阅读说明：本技术 一种基于网格结构的整流罩 (Fairing based on grid structure ) 是由 季宝锋 王志勇 刘含洋 唐占文 刘千 金�一 王非 刘发杰 张鹏 李世伟 于 2020-06-04 设计创作，主要内容包括：本发明的实施例提供一种基于网格结构的整流罩,包括：整流罩本体,所述整流罩本体包括斜置格栅结构和设置在所述斜置格栅结构外部的蒙皮结构,所述整流罩本体的连接端设置有分离螺栓盒。本发明的整流罩本体的内部为格栅结构,解决了现有整流罩重量大、刚度低、河蚌对接缝需要热密封等问题。本发明的基于固体运载火箭拔罩分离方式的整体式、超轻质整流罩,相对于现有结构减重30％以上。(An embodiment of the present invention provides a fairing based on a mesh structure, including: the fairing body comprises an inclined grid structure and a skin structure arranged outside the inclined grid structure, and a separation bolt box is arranged at the connecting end of the fairing body. The fairing body is of a grid structure, and the problems that the existing fairing is heavy in weight and low in rigidity, and freshwater mussels need to be subjected to heat sealing on seams and the like are solved. Compared with the existing structure, the integrated ultra-light fairing based on the solid carrier rocket draft hood separation mode reduces weight by more than 30%.)

1. A fairing based on a lattice construction, comprising: the fairing comprises a fairing body (1), wherein the fairing body (1) comprises an inclined grid structure (11) and a skin structure (12) arranged outside the inclined grid structure (11), and a connecting end (13) of the fairing body (1) is provided with a separation bolt box (2).

2. The fairing based on a lattice structure as claimed in claim 1, wherein said slanted grid structure (11) is a rhomboid grid with equal pitch or a triangular grid with equal pitch.

3. The fairing based on lattice structure as claimed in claim 1, characterized in that the front end (14) of the fairing body (1) is provided with at least one mounting opening (3) for mounting a pull-out rocket.

4. The fairing based on lattice structure as recited in claim 3, characterised in that said mounting openings (3) comprise two mounting openings or four mounting openings, which are arranged symmetrically with respect to a radial axis of said fairing body (1).

5. The fairing based on a lattice structure as recited in claim 1, characterised in that the connection end (13) of the fairing body (1) has a circumferentially arranged L-shaped end frame (15), the split bolt box (2) being fixedly connected to the L-shaped end frame (15).

6. The mesh structure based fairing according to claim 5, characterized in that said split bolt box (2) comprises: a bottom surface (21), a side wall (22) formed integrally with the bottom surface (21); the bottom surface (21) and the side wall (22) are fixedly connected with the L-shaped end frame (15);

the bottom surface (21) is provided with first reinforcing ribs (23) and second reinforcing ribs (24) which are arranged at intervals, and bolt holes (25) for connecting separating bolts are formed in the bottom surface between the first reinforcing ribs (23) and the second reinforcing ribs (24).

7. The fairing based on grid structure as recited in claim 6, characterised in that said bottom surface (21) and said side walls (22) are fixedly connected to said L-shaped end frame (15) by means of fasteners.

8. The fairing based on lattice structure as recited in claim 5, characterised in that said split bolt boxes (2) are 6 and evenly distributed on said L-shaped end frame (15).

9. The fairing based on a lattice structure as claimed in claim 1, characterised in that said slanted grid structure (11) and said skin structure (12) have the same shape and are each a spindle-shaped flow-linear structure.

10. The fairing based on lattice structure as recited in claim 1, characterised in that said fairing body (1) is made of one or more of carbon fibre composite material, glass fibre composite material, high strength aluminium alloy.

Technical Field

The invention relates to the technical field of aircrafts, in particular to a fairing based on a grid structure.

Background

The fairing is positioned at the foremost end of the carrier rocket and is used for protecting the safety of products such as internal satellites, airships, detectors and the like conveyed by the rocket in the process of flying the rocket. In order to improve the carrying capacity of the rocket and ensure the integral stability of the carrier rocket, the design of the rocket fairing requires ultra-light weight and high rigidity. Regardless of liquid rockets or solid rockets, the overall structure of the fairing is generally streamline to adapt to aerodynamics, and the fairing is generally divided into an integral fairing and a split fairing according to different fairing separation modes.

At present, the fairing used for the liquid carrier rocket is mainly of a split clam type structure, and the fairing applied to the solid rocket basically adopts the scheme of the fairing of the liquid rocket and is also of a split type. Because the diameter of the solid rocket is smaller than that of the liquid rocket, the split structure is additionally provided with a longitudinal butt joint frame, a separation structure and the like, so that the rocket fairing is heavier, in a fairing structure system, the weight of the fairing body is very light, and the structure of an additional system is very heavy, so that the service efficiency of the fairing is greatly influenced.

Disclosure of Invention

The technical problem to be solved by the invention is to provide a fairing based on a grid structure, and the problems of heavy weight and low use efficiency of the fairing in the prior art are solved.

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

a mesh structure based fairing comprising: the fairing body comprises an inclined grid structure and a skin structure arranged outside the inclined grid structure, and a separation bolt box is arranged at the connecting end of the fairing body.

Preferably, the inclined grid structure is a rhombic grid with equal edge distance or a triangular grid with equal edge distance.

Preferably, the front end of the fairing body is provided with at least one mounting opening for mounting the pull-out separation rocket.

Preferably, the mounting openings include two mounting openings or four mounting openings, and the two mounting openings or the four mounting openings are symmetrically arranged about a radial axis of the fairing body.

Preferably, the connecting end of the fairing body is provided with an L-shaped end frame arranged annularly, and the separation bolt box is fixedly connected with the L-shaped end frame.

Preferably, the split bolt housing comprises: a bottom surface, a sidewall integrally formed with the bottom surface; the bottom surface and the side wall are both fixedly connected with the L-shaped end frame;

the bottom surface is provided with a first reinforcing rib plate and a second reinforcing rib plate which are arranged at intervals, and a bolt hole for connecting a separation bolt is formed in the bottom surface between the first reinforcing rib plate and the second reinforcing rib plate.

Preferably, the bottom surface and the side wall are fixedly connected with the L-shaped end frame through fasteners.

Preferably, the number of the separation bolt boxes is 6, and the separation bolt boxes are uniformly distributed on the L-shaped end frame.

Preferably, the shape of the inclined grid structure is the same as that of the skin structure, and the inclined grid structure and the skin structure are both in a spindle flow linear structure.

Preferably, the fairing body is made of one or more materials of carbon fiber composite materials, glass fiber composite materials and high-strength aluminum alloy.

In the scheme of the invention, the inside of the fairing body is of a grid structure, and the integral ultra-light fairing based on the solid carrier rocket hood-pulling separation mode reduces weight by more than 30% compared with the existing structure, has high integral rigidity, simple manufacture and assembly, high reliability, good manufacturability and good product consistency, is suitable for the high-temperature use environment requirement of the fairing, and is particularly suitable for batch production.

Drawings

FIG. 1 is a first view of the overall construction of the fairing of the present invention;

FIG. 2 is a first view of the fairing of the present invention in section;

FIG. 3 is a second view of the fairing of the present invention in section;

FIG. 4 is a second view of the overall fairing construction of the present invention;

FIG. 5 is a third view of the fairing of the present invention in section;

fig. 6 is a schematic structural view of the split bolt kit of the present invention.

Description of reference numerals:

1- -fairing body; 11- -a grid construction; 12- -skin construction; 13- -connecting end; 14- -front end; 15-L-shaped end frame;

2- -separation bolt box; 21- -bottom surface; 22- -side wall; 23- -a first reinforcing floor; 24- -a second reinforcing floor; 25- -bolt hole;

3- -mounting opening.

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 to 6, an embodiment of the present invention provides a fairing based on a mesh structure, including: the fairing body 1 comprises an inclined grille structure 11 and a skin structure 12 arranged outside the inclined grille structure 11, and a connecting end 13 of the fairing body 1 is provided with a separation bolt box 2. The fairing body is of a grid structure, and the problems that the existing fairing is heavy in weight and low in rigidity, and freshwater mussels need to be subjected to heat sealing on seams and the like are solved. The invention is an integral ultra-light fairing based on a solid carrier rocket hood-pulling separation mode, and reduces weight by more than 30% compared with the existing structure.

Referring to fig. 4 and 5, the fairing body 1 is an integral structure in the form of an inclined grid structure, and the inclined grid is a rhombus grid with equal pitch or a triangular grid with equal pitch, so that the outer pressure bearing capacity is the strongest. The typical skin-grid structure form, local structures such as grids, skins, end frames and the like are manufactured in a unified mode. The inclined grid structure 11 of the invention is a rhombus grid with equal edge distance or a triangular grid with equal edge distance, and can also be other grid structures, and the weight can be greatly reduced by adopting the grid structure, thereby being beneficial to improving the competitive advantage of products.

The cowl body 1 of the present invention is provided at the front end 14 thereof with at least one mounting hole 3 for mounting a pull-out rocket. Preferably, the mounting openings 3 include two mounting openings or four mounting openings, and the two mounting openings or the four mounting openings are symmetrically arranged about a radial axis of the fairing body 1.

As shown in fig. 6, the connecting end 13 of the cowl body 1 of the present invention has an L-shaped end frame 15 that is circumferentially provided, and the split bolt case 2 is fixedly connected to the L-shaped end frame 15. Preferably, the split bolt housing 2 includes: the bottom surface 21 and the side wall 22 are integrally formed with the bottom surface 21, and the bottom surface 21 and the side wall 22 are fixedly connected with the L-shaped end frame 15; first reinforcement ribs 23 and second reinforcement ribs 24 are provided at intervals on the bottom surface 21, and bolt holes 25 for separate bolt connection are provided on the bottom surface between the first reinforcement ribs 23 and the second reinforcement ribs 24. Preferably, the bottom surface 21 and the side wall 22 are fixedly connected to the L-shaped end frame 15 by fasteners. The part of the invention has the characteristics of high bearing capacity and separation impact resistance.

The number of the separate bolt boxes 2 is 6, and the separate bolt boxes are uniformly distributed on the L-shaped end frame 15. The bolt connecting hole is arranged on the inner wall of the rear end of the fairing body 1. The number of the separation bolt boxes 2 is determined according to the separation requirement, and the separation bolt boxes are mounted on the inner side of the rear end of the fairing body 1 through fasteners such as bolts or rivets and are mainly used for connection and separation of the fairing and the rear end cabin section. The rear section of the fairing structure is provided with 6 separating bolt connecting holes for installing and penetrating separating bolts, the separating bolt box is a connecting surface of the separating bolts, and the other separating bolt box is connected to the rear section connecting cabin section of the product. The front section of the fairing body 1 is provided with 2 mounting ports 3 for mounting a pull-out separation rocket which is generally a small solid rocket.

The inclined grid structure 11 and the skin structure 12 have the same shape and are both spindle flow linear structures. Preferably, the fairing body 1 is made of one or more of carbon fiber composite material, glass fiber composite material and high-strength aluminum alloy.

The invention is in a typical skin-grid structure form, and local structures such as grids, skins, end frames and the like are manufactured in a unified mode. The product manufacturing material can be selected from carbon fiber composite materials, glass fiber composite materials, high-strength aluminum alloy and other light materials. If the composite material is used for manufacturing, the high-temperature resistant resin base material is used, so that the whole product has the characteristic of high-temperature use resistance.

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.