CN111645884B - Frame honeycomb structure, honeycomb sandwich structure and fiber filling type protection configuration - Google Patents
Frame honeycomb structure, honeycomb sandwich structure and fiber filling type protection configuration Download PDFInfo
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- CN111645884B CN111645884B CN202010551374.8A CN202010551374A CN111645884B CN 111645884 B CN111645884 B CN 111645884B CN 202010551374 A CN202010551374 A CN 202010551374A CN 111645884 B CN111645884 B CN 111645884B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
Abstract
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.
Description
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.
(II) technical scheme
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
Length h of rectangular hole in vertical 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.
Example one
Referring to fig. 1 and 2, a framed honeycomb structure according to an embodiment of the present invention includes a plurality of honeycomb core cells 1, a rectangular hole 111 penetrating through each wall surface 11 is formed in a central position of each wall surface 11 of the honeycomb core cell 1, and sides of the rectangular hole 111 are parallel to sides of the wall surfaces 11 to form framed wall surfaces having a symmetrical structure. Each honeycomb cell 1 is formed from a plurality of the above-described frame-shaped walls 11. Each honeycomb structure is composed of a plurality of honeycomb core cells 1.
The rectangular hole 111 is disposed at the center of the wall surface 11, which means that the distance between each two opposite sides of the rectangular hole 111 and the side of the wall surface 11 adjacent to the same side is the same, and specifically, in fig. 2, on one wall surface 11, the distance between the left side of the rectangular hole 111 and the left side of the wall surface is the same as the distance between the right side of the rectangular hole 111 and the right side of the wall surface, and the distance between the upper side of the rectangular hole 111 and the upper side of the wall surface is the same as the distance between the lower side of the rectangular hole 111 and the lower side of the wall surface.
It should be noted that the center of the wall 11 of the present invention has a rectangular hole 111 penetrating through the wall 11, which is a specific description of the frame-type wall structure, and the frame-type wall 11 is not limited to the hole on the wall 11. In some embodiments, each wall 11 may be formed by combining two supporting portions 113 and two connecting portions 112, that is, two supporting portions 113 and two connecting portions 112 are combined in a split structure. Specifically, each wall surface 11 is formed by two support portions 113 with the same size, which are arranged in parallel at intervals, two connecting portions 112 are respectively arranged at two ends of each support portion 113 for connecting the two support portions 113, the two connecting portions 112 are arranged in parallel with the same size, and a rectangular interval (rectangular hole) is formed between the two connecting portions 112 and the two support portions 113, so as to form the frame-type wall surface 11. The support portion 113 disposed vertically mainly plays a supporting role in the structure, and the connection portion 112 mainly plays a connecting role in the structure.
Of course, in some embodiments, among the plurality of wall surfaces 11 constituting the honeycomb core cell 1, the contacting supporting portions 113 of two adjacent wall surfaces 11 may be an integral structure, taking the honeycomb core cell with a regular hexagonal cross section as an example, the integral structure includes six supporting portions 113 distributed along the circumference and arranged at intervals in parallel, and at the upper ends of the six supporting portions 113, a connecting portion 112 is arranged between two adjacent supporting portions 113, for a total of six connecting portions 112; at the lower ends of the six supporting portions 113, a connecting portion 112 is provided between two adjacent supporting portions 113, and six connecting portions 112 are formed to form the honeycomb core cell 1, in the above embodiment, the supporting portions 113 having corners are formed at an angle of 120 ° between every two adjacent supporting portions 113.
In some embodiments, the cross-section of the honeycomb core cell 1 may be in the shape of a diamond or a rectangle, etc., as desired, in addition to the regular hexagon which is used more frequently.
To is coming toIn order to better solve the channeling effect of the honeycomb structure and avoid the concentration of debris cloud, and simultaneously make the honeycomb structure have better structural strength, in some preferred embodiments, referring to fig. 2, the width a of the rectangular hole 111 in the horizontal direction1The ratio of the width a to the horizontal direction of the wall surface 11 is 0.8 to 0.95. Preferably, the length h of the rectangular hole 111 in the vertical direction1The ratio of the length h to the vertical direction of the wall surface 11 is in the range of 0.8-0.95.
In addition, because the honeycomb core cells 1 are all composed of the frame-type wall surfaces 11, the wall surface thickness can have larger thickness in the honeycomb structure with the same density, and the stability and the strength of the frame-type honeycomb structure are increased.
In some embodiments, the frame honeycomb structure is made of aluminum, titanium alloy, glass fiber reinforced plastic, aramid paper, plain paper, kraft paper, or graphite fiber.
Fig. 3 is a schematic top view of a frame honeycomb structure formed by bonding a plurality of honeycomb core cells 1 by a conventional bonding method. Fig. 4 is a schematic sectional view a-a of fig. 3. Referring to fig. 3 and 3, in a certain direction, two adjacent honeycomb core cells 1 have a wall surface 11 overlapped (see the portion indicated by a thick line in fig. 3), and the rectangular holes 111 of the two overlapped wall surfaces 11 are overlapped and penetrate through the two overlapped wall surfaces 11.
Example two
Referring to fig. 5 and fig. 6, the second embodiment is substantially the same as the first embodiment, and the description of the same parts is omitted, except that: the frame-type honeycomb structure in the second embodiment is manufactured by using a 3D printing technology, and the wall surface 11 can have a larger thickness without the wall surfaces 11 being overlapped together.
EXAMPLE III
In the honeycomb sandwich structure provided by this embodiment, the honeycomb core may adopt the frame honeycomb structure in any one of the first embodiment and the second embodiment, as shown in fig. 7, the upper and lower ends of the frame honeycomb structure are respectively bonded with a skin 2 to form the honeycomb sandwich structure.
Preferably, the material of the skin 2 may be aluminum, titanium alloy, glass fiber reinforced plastic, graphite fiber, or the like.
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.
Example four
Referring to fig. 8, the fiber-filled protective structure provided in this embodiment is located between the buffer layer 6 and the spacecraft bulkhead 5, and includes a fixed support 4 and a fiber-filled layer 3, where the fixed support 4 may adopt a frame honeycomb structure implemented in any one of the first embodiment and the second embodiment, the fiber-filled layer 3 is disposed at one end of the frame honeycomb structure close to the buffer layer 6, and the fiber-filled layer 3 is spaced from the buffer layer 6 by a distance at least twice the axial height of the frame honeycomb structure.
Preferably, the fiber filling layer 3 is a plurality of layers of ceramic fiber cloth and aramid fiber cloth which are alternately arranged.
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%.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: each embodiment does not include only one independent technical solution, and in the case of no conflict between the solutions, the technical features mentioned in the respective embodiments can be combined in any way to form other embodiments which can be understood by those skilled in the art.
Furthermore, modifications may be made to the technical solutions described in the foregoing embodiments, or equivalents may be substituted for some of the technical features thereof, without departing from the scope of the present invention, and the essence of the corresponding technical solutions does not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (5)
1. A fiber-filled protective structure between a cushioning layer and a spacecraft bulkhead, comprising a stationary support and a fiber-filled layer, characterized in that: the fixed supporting part is of a frame honeycomb structure, the fiber filling layer is arranged at one end, close to the buffer layer, of the frame honeycomb structure, and a gap is formed between the fiber filling layer and the buffer layer;
the frame honeycomb structure comprises a plurality of honeycomb core grids, wherein a rectangular hole penetrating through the wall surface is formed in the center of each wall surface of each honeycomb core grid, and the sides of the rectangular hole are parallel to the sides of the wall surface to form a frame type wall surface with a symmetrical structure.
2. The fiber-filled protective form of claim 1, wherein: the cross section of the honeycomb core lattice is a regular hexagon, a rhombus or a rectangle.
3. The fiber-filled protective form 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 fiber-filled protective form of claim 1, 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. The fiber-filled protective form according to any one of claims 1-4, wherein: the fiber filling layer is formed by alternately arranging a plurality of layers of ceramic fiber cloth and aramid fiber cloth.
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| CN202010551374.8A CN111645884B (en) | 2020-06-17 | 2020-06-17 | Frame honeycomb structure, honeycomb sandwich structure and fiber filling type protection configuration |
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| CN202010551374.8A CN111645884B (en) | 2020-06-17 | 2020-06-17 | Frame honeycomb structure, honeycomb sandwich structure and fiber filling type protection configuration |
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| CN111645884B true CN111645884B (en) | 2021-11-19 |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112977894B (en) * | 2021-03-17 | 2022-04-19 | 航天科工空间工程发展有限公司 | Spacecraft buffer device |
| CN113653758B (en) * | 2021-08-18 | 2023-03-14 | 北京安达泰克科技有限公司 | Honeycomb structure |
| CN115180184A (en) * | 2022-08-08 | 2022-10-14 | 中国空气动力研究与发展中心超高速空气动力研究所 | Filling type protection structure |
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