CN201703569U - Installation and storage platform for equipment of space station - Google Patents
Installation and storage platform for equipment of space station Download PDFInfo
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- CN201703569U CN201703569U CN2010201048096U CN201020104809U CN201703569U CN 201703569 U CN201703569 U CN 201703569U CN 2010201048096 U CN2010201048096 U CN 2010201048096U CN 201020104809 U CN201020104809 U CN 201020104809U CN 201703569 U CN201703569 U CN 201703569U
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Abstract
The utility model relates to an installation and storage platform for the equipment of a space station, which comprises a main body frame component, two upper joint components, two lower front joint components, two lower back joint components, two upper connecting rod components and two lower connecting rod components. Under the condition of meeting light weight and high load, the utility model adopts the connection mode of connecting rods, adapts to the frequency requirement under a transmission environment and avoids the occurrence of resonance with an entire capsule body; a mechanism at the joint of the storage platform can be conveniently and quickly disassembled, can be fixedly connected with and separated from an orbit and a capsule body at the ground, is convenient for carrying out transfer and installation between different capsule sections, meets the requirement of the transmission environment and can be firmly connected by the disassembly of the ground when being at the orbit; and a cabinet can rotate around a structure inside a capsule by the installation of a rotary pin, which is convenient for a cosmonaut to carry out the operation of maintenance and the like.
Description
Technical field
The utility model relates to a kind of space station equipment storage platform is installed, and is used in the Large Spacecraft cabin belonging to the manned space technology field for capacity weights such as test apparatus equipment provide storage space and support.
Background technology
Along with China after manned space flight and lunar exploration engineering are achieved success, the space station becomes the Large Spacecraft that Future in China is given priority to, its main application be exactly in space for the mankind provide one can long playing research laboratory, can carry out related experiment and researchs such as life science, microgravity science, space science, engineering technology here.The structure that is used in the spacecraft at present supporting with erecting equipment mostly is the frame form that structural beams overlaps, can not realize conveniently installation and removal, shift and exchange by modular together with equipment or instrument in the time of can not being implemented in rail, therefore, in order in the space station, more effectively and easily to carry out the space science experiment, and, need that utility model is a kind of can be in sealed module to provide the platform of storage space and support efficiently for capacity weights such as correlation test instrument and equipments in conjunction with the development strategy of China's aerospace industry.
The utility model content
Technology of the present utility model is dealt with problems and is: overcomes the deficiencies in the prior art, provides a kind of space station equipment that storage platform is installed, and simple in structure, light weight, the normalisation, modularization, the modularization that can be used for capacity weight in the spacecraft are installed.
Technical solution of the present utility model is: a kind of space station equipment is installed storage platform, comprise the main body frame assembly, two top connection assemblies, two following front connector assemblies, back joint under two, two boxed rod assemblies and two lower link assemblies, two top connection assemblies are installed in two end angles at main body frame assembly top, two following front connector assemblies and two following back joinies are installed in four end angles bottom the main body frame assembly, two top connection assemblies are fixed by be connected with contiguous block on the bulkhead of the space station top of realization body frame assembly and cabin, space bulkhead of two boxed rod assemblies respectively, the back joint is connected with two lower connecting blocks of cabin, space bulkhead respectively under two, and two lower link assemblies pass down the front connector assembly respectively successively, the following back joint and the lower connecting block realization body frame assembly of cabin, space bulkhead and the bottom of cabin, space bulkhead are fixed.
Described top connection assembly adopts the rack and pinion drive mechanism of being made up of transmission gear, driving rack and Teethed bolt lock rationed marketing, the upper end of driving rack is connected with the globe bearing of boxed rod assembly, drive driving rack by rotary transmission gear and rise or descend, the Teethed bolt lock rationed marketing is used to prevent that driving rack is loosening.
Adopt aluminum alloy materials to make in described boxed rod assembly and the lower link assembly, an end of boxed rod assembly is equipped with globe bearing.
The utility model beneficial effect compared with prior art is: satisfying under the high condition of carrying of lightweight, the utility model adopts the connecting rod connection mode, adapts to the frequency requirement under the launch environment, avoids resonating with whole cabin body; The mechanism of storage platform junction can dismantle easily and efficiently, can ground be connected with the cabin body at rail and separate, be convenient to intersegmentally in different cabins shift, install, satisfy the launch environment requirement, when rail, can be fastenedly connected by dismounting ground, swivel pin is installed rack is rotated around the cabin inner structure, make things convenient for operations such as the astronaut keeps in repair.
Description of drawings:
Fig. 1 is a front view of the present utility model;
Fig. 2 is that the A of Fig. 1 is to view;
Fig. 3 is a block diagram of the present utility model;
Fig. 4 is a front connector assembly and the connection diagram that descends back joint and space station bulkhead under the utility model;
Fig. 5 is the connection diagram of the utility model top connection assembly and space station bulkhead;
Fig. 6 is the cut-away view of the utility model top connection assembly.
The specific embodiment
Below in conjunction with the drawings and specific embodiments the utility model is described in further detail:
Principle of the present utility model is: according to space station equipment storage platform is installed and will experiences emission/in process characteristics such as rails, to strengthen the integral structure of cabin body from the mechanics angle, main platform body adopts framed structure, from the main support main beam of elastomeric material terms of mechanics utility model framed structure is carbon fiber-reinforced resin composite materials, from theory of machines and operability design, and the principle of ergonomics comes flat-bed point of connection and operating mechanism are carried out utility model, finally sum up in the point that the flat-bed functionalized design, be integrated into modularization, maintainability and mechanical, electrical and heating integrated unit.The utility model mainly comprises the chassis body structure that four girders and some auxilliary beams and dividing plate are formed, all around by top connection assembly, front connector assembly, back joint connection down down, for realizing Fast Installation and being convenient to dismounting, top connection assembly and following front connector component internal all have corresponding mechanism design, and the main frame structure outside is as a whole with this structure envelope by covering.As Fig. 1,2, shown in 3, comprise main body frame assembly 1, two top connection assemblies 2, two following front connector assemblies 3, back joint 4 under two, two boxed rod assemblies 7 and two lower link assemblies 9, two top connection assemblies 2 are installed in two end angles at main body frame assembly 1 top, two following front connector assemblies 3 and two four end angles descending back joint 4 to be installed in main body frame assembly 1 bottom, top connection assembly 2 is fixed with the top of cabin, space bulkhead by the boxed rod assembly 7 realization body frame assembly 1 that is connected with contiguous block on the bulkhead of space station, following back joint 4 is connected with the lower connecting block 5 of cabin, space bulkhead, and lower link assembly 9 is from passing down front connector assembly 3 successively, the lower connecting block 5 realization body frame assemblies 1 of following back joint 4 and cabin, space bulkhead are fixed with the bottom of cabin, space bulkhead.
Wherein the chassis body structure constitutes the covering truss structure by four girders and joint and covering, its main load parts are main beam structure, situation analysis is defined as two C ellbeams and adds that lower cover forms the form of H-girder according to main beam stress, process by carbon fiber-reinforced resin composite materials, (carbon fibre material is T300 or T700, resin is a cyanate ester resin), cover plate can be chosen high-strength aluminum alloy material as required up and down.
As shown in Figure 4, the flat-bed bottom connects: at first equipment is installed storage platform and move to the installation site, the interior contiguous block 5 of the following back joint 4 that makes platform bottom and station module body docks, penetrate following back joint 5 with lower link assembly 9 from the following access hole of front connector assembly 3 through to the platform bottom, platform and bulkhead lower connecting block 5 are connected, lower link assembly 4 is fastening, at last that lock bolt 8 and following front connector is fastening, prevent lower link assembly 4 plaies.Before the lower adaptor assembly be the left-right symmetric assembly, the lower adaptor lower end has port and is used to connect the lower link assembly, upper end design has projection to be connected with the girder of chassis body, the joint middle part is designed a short side groove, with lower adaptor itself and lower supporting plate as support.
As shown in Figure 5, flat-bed top connects: equipment install storage platform be connected with the top of cabin body be top connection assembly 2 with the cabin body on contiguous block link to each other by boxed rod assembly 7 and realize, boxed rod assembly 7 two ends are by being threaded and possessing the length adjustment function, contiguous block is connected on one end of boxed rod assembly 7 and the bulkhead, the other end is connected with flat-bed top connection assembly 2, so that carry out platform is connected the micro-adjustment of attitude.As shown in Figure 6, the top connection assembly is the left-right symmetric assembly, by top connection, transmission gear 10, driving rack 11, Teethed bolt lock rationed marketing 12, upper backup pad and three screws constitute, top connection has the projection of three directions to be used for being connected with auxilliary beam with the girder of chassis body, driving rack 11 is that little free-running fit can be slided in the centre hole of top connection with top connection, by being fixed on the action transmission of the transmission gear on the upper backup pad, the rotation of transmission gear 10 drives driving rack 11 can upward movement and pass square groove (inspection door), insert the globe bearing 13 of the termination of the boxed rod assembly 7 that links together with the cabin body, be connected in one with boxed rod assembly 7, finish being connected by boxed rod assembly and cabin body.Flat-bed top connection assembly 2 adopts rack and pinion drive mechanisms, is fixed on transmission gear 10 on the upper backup pad 14 by rotation, and driving rack 11 rises, insert the inspection door square groove, be connected with the globe bearing 13 of boxed rod assembly 7, locking rack stop pin 12 prevents that driving rack 11 is loosening.
This utility model can be implemented in ground and dismantle at rail, in order to adapt to the launch environment requirement, floor mounted with install to adopt diverse ways at rail, when rail, can be fastenedly connected by dismounting ground, swivel pin is installed can be rotated by the lower adaptor assembly equipment installation storage platform before platform, make things convenient for personnel when maintenance the access platform back or below equipment, be placed on other positions after also can platform shifting.Below with regard to this utility model of simple declaration in the fastening means of transmitter section/reentry phase, in rail dismounting/transfer process, in the total system implementation of rail rotation.
Of the present utility modelly implementation is installed at rail: as required can be after aircraft is entered the orbit by removing upper and lower connecting rod assembly, convert to the rail mounting means come the displacement of implementation platform or operating personal can the access platform back or below equipment.
Bottom bonded assembly dismounting implementation when rail is installed: the lock bolt 8 of front connector assembly 3 under the platform unclamped and screw out to the access hole of lower link assembly 9 and do not block, lower link assembly 9 is outwards screwed out till can not turn, back joint 4 is removed with cabin body lower connecting block 5 to be connected, at last lock bolt 8 is screwed in the hole and tighten, so just realized bottom bonded assembly dismounting.The implementation of the installation of turnover bracket axle when rail is installed: with the lax circle of knob of 3 li of front connector assemblies under the platform bottom, be in released state, then block is rotated down and is placed on bottom dead point, in the slot with front connector assembly 3 under the swivel pin insertion of turnover bracket axle, the turnover bracket axle is installed in by binding bolt and descends on the fixed beam in the cabin then, look into by spurring mounted turnover bracket repacking whether it fastened, promote knob at last and drive block, upwards push away and be placed on top dead center position, the right-hand revolution knob is in locking state to tightening again.
The implementation of upper end ways of connecting conversion when rail is installed: the Teethed bolt lock rationed marketing 12 of top connection assembly 2 is screwed out, driving rack 11 is carried out release, rotary transmission gear 10 drives driving rack 11 and moves down, it is deviate from from globe bearing 13, then boxed rod assembly 7 is extracted out the top connection assembly 2 of implementation platform and the disengaging of boxed rod assembly 7 from inspection door; Bolt mechanism is inserted in the inspection door of top connection assembly, and fix, at last latch is inserted on the body of cabin in the latch capture mechanism on the fixed beam, finish the whole conversion of platform at the rail mounting means with bolt.
The utility model not detailed description is a technology as well known to those skilled in the art.
Claims (3)
1. a space station equipment is installed storage platform, it is characterized in that comprising: main body frame assembly (1), two top connection assemblies (2), two following front connector assemblies (3), back joint (4) under two, two boxed rod assemblies (7) and two lower link assemblies (9), two top connection assemblies (2) are installed in two end angles at main body frame assembly (1) top, two following front connector assemblies (3) and two following back joinies (4) are installed in four end angles of main body frame assembly (1) bottom, two top connection assemblies (2) are fixed with the top of cabin, space bulkhead by two boxed rod assemblies (7) realization body frame assembly (1) that is connected with contiguous block on the bulkhead of space station respectively, back joint (4) is connected with two lower connecting blocks (5) of cabin, space bulkhead respectively under two, and two lower link assemblies (9) pass down front connector assembly (3) respectively successively, lower connecting block (5) the realization body frame assembly (1) of following back joint (4) and cabin, space bulkhead is fixed with the bottom of cabin, space bulkhead.
2. a kind of space station according to claim 1 equipment is installed storage platform, it is characterized in that: described top connection assembly (2) adopts the rack and pinion drive mechanism of being made up of transmission gear (10), driving rack (11) and Teethed bolt lock rationed marketing (12), the upper end of driving rack (11) is connected with the globe bearing (13) of boxed rod assembly (7), drive driving rack (11) by rotary transmission gear (10) and rise or descend, Teethed bolt lock rationed marketing (12) is used to prevent that driving rack (11) is loosening.
3. a kind of space station according to claim 1 equipment is installed storage platform, it is characterized in that: adopt aluminum alloy materials to make in described boxed rod assembly (7) and the lower link assembly (9), an end of boxed rod assembly (7) is equipped with globe bearing (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201048096U CN201703569U (en) | 2010-01-29 | 2010-01-29 | Installation and storage platform for equipment of space station |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201048096U CN201703569U (en) | 2010-01-29 | 2010-01-29 | Installation and storage platform for equipment of space station |
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| Publication Number | Publication Date |
|---|---|
| CN201703569U true CN201703569U (en) | 2011-01-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010201048096U Expired - Lifetime CN201703569U (en) | 2010-01-29 | 2010-01-29 | Installation and storage platform for equipment of space station |
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| CN (1) | CN201703569U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107594949A (en) * | 2017-11-03 | 2018-01-19 | 北京天宫空间应用技术有限公司 | A kind of light composite material Space Experiments cabinet |
| CN108657472A (en) * | 2017-05-19 | 2018-10-16 | 北京空间飞行器总体设计部 | A kind of spacecraft internal unit mounting structure of in-orbit quick release overturning |
| CN110416775A (en) * | 2019-06-03 | 2019-11-05 | 中国航天时代电子有限公司 | A kind of electromechanics mating interface and the in-orbit restructural aircraft unit based on the interface |
| CN112520069A (en) * | 2020-12-11 | 2021-03-19 | 中国科学院沈阳自动化研究所 | Labor-saving device for track operation of load supporting frame in space station cabin |
| CN113800010A (en) * | 2021-10-29 | 2021-12-17 | 北京卫星环境工程研究所 | Operating platform for maintaining external rail of space station cabin |
| CN114263393A (en) * | 2021-12-24 | 2022-04-01 | 哈尔滨工业大学 | Connecting rod linkage type hatch cover overturning locking mechanism and overturning locking method thereof |
| CN116096023A (en) * | 2022-12-30 | 2023-05-09 | 中国科学院空间应用工程与技术中心 | On-line maintenance, adjustment and operation cabinet for space station |
-
2010
- 2010-01-29 CN CN2010201048096U patent/CN201703569U/en not_active Expired - Lifetime
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108657472A (en) * | 2017-05-19 | 2018-10-16 | 北京空间飞行器总体设计部 | A kind of spacecraft internal unit mounting structure of in-orbit quick release overturning |
| CN108657472B (en) * | 2017-05-19 | 2020-05-08 | 北京空间飞行器总体设计部 | On-orbit spacecraft internal equipment mounting structure capable of being rapidly detached and turned |
| CN107594949A (en) * | 2017-11-03 | 2018-01-19 | 北京天宫空间应用技术有限公司 | A kind of light composite material Space Experiments cabinet |
| CN110416775A (en) * | 2019-06-03 | 2019-11-05 | 中国航天时代电子有限公司 | A kind of electromechanics mating interface and the in-orbit restructural aircraft unit based on the interface |
| CN112520069A (en) * | 2020-12-11 | 2021-03-19 | 中国科学院沈阳自动化研究所 | Labor-saving device for track operation of load supporting frame in space station cabin |
| CN113800010A (en) * | 2021-10-29 | 2021-12-17 | 北京卫星环境工程研究所 | Operating platform for maintaining external rail of space station cabin |
| CN114263393A (en) * | 2021-12-24 | 2022-04-01 | 哈尔滨工业大学 | Connecting rod linkage type hatch cover overturning locking mechanism and overturning locking method thereof |
| CN114263393B (en) * | 2021-12-24 | 2022-10-14 | 哈尔滨工业大学 | Connecting rod linkage type hatch cover overturning locking mechanism and overturning locking method thereof |
| CN116096023A (en) * | 2022-12-30 | 2023-05-09 | 中国科学院空间应用工程与技术中心 | On-line maintenance, adjustment and operation cabinet for space station |
| CN116096023B (en) * | 2022-12-30 | 2023-08-18 | 中国科学院空间应用工程与技术中心 | On-line maintenance, adjustment and operation cabinet for space station |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20110112 |
|
| CX01 | Expiry of patent term |