阅读说明：本技术 一种框架蜂窝结构、蜂窝夹层结构及纤维填充式防护构型 (Frame honeycomb structure, honeycomb sandwich structure and fiber filling type protection configuration ) 是由 柯发伟 罗庆 黄洁 蒋伟 于 2020-06-17 设计创作，主要内容包括：本发明涉及航天器防护技术领域,尤其涉及一种框架蜂窝结构、蜂窝夹层结构及纤维填充式防护构型。框架蜂窝结构包括多个蜂窝芯格,所述蜂窝芯格的每个壁面的中心位置均具有一个贯穿所述壁面的矩形孔,所述矩形孔的边与所述壁面的边平行设置,形成结构对称的框架式壁面,能够有效解决蜂窝结构因沟道效应而不利碎片云扩散的问题,同时使蜂窝结构具有相对高的结构强度。蜂窝夹层结构,其蜂窝芯使用框架蜂窝结构,在保证相应结构强度的同时,能够有效解决蜂窝结构因沟道效应而不利碎片云扩散的问题,起到更好的支撑和防护效果。纤维填充式防护构型利用框架蜂窝结构对纤维填充层进行支撑和固定,起到更好的支撑和防护效果,并至少可减轻其附加重量50％。(The invention relates to the technical field of spacecraft protection, in particular to a frame honeycomb structure, a honeycomb sandwich structure and a fiber filling type protection configuration. The frame honeycomb structure comprises a plurality of honeycomb core grids, the central position of each wall surface of each honeycomb core grid is provided with a rectangular hole penetrating through the wall surface, the sides of the rectangular holes are parallel to the sides of the wall surfaces, the frame type wall surfaces with symmetrical structures are formed, the problem that the cloud of fragments of the honeycomb structure is unfavorable to diffuse due to the channeling effect can be effectively solved, and meanwhile, the honeycomb structure has relatively high structural strength. The honeycomb sandwich structure has the advantages that the honeycomb core of the honeycomb sandwich structure adopts the frame honeycomb structure, the problem that the cloud diffusion of fragments of the honeycomb structure is unfavorable due to the channel effect can be effectively solved while the strength of the corresponding structure is ensured, and better supporting and protecting effects are achieved. The fiber-filled protective structure utilizes the frame honeycomb structure to support and fix the fiber filling layer, thereby achieving better supporting and protective effects and reducing the additional weight by at least 50 percent.)

1. A frame honeycomb structure comprising a plurality of honeycomb core cells, characterized in that: the center position of each wall surface of the honeycomb core lattice is provided with a rectangular hole penetrating through the wall surface, and the sides of the rectangular hole are arranged in parallel with the sides of the wall surface to form a frame type wall surface with a symmetrical structure.

2. The frame cell structure of claim 1, wherein: the cross section of the honeycomb core lattice is a regular hexagon, a rhombus or a rectangle.

3. The frame cell structure of claim 1, wherein: the width a of the rectangular hole in the horizontal direction₁The ratio of the width a to the horizontal direction of the wall surface is 0.8-0.95; and/or

The length h of the rectangular hole in the vertical direction₁The ratio of the length h to the vertical direction of the wall surface ranges from 0.8 to 0.95.

4. The framed honeycomb structure according to any one of claims 1 to 3, wherein: the frame honeycomb structure is made of aluminum, titanium alloy, glass fiber reinforced plastic, aramid paper, common paper, kraft paper or graphite fiber.

5. A honeycomb sandwich structure characterized by: the frame honeycomb structure comprises the frame honeycomb structure as claimed in any one of claims 1 to 4, wherein a skin is bonded to each of the upper and lower ends of the frame honeycomb structure.

6. The honeycomb sandwich structure of claim 5, wherein: the skin is made of aluminum, titanium alloy, glass fiber reinforced plastic or graphite fiber.

7. The utility model provides a fibre filled formula protection configuration, is located between buffer screen and the spacecraft bulkhead, includes fixed support portion and fibre filling layer, its characterized in that: the fixed support part is the frame honeycomb structure of any one of claims 1 to 4, the fiber filling layer is arranged at one end of the frame honeycomb structure close to the buffer layer, and a space is arranged between the fiber filling layer and the buffer layer.

8. The honeycomb sandwich structure of claim 7, wherein: the fiber filling layer is formed by alternately arranging a plurality of layers of ceramic fiber cloth and aramid fiber cloth.

Technical Field

The invention relates to the technical field of spacecraft protection, in particular to a frame honeycomb structure, a honeycomb sandwich structure and a fiber filling type protection configuration.

Background

In order to ensure the safe operation of the in-orbit spacecraft, protection against space debris impact needs to be developed. The honeycomb sandwich structure is widely applied to a protection structure on a spacecraft due to higher strength-weight ratio and designability, and is used as a supporting structure and a protection structure on the spacecraft, and the honeycomb sandwich plate with the same surface density is inferior to a Whipple structure in impact energy absorption and dissipation characteristics.

The traditional Whipple protection structure consists of a buffer screen and a spacecraft cabin wall which are arranged at intervals, and the fiber filling type protection structure which is widely used at present is characterized in that a fiber filling layer is added between the buffer screen and the spacecraft cabin wall of the Whipple protection structure, and an aluminum alloy frame is used for fixing and supporting the Whipple protection structure, so that the Whipple protection structure has higher additional weight. Although the weight of the additional structure of the fiber filling layer can be reduced by 35% by adopting the traditional honeycomb structure as the fixing and supporting structure of the fiber filling layer, the honeycomb core grids have a convergence effect on fragment clouds, and the perforation damage of the cabin wall of the spacecraft is aggravated.

Disclosure of Invention

The invention aims to solve the problem that the damage of a rear wall perforation of a spaceflight bulkhead is aggravated due to the fact that the channel effect of a traditional honeycomb structure is not beneficial to the diffusion of fragment cloud in the existing spacecraft supporting structure or protective structure, and provides a frame honeycomb structure, a honeycomb sandwich structure and a fiber filling type protective structure.

In order to achieve the above object, in a first aspect, the present invention provides a framed honeycomb structure, which includes a plurality of honeycomb core cells, each of the walls of the honeycomb core cells has a rectangular hole passing through the wall at a central position, and sides of the rectangular hole are arranged in parallel with sides of the wall to form framed walls having a symmetrical structure.

Preferably, the honeycomb core cells are regular hexagonal, diamond shaped or rectangular in cross-section.

Preferably, the width a of the rectangular hole in the horizontal direction₁The ratio of the width a to the horizontal direction of the wall surface is 0.8-0.95; and/or

The vertical direction of the rectangular holeLength h of direction₁The ratio of the length h to the vertical direction of the wall surface ranges from 0.8 to 0.95.

Preferably, the material of the frame honeycomb structure is aluminum, titanium alloy, glass fiber reinforced plastic, aramid paper, common paper, kraft paper or graphite fiber.

In a second aspect, the present invention further provides a honeycomb sandwich structure, which may include any one of the frame honeycomb structures described in the first aspect, wherein a skin is bonded to each of upper and lower ends of the frame honeycomb structure.

Preferably, the skin is made of aluminum, titanium alloy, glass fiber reinforced plastic or graphite fiber.

In a third aspect, the present invention further provides a fiber-filled protective structure, located between the buffer layer and the spacecraft bulkhead, including a fixing support and a fiber-filled layer, where the fixing support can be any one of the frame honeycomb structures described in the first aspect, the fiber-filled layer is disposed at one end of the frame honeycomb structure close to the buffer layer, and a space is provided between the fiber-filled layer and the buffer layer.

Preferably, the fiber filling layer is a plurality of layers of ceramic fiber cloth and aramid fiber cloth which are alternately arranged.

The technical scheme of the invention has the following advantages: the frame honeycomb structure provided by the invention comprises a plurality of honeycomb core grids, wherein the center of each wall surface of each honeycomb core grid is provided with a rectangular hole penetrating through the wall surface, the sides of the rectangular holes are arranged in parallel with the sides of the wall surfaces to form a frame type wall surface with a symmetrical structure, the problem that debris cloud diffusion is not facilitated due to a channel effect of the honeycomb structure can be effectively solved, and meanwhile, the honeycomb structure has relatively high structural strength.

In addition, compared with the traditional honeycomb structure, the frame type honeycomb structure can have a wall surface with larger thickness under the same density, and the structural strength of the frame type honeycomb structure can be selectively increased according to needs.

According to the honeycomb sandwich structure provided by the invention, the honeycomb core adopts the frame honeycomb structure, so that the problem that the fragments of the honeycomb structure are difficult to diffuse due to a channel effect can be effectively solved while the strength of the corresponding structure is ensured, and better supporting and protecting effects are achieved.

According to the fiber filling type protection structure provided by the invention, the fiber filling layer is supported and fixed by utilizing the frame honeycomb structure, the problem that the diffusion of fragments is not facilitated due to the channel effect of the honeycomb structure can be effectively solved, the better supporting and protecting effects are achieved, and the additional weight of the fiber filling type protection structure can be at least reduced by 50%.

Drawings

The drawings of the present invention are provided for illustrative purposes only, and the proportion and the number of the components in the drawings do not necessarily correspond to those of an actual product.

FIG. 1 is a schematic view of a honeycomb core cell structure of a frame honeycomb structure according to an embodiment of the present invention;

FIG. 2 is another perspective view of a honeycomb core cell structure of a frame honeycomb structure according to one embodiment of the present invention;

FIG. 3 is a schematic top view of a honeycomb structure of a frame honeycomb structure according to one embodiment of the present invention;

FIG. 4 is a schematic sectional view A-A of FIG. 3;

FIG. 5 is a schematic top view of a honeycomb structure of a frame honeycomb structure according to a second embodiment of the present invention;

FIG. 6 is a schematic view B-B of FIG. 5;

FIG. 7 is a schematic view of a honeycomb sandwich structure according to a third embodiment of the present invention;

fig. 8 is a schematic structural view of a fiber-filled protective configuration in accordance with a fourth embodiment of the present invention.

In the figure: 1: a honeycomb core grid; 11: a wall surface; 111: a square hole; 112: a connecting portion; 113: a support portion; 2: covering a skin; 3: a fiber-filled layer; 4: a fixed support part; 5: a spacecraft bulkhead; 6: a buffer layer.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.