阅读说明：本技术 一种飞机的背鳍结构 (dorsal fin structure of airplane ) 是由 庞华华 何四海 姚雄华 吴斌 于 2019-09-19 设计创作，主要内容包括：本申请属于飞机背鳍结构设计技术领域,具体涉及一种飞机的背鳍结构,包括：尖部结构,具有尖端、与尖端相对的末端、在尖端与末端延伸的两个侧边；尖部结构的尖端、两个侧边用以贴合至飞机的机身；中部结构,具有中部前端、与中部前端相对的中部后端、在中部前端与中部后端之间延伸的两个侧边；中部前端与末端对接；中部结构的两个侧边用以贴合至机身；根部结构,具有根部前端、与根部前端相对的根部后端、在根部前端与根部后端延伸的两个侧边；根部前端与中部后端对接；根部结构的两个侧边用以贴合至机身；根部后端用以贴合至飞机的垂尾前缘。(the application belongs to the technical field of aircraft dorsal fin structural design, concretely relates to dorsal fin structure of aircraft, include: a tip structure having a tip, a distal end opposite the tip, two sides extending between the tip and the distal end; the tip end and the two side edges of the tip structure are used for being attached to the airplane body of the airplane; a middle structure having a middle front end, a middle rear end opposite the middle front end, two sides extending between the middle front end and the middle rear end; the front end of the middle part is butted with the tail end; the two side edges of the middle structure are used for being attached to the machine body; a root structure having a root front end, a root rear end opposite the root front end, two sides extending at the root front end and the root rear end; the front end of the root part is butted with the rear end of the middle part; two sides of the root structure are used for being attached to the fuselage; the rear end of the root is used for being attached to the vertical tail front edge of the airplane.)

1. A dorsal fin structure for an aircraft, comprising:

A tip structure (1) having a tip, an end opposite to the tip, two sides extending at the tip and the end; the tip end and two side edges of the tip structure (1) are used for being attached to a fuselage (13) of an airplane;

a middle structure (2) having a middle front end, a middle rear end opposite the middle front end, two sides extending between the middle front end and the middle rear end; the front end of the middle part is butted with the tail end; two side edges of the middle structure (2) are used for being attached to the machine body (13);

a root structure (3) having a root front end, a root rear end opposite the root front end, two sides extending at the root front end and the root rear end; the front end of the root part is butted with the rear end of the middle part; the two side edges of the root structure (3) are used for being attached to the fuselage (13); the root aft end is configured to attach to a leading edge of a vertical tail (14) of the aircraft.

2. The dorsal fin structure of claim 1,

Further comprising:

A first partition (4) for connecting to the fuselage (13) and having a plurality of first lightening holes (11) made therein; the inner wall of the tail end and the inner wall of the front end of the middle part are overlapped along the edge of the first clapboard (4);

a second partition (5) for connecting to the fuselage (13) and provided with a plurality of second lightening holes; the inner wall of the rear end of the middle part and the inner wall of the front end of the root part are overlapped along the edge of the second clapboard (5).

3. The dorsal fin structure of claim 2,

further comprising:

a first bead (6) disposed along an edge of the first separator (4); the inner wall of the tail end and the inner wall of the front end of the middle part are overlapped along the first edge strip (6);

a second bead arranged along an edge of the second separator (5); the inner wall of the rear end of the middle part and the inner wall of the front end of the root part are in lap joint along the second edge strip.

4. the dorsal fin structure of claim 2,

the device also comprises a third clapboard (10) which is connected to the machine body (13) and is provided with a plurality of third lightening holes (12); the inner wall of the rear end of the root part is overlapped along the edge of the second clapboard (5).

5. the dorsal fin structure of claim 5,

The third edge strip (7) is arranged along the edge of the second partition plate (5); the inner wall of the rear end of the root part is lapped along the third edge strip (7).

6. the dorsal fin structure of claim 6,

Further comprising:

The first ribs (8) are arranged on the third partition board (10), and two ends of the first ribs extend to the third edge strips (7);

And the second ribs (9) are arranged on the third partition board (10) and are crossed with the first ribs (8), and two ends of the second ribs extend to the third edge strips (7).

7. the aircraft dorsal fin structure of claim 1,

The tip structure (1) is formed by integral composite materials.

8. The aircraft dorsal fin structure of claim 7,

the tip structure (1) is in the form of a laminate.

9. the aircraft dorsal fin structure of claim 8,

the tip end, the tail end and two side edge areas of the tip part structure (1) are locally thickened.

10. the aircraft dorsal fin structure of claim 1,

The middle structure (2) is made of composite materials, and the front end area and the rear end area of the middle part of the middle structure are locally thickened; the middle structure (2) is in a honeycomb sandwich structure in the areas at the front end of the middle part, the rear end of the middle part and between the two side edges;

The root structure (3) is made of composite materials, and the front end of the root and the rear end area of the root are locally thickened; the root structure (3) is in a honeycomb sandwich structure in the areas of the middle front end, the middle rear end and between the two side edges.

Technical Field

the application belongs to the technical field of airplane dorsal fin structural design, and particularly relates to a dorsal fin structure of an airplane.

background

The aircraft dorsal fin is used for being connected with aircraft vertical fin leading edge and fuselage, and current aircraft dorsal fin is mostly whole fashioned cover body structure, sets up the polylith baffle support in it, and the aircraft dorsal fin of this kind of form is in case its inside defect that appears, and the maintenance degree of difficulty is great, need change whole dorsal fin even when serious, and maintenance, maintenance cost are higher.

the present application is made in view of the above-mentioned drawbacks of the prior art.

Disclosure of Invention

It is an object of the present application to provide a dorsal fin structure for an aircraft that overcomes or mitigates at least one of the disadvantages of the prior art.

the technical scheme of the application is as follows:

A dorsal fin structure of an aircraft, comprising:

a tip structure having a tip, a distal end opposite the tip, two sides extending between the tip and the distal end; the tip end and the two side edges of the tip structure are used for being attached to the airplane body of the airplane;

a middle structure having a middle front end, a middle rear end opposite the middle front end, two sides extending between the middle front end and the middle rear end; the front end of the middle part is butted with the tail end; the two side edges of the middle structure are used for being attached to the machine body;

a root structure having a root front end, a root rear end opposite the root front end, two sides extending at the root front end and the root rear end; the front end of the root part is butted with the rear end of the middle part; two sides of the root structure are used for being attached to the fuselage; the rear end of the root is used for being attached to the vertical tail front edge of the airplane.

according to at least one embodiment of the present application, further comprising:

the first partition board is connected to the machine body and provided with a plurality of first lightening holes; the inner wall of the tail end and the inner wall of the front end of the middle part are overlapped along the edge of the first clapboard;

the second clapboard is used for being connected to the machine body and is provided with a plurality of second lightening holes; the inner wall of the rear end of the middle part and the inner wall of the front end of the root part are overlapped along the edge of the second clapboard.

according to at least one embodiment of the present application, further comprising:

a first bead disposed along an edge of the first separator; the inner wall of the tail end and the inner wall of the front end of the middle part are lapped along the first edge strip;

The second edge strip is arranged along the edge of the second partition plate; the inner wall of the rear end of the middle part and the inner wall of the front end of the root part are lapped along the second edge strip.

according to at least one embodiment of the present application, the portable terminal further includes a third partition plate for connecting to the body, and having a plurality of third lightening holes; the inner wall of the rear end of the root is overlapped along the edge of the second partition plate.

According to at least one embodiment of the present application, further comprising a third bead disposed along an edge of the second separator; the inner wall of the rear end of the root part is lapped along the third edge strip.

According to at least one embodiment of the present application, further comprising:

The first ribs are arranged on the third partition plate, and two ends of the first ribs extend to the third edge strips;

And the second ribs are arranged on the third partition board and are crossed with the first ribs, and two ends of the second ribs extend to the third edge strips.

According to at least one embodiment of the present application, the tip structure is integrally formed with the composite material.

According to at least one embodiment of the present application, the tip structure is in the form of a laminate.

According to at least one embodiment of the present application, the tip, end and side regions of the tip structure are locally thickened.

According to at least one embodiment of the application, the middle structure is made of a composite material, wherein the middle front end and the middle rear end are locally thickened; the middle structure is in a honeycomb sandwich structure in the areas positioned at the front end of the middle part, the rear end of the middle part and between the two side edges;

The root structure is made of composite materials, and the front end of the root and the rear end area of the root are locally thickened; the root structure is in a honeycomb sandwich structure in the areas between the middle front end, the middle rear end and the two side edges.

drawings

Fig. 1 is a schematic structural diagram of a dorsal fin structure of an aircraft provided in an embodiment of the present application;

Fig. 2 is a schematic structural diagram of a tip structure provided in an embodiment of the present application;

FIG. 3 is a schematic structural diagram of a middle structure provided in an embodiment of the present application;

FIG. 4 is a schematic structural diagram of a root structure provided in an embodiment of the present application;

FIG. 5 is a schematic structural diagram of a first separator according to an embodiment of the present disclosure;

FIG. 6 is a schematic structural diagram of a third separator according to an embodiment of the present disclosure;

FIG. 7 is a structural schematic diagram of an aircraft dorsal fin structure cooperating with an aircraft according to an embodiment of the present disclosure;

wherein:

1-tip structure; 2-middle structure; 3-root structure; 4-a first separator; 5-a second separator; 6-a first bead; 7-third bead; 8-first ribs; 9-second ribs; 10-a third separator; 11-a first lightening hole; 12-a third lightening hole; 13-a fuselage; 14-vertical tail.

Detailed Description

The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.

It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.

The present application is described in further detail below with reference to fig. 1 to 7.

A dorsal fin structure of an aircraft, comprising:

a tip structure 1 having a tip, a distal end opposite the tip, two sides extending between the tip and the distal end; the tip and the two side edges of the tip structure 1 are used for being attached to the fuselage 13 of the airplane;

a middle structure 2 having a middle front end, a middle rear end opposite the middle front end, two sides extending between the middle front end and the middle rear end; the front end of the middle part is butted with the tail end; two side edges of the middle structure 2 are used for being attached to the machine body 13;

A root structure 3 having a root front end, a root rear end opposite the root front end, two side edges extending at the root front end and the root rear end; the front end of the root part is butted with the rear end of the middle part; the two sides of the root structure 3 are intended to be attached to the fuselage 13; the rear end of the root is adapted to be attached to the leading edge of the vertical tail 14 of the aircraft.

as for the dorsal fin structure of the airplane disclosed in the above embodiments, it is easily understood by those skilled in the art that it is composed of the tip structure 1, the middle structure 2, and the root structure 3 which are butted in sequence, and the shape of the portion for fitting to the front edge of the fuselage 13 or the vertical fin 14 is adapted to the shape of the corresponding fitting portion, and the dorsal fin structure in this form is convenient for assembly, maintenance, and repair.

in some optional embodiments, further comprising:

A first partition plate 4 for connecting to a body 13, having a plurality of first lightening holes 11; the inner wall of the tail end and the inner wall of the front end of the middle part are lapped along the edge of the first clapboard 4;

A second partition 5 for connecting to the body 13, having a plurality of second lightening holes; the inner wall of the rear end of the middle part and the inner wall of the front end of the root part are overlapped along the edge of the second clapboard 5.

As for the dorsal fin structure of the aircraft disclosed in the above embodiments, it is easily understood by those skilled in the art that the first partition plate 4 and the second partition plate 5 are provided to support the butted portions between the tip structure 1 and the middle structure 2 and between the middle structure 2 and the root structure 3 to enhance the structural stability.

In some optional embodiments, further comprising:

A first bead 6 disposed along an edge of the first separator 4; the inner wall of the tail end and the inner wall of the front end of the middle part are overlapped along the first edge strip 6;

a second bead disposed along an edge of the second barrier 5; the inner wall of the rear end of the middle part and the inner wall of the front end of the root part are lapped along the second edge strip.

in some optional embodiments, the present invention further comprises a third partition 10, for connecting to the body 13, and having a plurality of third lightening holes 12; the inner wall of the rear end of the root portion is overlapped along the edge of the second partition 5.

As for the dorsal fin structure of the aircraft disclosed in the above embodiments, it is easily understood by those skilled in the art that the third partition 10 is disposed at the rear end of the root structure 3 to support the dorsal fin structure, so as to effectively increase the overall stability of the dorsal fin structure, and reduce the stress between the rear end of the root and the front edge of the vertical tail 14,

in some optional embodiments, a third bead 7 is further included, and is disposed along an edge of the second separator 5; the inner wall of the rear end of the root overlaps along the third bead 7.

in some optional embodiments, further comprising:

The first ribs 8 are arranged on the third partition board 10, and two ends of the first ribs extend to the third edge strips 7;

and the second ribs 9 are arranged on the third partition board 10, are crossed with the first ribs 8, and extend to the third edge strips 7 from two ends.

for the dorsal fin structure of an aircraft disclosed in the above embodiments, it is easily understood by those skilled in the art that this design form of the first ribs 8 and the second ribs 9 can effectively carry and disperse the load transmitted from both sides of the rear end of the root, and has a good supporting function.

In some alternative embodiments, the tip structure 1 is formed as a unitary composite.

As for the dorsal fin structure of an aircraft disclosed in the above embodiments, it is easily understood by those skilled in the art that the tip structure 1 manufactured by integral molding of composite material can effectively reduce the mass and achieve weight reduction while satisfying the requirement of rigidity.

In some alternative embodiments, the tip structure 1 is in the form of a laminate.

in some alternative embodiments, the tip, end and side regions of the tip structure 1 are locally thickened.

with regard to the dorsal fin structure of an aircraft disclosed in the above embodiment, it is easily understood by those skilled in the art that the tip end, the tail end and the two side areas of the tip structure 1 are locally thickened, that is, the area where the tip structure 1 is used for being attached to the fuselage 13 and being butted with the middle structure 2 is thickened, so that on one hand, the overall capability of the tip structure 1 can be enhanced, and on the other hand, since only the local area is thickened, that is, the part of the tip structure 1 except the above area is thinner, the tip structure 1 has a lighter weight as a whole, and the optimal missing layer of the composite material layer can be performed during the manufacturing process.

In some alternative embodiments, the central structure 2 is made of composite material, wherein the central front end and the central rear end regions are locally thickened; the middle structure 2 is in a honeycomb sandwich structure in the areas of the middle front end, the middle rear end and between the two side edges;

The root structure 3 is made of composite material, and the front end of the root and the rear end area of the root are locally thickened; the root structure 3 has a honeycomb sandwich structure in the areas located at the middle front end, the middle rear end and between the two side edges.

So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.