CN110104223B - Outer armor of spatial equipment based on flexible structure - Google Patents
Outer armor of spatial equipment based on flexible structure Download PDFInfo
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- CN110104223B CN110104223B CN201910499868.3A CN201910499868A CN110104223B CN 110104223 B CN110104223 B CN 110104223B CN 201910499868 A CN201910499868 A CN 201910499868A CN 110104223 B CN110104223 B CN 110104223B
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- flexible
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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
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- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention belongs to the technical field of space equipment protection, and particularly relates to an outer armor of space equipment based on a flexible structure. The flexible pressure-bearing unit comprises a module base, a pressure-bearing surface and a plurality of flexible pressure-bearing arms connected between the module base and the pressure-bearing surface, wherein the flexible pressure-bearing arms are uniformly distributed along the circumferential direction, and the module base is connected with space equipment. The invention is used for spacecrafts (space stations, satellites and the like) in space for a long time, reduces external impact, and prevents the spacecrafts from being damaged by small meteorites or other space garbage collisions.
Description
Technical Field
The invention belongs to the technical field of space equipment protection, and particularly relates to an outer armor of space equipment based on a flexible structure.
Background
Space books are a vast, unbiased space but increasingly crowded due to frequent human activities. Space garbage is space debris generated by human space activities, including rocket bodies, satellite bodies, rocket ejectors for completing tasks, throws and discards in the process of executing space tasks, fragments generated by space object collision and the like, and is a main pollution source of space environment. Space debris is a "natural enemy" of spacecraft and satellites, and even a slight collision can cause significant damage. A piece of space debris that is only large with the aspirin tablet can also crash the satellite into "scrap".
Since the first satellite in 1957 was lifted off, humans have launched 5000 or more various types of spacecraft into space, a significant portion of which has become space debris to float on the near-earth orbit. Currently, more than 4000 tens of thousands of space debris can be observed and recorded on the ground to form about 3000 tons of space garbage, and the space garbage is still increasing year by year. The largest fragment observed corresponds to a bus and the smallest corresponds to a softball.
Avoidance of space debris is almost a "prescribed action" for various spacecraft, satellites, and international space stations. The international space station adjusts the flight orbit and the altitude for many times in the last year, and the orbit is adjusted twice within three weeks most frequently, so that space debris is avoided.
In order to avoid space garbage, international space stations often change the flight attitude. In order to avoid the attack of space debris, the existing space plane in the United states is small in size, and the flight time is greatly reduced when the space plane performs tasks, which is only a few days to tens of days. Even so, they have changed flight attitude many times because of the avoidance of space debris. However, the energy expended to avoid flight and the costs paid are both very costly.
Disclosure of Invention
Aiming at the problems, the invention aims to provide the outer armor of the space equipment based on the flexible structure, which can bear the physical impact of space garbage, has strong pressure bearing capacity, low cost and is easy to install.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
the utility model provides an outer armor of spatial equipment based on flexible structure, includes a plurality of flexible pressure-bearing units, flexible pressure-bearing unit includes module base, pressure-bearing face and connects a plurality of flexible pressure-bearing arms between module base and the pressure-bearing face, a plurality of flexible pressure-bearing arms are along circumference equipartition, module base is connected with spatial equipment.
A plurality of connecting blocks are arranged below the pressure-bearing surface along the circumferential direction, and a plurality of flexible pressure-bearing arms are respectively connected with a plurality of connecting blocks.
The flexible pressure-bearing arm comprises a flexible supporting arm and a connecting rod supporting mechanism, wherein the upper end of the flexible supporting arm is fixedly connected with the connecting block, the lower end of the flexible supporting arm is in butt joint with the module base, the connecting rod supporting mechanism is arranged on the outer side of the flexible supporting arm, the lower end of the connecting rod supporting mechanism is fixedly connected with the module base, and the upper end of the connecting rod supporting mechanism is hinged with the connecting block.
The lower extreme of flexible support arm be equipped with the bottom sprag face of module base laminating.
The connecting rod supporting mechanism comprises a module supporting arm and a supporting rod, wherein one end of the supporting rod is fixedly connected with the module base, the other end of the supporting rod is hinged with one end of the module supporting arm, and the other end of the module supporting arm is hinged with the connecting block.
The module support arms are two and symmetrically arranged on two sides of the support rod, module support arm hinge holes are formed in two ends of the module support arms, module support arm hinge holes at the lower end are connected with support rod hinge holes formed in the support rod through bolts, and module support arm hinge holes at the upper end are rotatably connected with hinge shafts on two sides of the connecting block.
The upper end of the supporting rod is arranged in an outward inclined mode.
The top of the pressure-bearing surface is of an arc-shaped structure protruding outwards.
The size of the pressure bearing surface is equal to that of the module base.
And the module base is provided with a mounting hole for being connected with space equipment.
The invention has the advantages that:
1. the invention can effectively bear physical impact from all directions in space.
2. The invention has simple disassembly and assembly, the base of each unit is provided with a clamping groove structure, and the installation and the replacement are convenient.
3. The invention has lower cost per unit.
4. The invention can be arranged at different positions according to specific requirements, and can be fully covered when the requirements are high.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is an enlarged view of the portion I of FIG. 1;
FIG. 3 is a schematic view of the structure of the flexible pressure-bearing unit of the present invention;
FIG. 4 is a schematic view of the structure of the module base of the present invention;
FIG. 5 is a schematic view of a support arm according to the present invention;
FIG. 6 is a schematic view of a flexible support arm according to the present invention;
fig. 7 is a schematic structural view of the bearing surface in the present invention.
In the figure: 1 is a module base, 2 is a module supporting arm, 3 is a bolt, 4 is a flexible supporting arm, 5 is a pressure-bearing surface, 6 is a supporting rod, 7 is a supporting rod hinge hole, 8 is a module supporting arm hinge hole, 9 is a bottom supporting surface, 10 is a connecting block, 11 is a hinge shaft, 12 is a connecting shaft, 13 is a connecting hole, 14 is a flexible pressure-bearing arm, 15 is a mounting hole, and A is a flexible pressure-bearing unit.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in detail with reference to the accompanying drawings and specific embodiments.
As shown in fig. 1-2, the space equipment external armor based on the flexible structure provided by the invention comprises a plurality of flexible pressure-bearing units a, wherein each flexible pressure-bearing unit a comprises a module base 1, a pressure-bearing surface 5 and a plurality of flexible pressure-bearing arms 14 connected between the module base 1 and the pressure-bearing surface 5, the plurality of flexible pressure-bearing arms 14 are uniformly distributed along the circumferential direction, and the module base 1 is connected with the space equipment.
As shown in fig. 3, a plurality of connection blocks 10 are provided circumferentially below the pressure-receiving surface 5, and a plurality of flexible pressure-receiving arms 14 are connected to the plurality of connection blocks 10, respectively.
The flexible pressure-bearing arm 14 comprises a flexible supporting arm 4 and a connecting rod supporting mechanism, wherein the upper end of the flexible supporting arm 4 is fixedly connected with the connecting block 10, the lower end of the flexible supporting arm is in butt joint with the module base 1, the connecting rod supporting mechanism is arranged on the outer side of the flexible supporting arm 4, the lower end of the connecting rod supporting mechanism is fixedly connected with the module base 1, and the upper end of the connecting rod supporting mechanism is hinged with the connecting block 10.
Further, the lower end of the flexible support arm 4 is provided with a bottom support surface 9 which is attached to the module base 1, as shown in fig. 6. The bottom support surface 9 is slidable relative to the module base 1 to avoid over loading to crush the flexible support arm 4. The flexible supporting arm 4 is a main bearing device, and the flexible structure cut by the wire cutting process can be made of titanium alloy or 316L stainless steel.
The connecting rod supporting mechanism comprises a module supporting arm 2 and a supporting rod 6, wherein one end of the supporting rod 6 is fixedly connected with the module base 1, the other end of the supporting rod is hinged with one end of the module supporting arm 2, and the other end of the module supporting arm 2 is hinged with a connecting block 10.
In the embodiment of the invention, two module support arms 2 are symmetrically arranged on two sides of the support rod 6, and two module support arms 2 are arranged on each support rod 6 to improve stability.
As shown in fig. 4, the upper end of the supporting rod 6 is provided with a supporting rod hinge hole 7, and the upper end is inclined outwards, and the module base 1 is provided with a mounting hole 15 for connecting with space equipment, so that the module base is convenient to connect with the space equipment, and even if a certain unit or part of the unit is damaged, the module base is convenient to replace. The number of the distributed flexible pressure-bearing units A can be controlled at will according to different use positions.
As shown in fig. 5, both ends of the module support arm 2 are provided with module support arm hinge holes 8. As shown in fig. 6, the bottom of the connecting block 10 is fixedly connected with the upper end of the flexible supporting arm 4, the top is provided with a connecting shaft 12 fixedly connected with the pressure-bearing surface 5, and the left and right sides of the connecting block 10 are symmetrically provided with hinge shafts 11.
The module support arm hinge hole 8 at the lower end of the module support arm 2 is connected with the support rod hinge hole 7 arranged on the support rod 6 through the bolt 3, and the module support arm hinge hole 8 at the upper end is rotationally connected with the hinge shafts 11 at the two sides of the connecting block 10.
As shown in fig. 7, the top of the pressure-bearing surface 5 has an arc structure protruding outwards, and the arc structure at the upper part can disperse a part of the external force. The bottom of the pressure-bearing surface 5 is provided with a mounting hole for connection with the connecting shaft 12 at the top of the connecting block 10. The size of the pressure bearing surface 5 is equal to that of the module base 1 so as to ensure that the modules can be spliced seamlessly.
In the embodiment of the invention, each flexible pressure-bearing unit A is uniformly distributed by the circumferences of four identical flexible pressure-bearing arms 14, the total volume of the structure is 40 x 30mm, the volume is small, the pressure-bearing capacity is strong, and the replacement is convenient.
The invention relates to a buffer module capable of bearing physical impact in space, each module is provided with a small shield and is connected with a flexible pressure-bearing structure, so that the reliability of the module is enhanced.
The invention is used for spacecrafts (space stations, satellites and the like) in space for a long time, reduces external impact, and prevents the spacecrafts from being damaged by small meteorites or other space garbage collisions. The invention is based on a flexible structure, so the volume is small, the whole body can be installed, and a local pressure-bearing device can be also manufactured, and when the impact approaches, the device moves to the corresponding position (the mechanical arm moves). The unit of the invention has simple structure, can emit for small satellites at one time, and space stations can emit for multiple times and then splice.
The foregoing is merely an embodiment of the present invention and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, expansion, etc. made within the spirit and principle of the present invention are included in the protection scope of the present invention.
Claims (7)
1. The outer armor of the space equipment based on the flexible structure is characterized by comprising a plurality of flexible pressure-bearing units (A), wherein each flexible pressure-bearing unit (A) comprises a module base (1), a pressure-bearing surface (5) and a plurality of flexible pressure-bearing arms (14) connected between the module base (1) and the pressure-bearing surface (5), the plurality of flexible pressure-bearing arms (14) are uniformly distributed along the circumferential direction, and the module base (1) is connected with the space equipment;
a plurality of connecting blocks (10) are arranged below the pressure-bearing surface (5) along the circumferential direction, and a plurality of flexible pressure-bearing arms (14) are respectively connected with the plurality of connecting blocks (10);
the flexible pressure-bearing arm (14) comprises a flexible supporting arm (4) and a connecting rod supporting mechanism, wherein the upper end of the flexible supporting arm (4) is fixedly connected with the connecting block (10), the lower end of the flexible supporting arm is in butt joint with the module base (1), the connecting rod supporting mechanism is arranged on the outer side of the flexible supporting arm (4), the lower end of the connecting rod supporting mechanism is fixedly connected with the module base (1), and the upper end of the connecting rod supporting mechanism is hinged with the connecting block (10);
the top of the pressure-bearing surface (5) is of an arc-shaped structure protruding outwards.
2. The outer armor of a space device based on a flexible structure according to claim 1, characterized in that the lower end of the flexible support arm (4) is provided with a bottom support surface (9) which is in abutment with the module base (1).
3. The flexible structure-based space equipment external armor according to claim 1, wherein the connecting rod supporting mechanism comprises a module supporting arm (2) and a supporting rod (6), wherein one end of the supporting rod (6) is fixedly connected with the module base (1), the other end of the supporting rod is hinged with one end of the module supporting arm (2), and the other end of the module supporting arm (2) is hinged with the connecting block (10).
4. The flexible structure-based space equipment external armor according to claim 3, wherein the number of the module support arms (2) is two, the module support arms are symmetrically arranged on two sides of the support rod (6), the two ends of the module support arms (2) are respectively provided with a module support arm hinge hole (8), the module support arm hinge holes (8) positioned at the lower end are connected with the support rod hinge holes (7) arranged on the support rod (6) through bolts (3), and the module support arm hinge holes (8) positioned at the upper end are rotationally connected with hinge shafts (11) on two sides of the connecting block (10).
5. A flexible construction based space equipment external armor according to claim 3, characterized in that the upper end of the support bar (6) is arranged inclined outwards.
6. The flexible structure based space equipment external armor according to claim 1, characterized in that the pressure bearing face (5) is of equal size to the module base (1).
7. The flexible structure-based space equipment external armor according to claim 1, characterized in that the module base (1) is provided with mounting holes (15) for connection with space equipment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910499868.3A CN110104223B (en) | 2019-06-11 | 2019-06-11 | Outer armor of spatial equipment based on flexible structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910499868.3A CN110104223B (en) | 2019-06-11 | 2019-06-11 | Outer armor of spatial equipment based on flexible structure |
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| Publication Number | Publication Date |
|---|---|
| CN110104223A CN110104223A (en) | 2019-08-09 |
| CN110104223B true CN110104223B (en) | 2023-08-08 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910499868.3A Active CN110104223B (en) | 2019-06-11 | 2019-06-11 | Outer armor of spatial equipment based on flexible structure |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104919269A (en) * | 2012-11-30 | 2015-09-16 | 伦顿螺旋弹簧公司 | Resiliently mounted armor panel |
| CN105571400A (en) * | 2015-12-18 | 2016-05-11 | 中国航空工业集团公司北京航空制造工程研究所 | Titanium-based composite armor and manufacturing method thereof |
| CN108516109A (en) * | 2018-03-29 | 2018-09-11 | 北京卫星环境工程研究所 | Umbellate form space junk or micrometeoroid protection device for spacecraft |
| CN210063406U (en) * | 2019-06-11 | 2020-02-14 | 中国科学院沈阳自动化研究所 | Space equipment armor based on flexible structure |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2743065B1 (en) * | 2012-12-14 | 2016-11-30 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Grid type fibre composite structure and method of manufacturing such grid type structure |
-
2019
- 2019-06-11 CN CN201910499868.3A patent/CN110104223B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104919269A (en) * | 2012-11-30 | 2015-09-16 | 伦顿螺旋弹簧公司 | Resiliently mounted armor panel |
| CN105571400A (en) * | 2015-12-18 | 2016-05-11 | 中国航空工业集团公司北京航空制造工程研究所 | Titanium-based composite armor and manufacturing method thereof |
| CN108516109A (en) * | 2018-03-29 | 2018-09-11 | 北京卫星环境工程研究所 | Umbellate form space junk or micrometeoroid protection device for spacecraft |
| CN210063406U (en) * | 2019-06-11 | 2020-02-14 | 中国科学院沈阳自动化研究所 | Space equipment armor based on flexible structure |
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| Publication number | Publication date |
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| CN110104223A (en) | 2019-08-09 |
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