CN105539879A - Spatial box type cabin structure - Google Patents
Spatial box type cabin structure Download PDFInfo
- Publication number
- CN105539879A CN105539879A CN201510875189.3A CN201510875189A CN105539879A CN 105539879 A CN105539879 A CN 105539879A CN 201510875189 A CN201510875189 A CN 201510875189A CN 105539879 A CN105539879 A CN 105539879A
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- square
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- side plates
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- 230000007246 mechanism Effects 0.000 claims abstract description 22
- 238000009434 installation Methods 0.000 claims description 15
- 239000000853 adhesive Substances 0.000 claims description 6
- 230000001070 adhesive effect Effects 0.000 claims description 6
- 238000005242 forging Methods 0.000 claims description 6
- 239000003292 glue Substances 0.000 claims description 6
- 239000002184 metal Substances 0.000 claims description 6
- 230000008859 change Effects 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 5
- 230000008569 process Effects 0.000 claims description 5
- 238000004026 adhesive bonding Methods 0.000 claims description 3
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 12
- 239000011229 interlayer Substances 0.000 description 2
- 238000001514 detection method Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
Classifications
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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
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
Abstract
The invention relates to the field of spaceflight, is suitable for mounting high-accuracy mechanisms and high-accuracy equipment of a space exploration flight vehicle, and particularly relates to a spatial box type cabin structure. The spatial box type cabin structure comprises a square box body (1), namely a square box piece (1), and four triangular box bodies (2), namely four triangular box pieces (2), wherein the square box piece (1) is positioned in the center of the structure; the triangular box pieces (2) are uniformly distributed on four edges of the square box piece (1), and the four triangular box bodies (2) and the square box piece (1) are in the shape of forming spatial inclined angles; the spatial box type cabin structure adopts the whole configuration that the spatial box type cabin structure is gradually furled from top to bottom through the triangular box pieces (2) and is finally formed into a four-point support structure. The spatial box type cabin structure disclosed by the invention has the beneficial effects of being high in rigidity, high in accuracy, low in weight and the like.
Description
Technical Field
The invention relates to the field of spaceflight, is suitable for mounting high-precision mechanisms and equipment of space detection aircrafts, and particularly relates to a space box type cabin body structure.
Background
According to the light and high-precision design requirements of the spacecraft, the mechanism and equipment installation structure of the spacecraft needs to meet the following requirements: the structure has good rigidity; the high-precision installation requirements of mechanisms and equipment are met; and the structural lightweight design requirement is met.
At present, domestic spacecraft mechanisms and equipment mounting structures are mainly divided into two forms of space trusses and conical cylinders, and the application and the development process of the domestic spacecraft mechanisms mainly have the following problems:
(1) the space truss is complex in assembly form, weak in structural rigidity and not strong in adaptability to installation and adjustment of mechanisms and equipment in the later period;
(2) the conical cylinder structure mounting surface is in a cylindrical surface or hyperboloid form, and a large number of adjusting supports in different structural forms need to be matched in mechanism and equipment mounting, so that the precision guarantee difficulty and the development cost are increased.
Disclosure of Invention
The invention aims to provide a space box type cabin body structure to meet the installation requirements of spacecraft mechanisms and equipment.
In order to achieve the above purpose, the technical solution adopted by the present invention to solve the technical problem is:
a space box type cabin body structure comprises a square box body (1) and four triangular box bodies (2), wherein the square box part (1) is located at the center of the space box type cabin body structure, the triangular box parts (2) are uniformly distributed on four sides of the square box part (1), and the four triangular box bodies (2) and the square box part (1) are in a space included angle form; the overall structure of the space box type cabin body structure is gradually folded through the triangular box parts (2) from top to bottom to finally form a four-point support type structure; wherein
The square box piece (1) comprises a square top plate (101), four square side plates (102) and four cylindrical joints (103); the square top plate (101) and the four square side plates (102) are in a light and high-rigidity honeycomb sandwich flat plate structure, and interface embedded parts are embedded in the honeycomb sandwich flat plate structure; the cylindrical joint (103) adopts a prismatic structure form and is machined and formed by a metal forging; each cylindrical joint (103) is designed with four F-shaped adhesive joint assembling interfaces; the four square side plates (102) are assembled through four cylindrical joints (103) in a normal-temperature gluing manner to form a main body frame of the square box body (1); the square top plate (101) is in threaded assembly with a main body frame of the square box body (1) through a threaded embedded part embedded in the square side plate (102) to form the square box body (1); wherein the square top plate (101) is of a repeatable disassembly and assembly structure;
the triangular box (2) comprises a triangular top plate (201), two trapezoidal side plates (202) and a foot support (203); the triangular top plate (201) and the two trapezoidal side plates (202) are in a light and high-rigidity honeycomb sandwich flat plate structure form; the honeycomb sandwich flat plate structure is embedded with an interface embedded part; the foot supports (203) are multifunctional joints and are machined and formed by metal forging machines; two F-shaped gluing assembling interfaces are designed on the foot supports (203); meanwhile, the foot supports (203) are also provided with hoisting interfaces, connecting interfaces and separating interfaces of the cabin sections, and are provided with connecting and separating equipment installation spaces; the two trapezoidal side plates (202) and the foot supports (203) are assembled by normal temperature cementing to form a main body frame of the triangular box body (2); the triangular top plate (201) is in threaded connection with a main body frame of the triangular box body (2) through a threaded embedded part embedded in the trapezoidal side plate (202) to form the triangular box body (2); moreover, the triangular top plate (201) is of a structure capable of being repeatedly disassembled and assembled;
the square box body (1) and the four triangular box bodies (2) are assembled through the F-shaped interfaces of the four cylindrical connectors (103) in a normal-temperature bonding mode to form the space box type cabin body structure.
Preferably, at least one of the square top plate (101), the square side plate (102), the triangular top plate (201) and the two trapezoidal side plates (202) is subjected to interface adaptability adjustment in a manner of embedding an interface component later according to layout adjustment or change of mechanisms and equipment installation in the whole-period development process.
Compared with the prior art, the invention has the following beneficial effects:
the space box-shaped cabin body structure meets the installation requirements of space aircraft mechanisms and equipment, and the structural rigidity and lightweight design requirements are ensured by using the light honeycomb interlayer material; meanwhile, the high-precision assembly fixture and normal-temperature glue joint curing are adopted, so that the design requirement of structural precision is met. In conclusion, the space box type cabin body structure has the advantages of high rigidity, high precision, light weight and the like.
Of course, it is not necessary for any product in which the invention is practiced to achieve all of the above-described advantages at the same time.
Drawings
FIG. 1 is a schematic configuration diagram of a space box type cabin structure according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a square box (1) of the structure of the space box type cabin body according to the embodiment of the invention;
FIG. 3 is a schematic structural diagram of the cylindrical joint (103) of the structure of the space box type cabin body according to the embodiment of the invention;
FIG. 4 is a schematic structural diagram of the triangular box (2) of the structure of the space box type cabin body according to the embodiment of the invention;
FIG. 5 is a schematic structural diagram of the foot supports (203) of the structure of the space box type cabin body according to the embodiment of the invention;
fig. 6 is an assembly schematic diagram of the square box body (1) and the triangular box body (2) of the space box type cabin body structure according to the embodiment of the invention.
Detailed Description
The invention is described in detail below with reference to the figures and examples.
Examples
Referring to fig. 1, fig. 1 is a schematic configuration diagram of a space box type cabin structure according to the present embodiment; wherein,
the space box type cabin structure comprises a square box body (1) and four triangular box bodies (2), wherein the square box part (1) is located at the center of the space box type cabin structure, the triangular box parts (2) are uniformly distributed on four sides of the square box part (1), and the four triangular box bodies (2) and the square box part (1) form a space included angle; the overall structure of the space box type cabin body structure is gradually folded from top to bottom through the triangular box parts (2), and finally a four-point supporting type structure is realized. The structure effectively simplifies the connection and separation design of the cabin sections and reduces the requirement of occupied structural space.
Please refer to fig. 2 and fig. 3, wherein fig. 2 is a schematic structural composition diagram of the square box (1), and fig. 3 is a schematic structural diagram of the cylindrical joint (103) of the square box (1).
Specifically, referring to fig. 2, the square box (1) comprises a square top plate (101), four square side plates (102) and four cylindrical joints (103); wherein,
the square top plate (101) and the four square side plates (102) are in a light and high-rigidity honeycomb sandwich flat plate structure form, so that a large number of mounting planes can be provided for mechanisms and equipment on the basis of realizing light structure; the honeycomb sandwich flat plate structure is embedded with an interface embedded part to provide a mechanism and equipment installation interface; in addition, at least one of the square top plate (101) and the square side plate (102) can be subjected to interface adaptability adjustment in a way of embedding an interface in a rear manner aiming at layout adjustment or change which can occur in mechanism and equipment installation in the whole-period development process;
the four cylindrical joints (103) are in prismatic structure forms and are machined and formed by metal forging; referring to fig. 3, each cylindrical joint (103) is designed with four F-shaped adhesive joint interfaces, which are respectively an interface of two square side plates (102) and an interface of two trapezoidal side plates (202), so as to meet the adhesive joint assembly requirements of a plurality of honeycomb sandwich plates of the square side plates (102) and the following trapezoidal side plates (202);
the four square side plates (102) are assembled by four cylindrical joints (103) through normal temperature cementing to form a main body frame of the square box body (1); the square top plate (101) is in threaded connection with a main body frame of the square box body (1) through a threaded embedded part embedded in the square side plate (102) to form the square box body (1); the square top plate (101) is of a structure capable of being repeatedly disassembled and assembled, and has a function of being repeatedly disassembled and assembled, so that convenience in mechanism and equipment installation operation is improved.
Please refer to fig. 4 and 5, wherein fig. 4 is a schematic structural composition diagram of the triangular box (2), and fig. 5 is a schematic structural diagram of the foot support (203) of the triangular box (2); wherein,
the triangular box (2) comprises a triangular top plate (201), two trapezoidal side plates (202) and a foot support (203); the triangular top plate (201) and the two trapezoidal side plates (202) are in a light and high-rigidity honeycomb sandwich flat plate structure form, so that a large number of mounting planes can be provided for mechanisms and equipment on the basis of realizing the light structure; the honeycomb sandwich flat plate structure is embedded with an interface embedded part to provide a mechanism and equipment installation interface; in addition, aiming at layout adjustment or change which can occur in mechanism and equipment installation in the whole-period development process, at least one of the triangular top plate (201) and the two trapezoidal side plates (202) can be subjected to interface adaptability adjustment in a mode of embedding an interface;
the foot supports (203) are multifunctional joints and are machined and formed by a metal forging machine; referring to fig. 5, two F-shaped glue joints are designed on the foot support (203) and are joints of two trapezoidal side plates (202), which can meet the glue joint assembly requirement of the two trapezoidal side plates (202). Meanwhile, the foot support (203) is also provided with a hoisting interface, a connecting interface and a separating interface of the cabin section, and is provided with a connecting and separating equipment mounting space;
the two trapezoidal side plates (202) and the foot supports (203) are assembled by normal temperature cementing to form a main body frame of the triangular box body (2); the triangular top plate (201) is in threaded connection with a main body frame of the triangular box body (2) through a threaded embedded part embedded in the trapezoidal side plate (202) to form the triangular box body (2); the triangular top plate (201) is of a structure capable of being repeatedly disassembled and assembled, has a function of being repeatedly disassembled and assembled, and improves convenience of installation and operation of mechanisms and equipment.
Referring to fig. 6, fig. 6 is an assembly diagram of the square box (1) and the triangular box (2). Wherein,
the square box body (1) and the four triangular box bodies (2) are subjected to normal-temperature adhesive joint assembly through F-shaped interfaces of the four cylindrical connectors (103) under the assistance of a high-precision assembly fixture to form a space box type cabin body structure. The normal temperature glue joint assembly is convenient to operate, and meanwhile, the influence of the curing residual stress of the adhesive on the structural precision can be reduced, and the overall structural precision is effectively guaranteed.
According to the invention, the mechanism and equipment mounting structure adopts a light and high-rigidity honeycomb interlayer space box type structural form, so that a large number of mechanism and equipment mounting planes can be provided on the premise of meeting the structural rigidity and light weight design requirements, and the requirements of later equipment mounting adjustment and change can be fully met. In addition, the cabin body structure precision can be effectively ensured through normal-temperature glue joint assembly of the high-precision assembly jig.
The preferred embodiments of the invention disclosed above are intended to be illustrative only. The preferred embodiments are not intended to be exhaustive or to limit the invention to the precise embodiments disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best utilize the invention. The invention is limited only by the claims and their full scope and equivalents.
Claims (2)
1. The space box type cabin structure is characterized by comprising a square box body (1) and four triangular box bodies (2), wherein the square box body (1) is located at the center of the space box type cabin structure, the triangular box bodies (2) are uniformly distributed on four sides of the square box body (1), and the four triangular box bodies (2) and the square box body (1) form a space included angle; the overall structure of the space box type cabin body structure is gradually folded through the triangular box parts (2) from top to bottom to finally form a four-point support type structure; wherein,
the square box piece (1) comprises a square top plate (101), four square side plates (102) and four cylindrical joints (103); the square top plate (101) and the four square side plates (102) are of honeycomb sandwich flat plate structures, and interface embedded parts are embedded in the honeycomb sandwich flat plate structures; the four cylindrical joints (103) are in prismatic structure forms and are machined and formed by metal forging; each cylindrical joint (103) is designed with four F-shaped adhesive joint assembling interfaces; the four square side plates (102) are assembled through normal-temperature cementing of the four cylindrical joints (103) to form a main body frame of the square box body (1); the square top plate (101) is in threaded assembly with a main body frame of the square box body (1) through a threaded embedded part embedded in the square side plate (102) to form the square box body (1); wherein the square top plate (101) is of a repeatable disassembly and assembly structure;
the triangular box (2) comprises a triangular top plate (201), two trapezoidal side plates (202) and a foot support (203); the triangular top plate (201) and the two trapezoidal side plates (202) both adopt a honeycomb sandwich flat plate structure; the honeycomb sandwich flat plate structure is embedded with an interface embedded part; the foot support (203) is machined and formed by a metal forging machine, and two F-shaped gluing assembling interfaces are designed on the foot support (203); meanwhile, the foot supports (203) are also provided with hoisting interfaces, connecting interfaces and separating interfaces of the cabin sections, and are provided with connecting and separating equipment installation spaces; the two trapezoidal side plates (202) and the foot supports (203) are assembled through normal-temperature glue joint to form a main body frame of the triangular box body (2); the triangular top plate (201) is in threaded connection with a main body frame of the triangular box body (2) through a threaded embedded part embedded in the trapezoidal side plate (202) to form the triangular box body (2); moreover, the triangular top plate (201) is of a structure capable of being repeatedly disassembled and assembled;
the square box body (1) and the four triangular box bodies (2) are assembled through the F-shaped interfaces of the four cylindrical connectors (103) in a normal-temperature bonding mode to form the space box type cabin body structure.
2. The spatial box-shaped cabin structure according to claim 1, wherein at least one of the square top plate (101) and four square side plates (102), the triangular top plate (201) and two trapezoidal side plates (202) is adapted to the interface by embedding the interface in the way of a rear-embedded interface embedded component for layout adjustment or change of mechanism and equipment installation in the whole-period development process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510875189.3A CN105539879B (en) | 2015-12-02 | 2015-12-02 | Space cell type section structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510875189.3A CN105539879B (en) | 2015-12-02 | 2015-12-02 | Space cell type section structure |
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| Publication Number | Publication Date |
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| CN105539879A true CN105539879A (en) | 2016-05-04 |
| CN105539879B CN105539879B (en) | 2017-10-27 |
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| CN201510875189.3A Active CN105539879B (en) | 2015-12-02 | 2015-12-02 | Space cell type section structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106021802A (en) * | 2016-06-06 | 2016-10-12 | 上海宇航系统工程研究所 | Finite element calculation method for strength of embedded-beam-containing honeycomb sandwich structure |
| CN106043741A (en) * | 2016-08-05 | 2016-10-26 | 深圳航天东方红海特卫星有限公司 | Satellite configuration design method adapting to one-rocket multi-satellite launching |
| CN110836635A (en) * | 2019-09-30 | 2020-02-25 | 上海航天设备制造总厂有限公司 | Measuring reference establishing and measuring method for light honeycomb sandwich box type structure |
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| CN106021802A (en) * | 2016-06-06 | 2016-10-12 | 上海宇航系统工程研究所 | Finite element calculation method for strength of embedded-beam-containing honeycomb sandwich structure |
| CN106043741A (en) * | 2016-08-05 | 2016-10-26 | 深圳航天东方红海特卫星有限公司 | Satellite configuration design method adapting to one-rocket multi-satellite launching |
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| CN110836635A (en) * | 2019-09-30 | 2020-02-25 | 上海航天设备制造总厂有限公司 | Measuring reference establishing and measuring method for light honeycomb sandwich box type structure |
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