阅读说明：本技术 一种基于正交网格结构的整流罩 (Radome fairing based on orthogonal 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正交网格结构的整流罩,包括：整流罩本体,所述整流罩本体包括正交网络结构和设置在所述正交网格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环。本发明的整流罩本体的内部为正交网格结构,解决了现有整流罩重量大、刚度低、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 an orthogonal grid structure, including: the fairing body comprises an orthogonal network structure and a skin structure arranged outside the orthogonal network structure, and a separating ring is arranged at the connecting end of the fairing body. The interior of the fairing body is of an orthogonal grid structure, so that the problems that the existing fairing is heavy in weight, low in rigidity, and the joint seam needs to be sealed by heat 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 an orthogonal grid structure, comprising: the fairing body (1) comprises an orthogonal grid structure (11) and a skin structure (12) arranged outside the orthogonal grid structure (11), and a connecting end (13) of the fairing body (1) is provided with a separating ring (2).

2. The fairing based on a grid structure as claimed in claim 1, characterised in that said orthogonal grid structure (11) is a square grid of equal pitch.

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

5. The fairing based on orthogonal grid structure as recited in claim 1, characterised in that said separating ring (2) is of an out-of-plane T-shaped configuration.

6. The fairing based on orthogonal grid structure as recited in claim 5, characterised in that said separating ring (2) comprises: butt joint end (21), installation end (25) of being connected with radome body (1), the inboard of butt joint end (21) is provided with hoop frame (22), keeps off platform (23), the outside of installation end (25) is provided with weakens groove (24).

7. The fairing based on orthogonal grid structure as recited in claim 6, characterised in that said weakening grooves (23) are two and are evenly arranged outside the mounting end (25).

8. The orthogonal grid structure-based fairing as recited in claim 6, wherein said abutment (23) is spaced from said mounting end (25).

9. The fairing based on orthogonal grid structure as claimed in claim 1, characterised in that said orthogonal grid structure (11) and said skin structure (12) are identical in shape, both being a spindle-shaped flow-linear structure.

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

Technical Field

The invention relates to the technical field of aircrafts, in particular to a fairing based on an orthogonal 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. The fairings currently used in liquid launch vehicles are primarily of a split clam-type construction. The fairing applied to the solid rocket basically adopts the scheme of a liquid rocket fairing at present and is also in 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 an orthogonal 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:

the fairing based on the orthogonal grid structure comprises a fairing body, wherein the fairing body comprises the orthogonal grid structure and a skin structure arranged outside the orthogonal grid structure, and a connecting end of the fairing body is provided with a separating ring.

Preferably, the orthogonal grid structure is a square 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 section of the separating ring is of an out-of-plane T-shaped structure.

Preferably, the separating ring comprises: butt joint end, installation end of being connected with the radome body, the inboard of butt joint end is provided with hoop frame, keeps off the platform, the outside of installation end is provided with weakens the groove.

Preferably, the weakening grooves are two and are uniformly arranged on the outer side of the mounting end.

Preferably, the blocking platform is arranged at a gap from the mounting end.

Preferably, the orthogonal grid structure and the skin structure have the same shape and are both spindle flow linear structures.

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 interior of the fairing body is of an orthogonal 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 schematic view of a split ring configuration of the present invention;

fig. 5 is a cross-sectional view of a split ring of the present invention.

Description of reference numerals:

1- -fairing body; 11- -orthogonal grid structure; 12- -skin construction; 13- -connecting end; 14- -front end;

2- -separation ring; 21- -butt end; 22-circumferential frame; 23- -stop table; 24- -weakening groove; 25- -mounting end;

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 5, an embodiment of the present invention provides a fairing based on an orthogonal grid structure, including: the fairing body 1 comprises an orthogonal grid structure 11 and a skin structure 12 arranged outside the orthogonal grid structure 11, and a separating ring 2 is arranged at a connecting end 13 of the fairing body 1. The separating ring 2 is installed on the inner side of the connecting end 13 of the fairing body 1 through bolts, rivets and other fasteners in an inserting mode and is mainly used for connecting and separating a fairing and a rear-end cabin section. The separating ring 2 is a connecting surface of a line type separating structure, and the other separating ring is connected to a rear section connecting cabin section.

The fairing body is an integral structure in an orthorhombic grid structure form, and has the strongest axial pressure bearing capacity. The inside of radome fairing body is orthogonal grid structure, has solved current radome fairing weight big, rigidity is low, freshwater mussel needs heat seal scheduling problem to the seam. 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. 2 and 3, the fairing body 1 is a unitary structure in the form of an orthogonal grid structure, preferably, the orthogonal grid structure 11 is a square grid with equal pitch, and has the highest external pressure bearing capacity. The typical skin-grid structure form, local structures such as grids, skins, end frames and the like are manufactured in a unified mode.

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 opening 3 is an elliptical hood-removed rocket mounting opening for mounting a hood-removed breakaway rocket, which is typically a small solid rocket; the mounting openings 3 may comprise two mounting openings or four mounting openings, which are arranged symmetrically with respect to a radial axis of the fairing body 1.

As shown in fig. 4 and 5, the cowl body 1 of the present invention has a separating ring 2 provided at the connecting end 13, and the separating ring 2 has a cross-section of a T-shaped structure having a different surface for connecting the cowl with the rear portion while taking into consideration the effect of the mounting line type separation, which is a cowl separating surface. The separation ring 2 of the present embodiment includes: the fairing comprises a butt joint end 21 and a mounting end 25 which are connected with the connecting end 13 of the fairing body 1, wherein the butt joint end 21 is in forked butt joint with the connecting end 13 of the fairing body 1, the inner side of the butt joint end 21 is provided with a hoop frame 22 and a baffle table 23, the outer side of the mounting end 25 is provided with weakening grooves 24, the weakening grooves are two, and the weakening grooves are uniformly arranged on the outer side of the mounting end 25.

The inboard installation line formula separation initiating explosive device and the separation safety cover that weaken groove 24, when initiating explosive device explosive work, the separating ring is wholly cut by the annular in twice weak trench position to realize the lateral separation of radome fairing, initiating explosive device work separation back, under the effect of rocket, can take the radome fairing from the rocket body, realize that the radome fairing is thrown away.

In order to install the protective cover required by the separation initiating explosive device, the annular frame 22 and the separation protective cover baffle table 23 are arranged on the inner side of the separation ring 2, the baffle table 23 and the inner side gap of the installation end 25 are arranged, the annular frame 22 is used for increasing the annular rigidity of the separation ring, and the separation protective cover baffle table 23 is used for blocking the radial movement of the separation initiating explosive device protective cover on the fairing, so that the energy of the initiating explosive device is all applied to the annular weakening groove part, and the separation reliability is ensured.

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 orthogonal 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.