners, and the back of the connector 12 is fixedly connected with a thickened area of the shell 1 through the fasteners. Thereby achieving a strong connection of the connection head 12 to the housing 1.

The structure of the embodiment of the invention is a structure of thickening and transition of four ring frames, a large cross beam composite joint and a composite material shell after being integrally assembled, can effectively diffuse and decompose extra large concentrated force borne by the connector 12 in the radial direction of the box body, finally diffuses the radial tensile force of the connector 12 to the n-shaped ring frames, and then transmits the radial tensile force to the thin-wall shell through the n-shaped ring frames, thereby realizing the dispersion, decomposition and transfer of the extra large concentrated force.

The light diffusion structure at the hoisting position of the aircraft fuel tank can solve the problem of the dispersion and transmission of the extra-large concentrated force, has the advantages of light weight, simple structure, capability of being integrally manufactured with a thin-wall structure, easiness in ensuring the sealing characteristic of the tank body, good manufacturability and the like, and is suitable for the dispersion and transmission of the radial large load of the ultra-thin-wall structure.

In the above description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.

Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically connected, electrically connected or can communicate with each other; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.

While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the appended claims.