CN200978009Y - Hanging apparatus for spacing environment simulation device - Google Patents
Hanging apparatus for spacing environment simulation device Download PDFInfo
- Publication number
- CN200978009Y CN200978009Y CN 200620048129 CN200620048129U CN200978009Y CN 200978009 Y CN200978009 Y CN 200978009Y CN 200620048129 CN200620048129 CN 200620048129 CN 200620048129 U CN200620048129 U CN 200620048129U CN 200978009 Y CN200978009 Y CN 200978009Y
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- environment simulation
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- space environment
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Abstract
The utility model discloses a suspension device for space environment simulation facilities, which comprises a vertical lifting mechanism and a vertical suspension mechanism. The vertical lifting mechanism comprises a working platform, which is able to enter and exit a vacuum chamber along a guide-way, a jack and an elevating platform. The jack is provided between the elevating platform and the working platform, and the elevating platform is available to lift along vertical direction. The vertical lifting mechanism comprises a rectangular frame, a beam, a suspender and a slider. The frame is fixed on the inner wall of the vacuum chamber; the beam is connected with the frame by the slider and able to translate vertically along the frame; the suspender is connected with the beam by the slider and able to move horizontally along the beam. The utility model is used for aircraft overhung mounting in space environment simulation facilities by way of mechanical work instead of manual work, and has advantages of labor saving and high working efficiency, most of all, the safety of the aircraft is guaranteed and overhung mounting work is reliable. The utility model can adapt to aircraft overhung mounting with various volumes and sizes.
Description
Technical field:
The utility model relates to a kind of test facility that is used for spacecraft, particularly relate to a kind of in space environment simulation equipment in order to hang the device of spacecraft.
Background technology:
The spacecraft that enters the space must be made various performance tests or reliability test earlier in ground-surface space environment simulation equipment before emission, whether satisfy pre-provisioning request to check its structure design, thermal control design etc., thereby can decision launch on the spot.Be that spacecraft is hung in the center of the formed cold-scarce scape of space environment simulation equipment available space when carrying out ground simulation test, the actual state of in the cosmic space, flying with Simulated Spacecraft the most closely.
Because researcher is generally only paid attention to the research of environmental simulation aspects such as cosmic space vacuum, cold black background, and hang fixing link when often ignoring test, think that mistakenly this is experimental implementation person's a thing, therefore at present in the existing space environmental simulation equipment hanging of spacecraft installed and remain by manual type, means such as promptly adopt manpower to lift, steel rope draws are hung spacecraft on the suspension ring at the vacuum vessel top of space environment simulation equipment.This traditional not only labor intensive but also bring many safety hazard of mounting means of manually hanging: on the one hand, manually hang and the heavy weight spacecraft is installed is not only needed to employ more personnel, and expend time in long, inefficiency; On the other hand, be loaded with the precision instrument and the device of many costlinesses in the spacecraft of test, the manually-operated damage that can cause spacecraft accidentally causes serious consequence, even brings irretrievable loss.
Summary of the invention:
In order to overcome the defective that manual type is hung the installation spacecraft in the above-mentioned existing space environmental simulation equipment, the utility model provides a kind of erecting by overhang of space environment simulation equipment, it adopts mechanical system to carry out the installation of hanging of spacecraft, has high efficiency, safe and reliable advantage.
The technical scheme in the invention for solving the technical problem is:
A kind of erecting by overhang of space environment simulation equipment is arranged in the vacuum vessel, and it comprises vertical takeoff and landing mechanism and vertical hanging mechanism; Vertical takeoff and landing mechanism includes can be along guide rail come in and go out workplatform, jack and the lifting table of vacuum vessel, and this lifting table is positioned at the top of workplatform, but jack is located between lifting table and the workplatform and the operate lifting platform along vertical lifting; Vertical hanging mechanism includes framework, crossbeam, suspension rod and slide block, this framework is rectangle and is fixed on the inner roof wall of vacuum vessel, the slide block of crossbeam by its two ends is connected with framework and can be along the longitudinal translation of framework, and the slide block of suspension rod by its top is connected with crossbeam and can carries out side travel along crossbeam.
The erecting by overhang of space environment simulation equipment described in the utility model, its vertical takeoff and landing mechanism also includes the connecting rod mechanism of parallelogram, and the upper and lower end of this connecting rod mechanism is hinged on respectively on lifting table and the workplatform so that lifting table remains level in lifting; The framework of vertical hanging mechanism is fixed on the inner roof wall of vacuum vessel by 6 fixed link suspentions, and the crossbeam of this vertical hanging mechanism is 2, and suspension rod is 4, and the bottom of this suspension rod is by turnbuckle and the shackle of being threaded.
Hanging the manual type that spacecraft is installed with existing space environmental simulation equipment compares, the utility model adopts mechanical system to carry out hanging and installing of spacecraft, the jack of its vertical takeoff and landing mechanism can be handled the lifting table that is loaded with spacecraft and remain on even keel along vertical lifting reposefully, the suspension rod of its vertical hanging mechanism can move in that the framework upper edge is vertical or horizontal by slide block and beam structure, thereby adapts to the hanging of different posture positions of different spacecrafts.Therefore, a large amount of manpowers have been saved in the application of the utility model in space environment simulation equipment, have improved spacecraft greatly and have hung the work efficiency of installation, and the more important thing is the safety of having guaranteed spacecraft and hang the reliable of installation, have avoided the generation of accident.
Description of drawings:
Fig. 1 is a structural representation of the present utility model.
Fig. 2 is the front view of the vertical hanging mechanism of the utility model.
Fig. 3 is that the A of Fig. 2 is to view.
Fig. 4 is the lateral plan of Fig. 2.
The specific embodiment:
The utility model is described in further detail below in conjunction with specific embodiments and the drawings.
At first see also Fig. 1 structural representation of the present utility model.The erecting by overhang of diagram space environment simulation equipment is arranged in the vacuum vessel 3 of space environment simulation equipment, and this vacuum vessel 3 is cylindric, and its inner chamber will form the available space of environment such as simulated space vacuum, cold black background in process of the test.The erecting by overhang of described space environment simulation equipment comprises vertical takeoff and landing mechanism 1 and vertical hanging mechanism 2.Vertical takeoff and landing mechanism 1 includes workplatform 11, jack 12, lifting table 13 and connecting rod mechanism 14.The bottom of workplatform 11 is equiped with four rolling 15, and this roller 15 is shelved on along on vacuum vessel 3 vertical guide rails of laying 4, and workplatform 11 can advance or pull out vacuum vessel 3 by the outside by roller 15 moving on guide rail 4.The center of workplatform 11 is equipped with a hydraulic jack 12 with manual voltage boosting and release, lifting table 13 is positioned at the top of workplatform 11, jack 12 is located between lifting table 13 and the workplatform 11, its bottom places on the workplatform 11, its top braces lifting table 13, thereby can drive lifting table 13 along the vertical lifting by handling jack 12, can place the spacecraft S of test on the lifting table 13.Connecting rod mechanism 14 is a parallelogram, and its upper and lower end is hinged on (see figure 1) on lifting table 13 and the workplatform 11 respectively, because the motion characteristics of parallelogram linkage 14, lifting table 13 just can remain level in lifting process.
The structure of vertical takeoff and landing shown in Figure 1 mechanism 1 is that the utility model is realized driving the lifting table 13 that is loaded with spacecraft S and can and be remained a kind of embodiment of level along the steady lifting of vertical.Can also there be the embodiment of more other form structure in vertical takeoff and landing of the present utility model mechanism 1, for example, several jacks 12 are set between lifting table 13 and workplatform 11, the position distribution of these jacks 12 is even and gravity balance, as long as handling these jacks 12 rises synchronously or descends, just also can reach lifting table 13 along the steady lifting of vertical and remain the purpose of level, and just can omit connecting rod mechanism 14 in the structure.And for example, between lifting table 13 and workplatform 11 several hydraulic rams are set, the synchronization lifting of this hydraulic ram also can reach above-mentioned identical effect.
Please comprehensively consult Fig. 2, Fig. 3 and Fig. 4, illustrate vertical hanging mechanism 2 and include framework 21, crossbeam 22, suspension rod 23 and slide block 24.This framework 21 is a rectangle, and it is fixed on (see figure 1) on the inner roof wall of vacuum vessel 3 by 6 fixed links 27 suspention, its vertically along vacuum vessel 3 axially, its laterally perpendicular to vacuum vessel 3 axially; Junction between fixed link 27 and the framework 21 is gripped with polytetrafluoroethylene gasket and makes it insulation, thereby makes framework 21 and top coupling link and vacuum vessel 3 insulation thereof.Two crossbeams 22 are located at the transversely (see figure 3) of framework 21, and its slide block 24 by two ends is connected with vertical hack lever of framework 21, this slide block 24 can be on vertical hack lever of framework 21 mobile (see figure 4), thereby crossbeam 22 also can be along the longitudinal translation of framework 21.Equally respectively be equipped with 2 slide blocks 24 on two crossbeams 22, each slide block 24 is all connecting the top (see figure 2) of a suspension rod 23, and it can move on crossbeam 22 and available setting screw 28 fixed positions thereon.Therefore 4 suspension rods 23 slide block 24 of all pass through its top is connected with crossbeam 22, and can pass through slide block 24 and screw 28 side travel or the location at crossbeam 22 upper edge frameworks 21.From the above mentioned,, can in the scope of framework 21, adjust the position and the span of 4 suspension rods 23,, can make various spacecraft S all can realize vertically hanging to adapt to the needs of hanging different big or small spacecraft S by moving slider 24 on framework 21 and crossbeam 22.See also Fig. 2 again, the bottom of suspension rod 23 is connected with turnbuckle 25 and shackle 26 in turn, between them all by being threaded, therefore the position height of shackle 26 can be suitably adjusted in turn turnbuckle 25 or shackle 26, shackle 26 is used to hang spacecraft S, and the diverse location height of adjusting 4 shackles 26 can adapt to the needs of hanging spacecraft S with different angles or attitude.
Application operating process of the present utility model is as follows:
1) the vertical takeoff and landing mechanism 1 with the erecting by overhang of described space environment simulation equipment is positioned on the guide rail of carrier loader, and spacecraft S is placed on the lifting table 13.
2) guide rail when carrier loader advances vacuum vessel 3 also to be fixed in company with spacecraft S vertical takeoff and landing mechanism 1 after guide rail 4 butt joints of vacuum vessel 3.
3) to jack 12 pressurizations, lifting table 13 remains on even keel and rises reposefully along vertical under the support of connecting rod mechanism 14, makes spacecraft S rise to the center that predetermined altitude arrives vacuum vessel 3 with reference to fixing scale.
4) implement hanging of spacecraft S by the 2-4 name operating personal that stands on the workplatform 11.
5) according to the span of spacecraft S suspension ring, operating personal moving slider 24 and crossbeam 22 with in the position of vertical and horizontal both direction adjusted suspension rod 23, can vertically be hung spacecraft S and tighten fix screw 28 up to 4 suspension rods 23.
6) turn turnbuckle 25 connects the suspension ring of spacecraft S and tightens up suspension rod 23 with shackle 26 again to adjust the height of 4 shackles 26, and then turn turnbuckle 25 adjustment spacecraft S make it to be in angle and the attitude that needs respectively.
7) operating personal is installed spacecraft S signal socket connector and joint detection circuit.
8) to jack 12 releases, lifting table 13 descends and breaks away from spacecraft S, spacecraft S promptly is suspended on the center of vacuum vessel 3 by suspension rod 23, at last vertical takeoff and landing mechanism 1 is pulled out vacuum vessel 3 along guide rail 4 and move on on the carrier loader, hangs operation and so far is and finishes.
In sum, the erecting by overhang of space environment simulation equipment described in the utility model substitutes manual type with machinery to carry out spacecraft S hang erection work in vacuum vessel 3, not only saved manpower, and improved work efficiency, also guaranteed the accuracy rate of the suspension location of spacecraft S simultaneously, the more important thing is the safety of having guaranteed spacecraft S and hang the reliable of installation, avoided the generation of accident.The utility model is applicable to the installation of hanging of the spacecraft S of various different volumes sizes.
Claims (5)
1, a kind of erecting by overhang of space environment simulation equipment, be arranged in the vacuum vessel, it is characterized in that: it comprises vertical takeoff and landing mechanism and vertical hanging mechanism, this vertical takeoff and landing mechanism includes can be along guide rail come in and go out workplatform, jack and the lifting table of vacuum vessel, this lifting table is positioned at the top of workplatform, but jack is located between lifting table and the workplatform and the operate lifting platform along vertical lifting; This vertical hanging mechanism includes framework, crossbeam, suspension rod and slide block, this framework is rectangle and is fixed on the inner roof wall of vacuum vessel, the slide block of crossbeam by its two ends is connected with framework and can be along the longitudinal translation of framework, and the slide block of suspension rod by its top is connected with crossbeam and can carries out side travel along crossbeam.
2, the erecting by overhang of space environment simulation equipment according to claim 1, it is characterized in that: described vertical takeoff and landing mechanism also includes the connecting rod mechanism of parallelogram, and the upper and lower end of this connecting rod mechanism is hinged on respectively on lifting table and the workplatform so that lifting table remains level in lifting.
3, the erecting by overhang of space environment simulation equipment according to claim 1 and 2 is characterized in that: the bottom of described suspension rod is by turnbuckle and the shackle of being threaded.
4, the erecting by overhang of space environment simulation equipment according to claim 1 is characterized in that: described crossbeam is 2, and suspension rod is 4.
5, the erecting by overhang of space environment simulation equipment according to claim 1 is characterized in that: described framework is fixed on the inner roof wall of vacuum vessel by 6 fixed link suspentions.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620048129 CN200978009Y (en) | 2006-11-24 | 2006-11-24 | Hanging apparatus for spacing environment simulation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200620048129 CN200978009Y (en) | 2006-11-24 | 2006-11-24 | Hanging apparatus for spacing environment simulation device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN200978009Y true CN200978009Y (en) | 2007-11-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200620048129 Expired - Fee Related CN200978009Y (en) | 2006-11-24 | 2006-11-24 | Hanging apparatus for spacing environment simulation device |
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| CN (1) | CN200978009Y (en) |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102009750A (en) * | 2010-12-02 | 2011-04-13 | 哈尔滨工业大学 | Carriage hanging and correction mechanism and method for low-gravity experimental system of planetary exploration vehicle |
| CN102009749A (en) * | 2010-08-02 | 2011-04-13 | 清华大学 | Simulation system for low-gravity ramble |
| CN102145755A (en) * | 2010-02-10 | 2011-08-10 | 上海卫星工程研究所 | Zero-gravity suspension type deployment test device |
| CN102200454A (en) * | 2010-03-26 | 2011-09-28 | 中国航天科技集团公司第五研究院第五一○研究所 | Floating vibration isolation device for vacuum tank |
| CN102444689A (en) * | 2010-10-09 | 2012-05-09 | 中国科学院沈阳自动化研究所 | Single-rail suspension gravitational equilibrium device |
| CN102564482A (en) * | 2011-11-15 | 2012-07-11 | 上海卫星工程研究所 | Joint bearing device for vacuum vessel |
| CN102862688A (en) * | 2011-07-05 | 2013-01-09 | 哈尔滨工业大学 | Sling-type low-gravity simulation tension control buffer mechanism and adjustment method |
| CN103033351A (en) * | 2012-12-10 | 2013-04-10 | 中国飞机强度研究所 | Bunching type horizontal loading follow-up weight deducting device |
| CN103085992A (en) * | 2012-11-23 | 2013-05-08 | 北京理工大学 | Spatial microgravity simulation experiment system |
| CN103287589A (en) * | 2013-04-08 | 2013-09-11 | 北京控制工程研究所 | Microgravity experimental system for component performance verification of plate type propellant management device |
| CN103359300A (en) * | 2013-08-06 | 2013-10-23 | 北京卫星环境工程研究所 | Satellite in-orbit free boundary condition simulation device |
| CN103466487A (en) * | 2013-08-06 | 2013-12-25 | 总装备部工程设计研究总院 | Vertical servo system |
| CN104235382A (en) * | 2014-08-29 | 2014-12-24 | 杭州杭氧环保成套设备有限公司 | Connecting structure of heat sink container and ascending and descending platform |
| CN104267779A (en) * | 2014-09-16 | 2015-01-07 | 长春理工大学 | Vertical type adjusting mechanism |
| CN104803013A (en) * | 2015-04-27 | 2015-07-29 | 重庆幻羽科技有限公司 | Three-degree-of-freedom spherical movement platform |
| CN105035366A (en) * | 2015-07-22 | 2015-11-11 | 上海卫星装备研究所 | Component separating mechanism applied to vacuum low-temperature environment |
| CN105173127A (en) * | 2015-08-06 | 2015-12-23 | 哈尔滨工业大学 | Six-freedom-degree zero-gravity simulation system based on combination of hoisting and air-suspending |
-
2006
- 2006-11-24 CN CN 200620048129 patent/CN200978009Y/en not_active Expired - Fee Related
Cited By (29)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102145755A (en) * | 2010-02-10 | 2011-08-10 | 上海卫星工程研究所 | Zero-gravity suspension type deployment test device |
| CN102145755B (en) * | 2010-02-10 | 2013-03-27 | 上海卫星工程研究所 | Zero-gravity suspension type deployment test device |
| CN102200454B (en) * | 2010-03-26 | 2012-09-05 | 中国航天科技集团公司第五研究院第五一○研究所 | Floating vibration isolation device for vacuum tank |
| CN102200454A (en) * | 2010-03-26 | 2011-09-28 | 中国航天科技集团公司第五研究院第五一○研究所 | Floating vibration isolation device for vacuum tank |
| CN102009749A (en) * | 2010-08-02 | 2011-04-13 | 清华大学 | Simulation system for low-gravity ramble |
| CN102009749B (en) * | 2010-08-02 | 2013-03-27 | 清华大学 | Simulation system for low-gravity ramble |
| CN102444689A (en) * | 2010-10-09 | 2012-05-09 | 中国科学院沈阳自动化研究所 | Single-rail suspension gravitational equilibrium device |
| CN102009750A (en) * | 2010-12-02 | 2011-04-13 | 哈尔滨工业大学 | Carriage hanging and correction mechanism and method for low-gravity experimental system of planetary exploration vehicle |
| CN102009750B (en) * | 2010-12-02 | 2014-09-03 | 哈尔滨工业大学 | Carriage hanging and correction mechanism and method for low-gravity experimental system of planetary exploration vehicle |
| CN102862688A (en) * | 2011-07-05 | 2013-01-09 | 哈尔滨工业大学 | Sling-type low-gravity simulation tension control buffer mechanism and adjustment method |
| CN102862688B (en) * | 2011-07-05 | 2015-02-04 | 哈尔滨工业大学 | Sling-type low-gravity simulation tension control buffer mechanism and adjustment method |
| CN102564482A (en) * | 2011-11-15 | 2012-07-11 | 上海卫星工程研究所 | Joint bearing device for vacuum vessel |
| CN102564482B (en) * | 2011-11-15 | 2014-09-10 | 上海卫星工程研究所 | Joint bearing device for vacuum vessel |
| CN103085992A (en) * | 2012-11-23 | 2013-05-08 | 北京理工大学 | Spatial microgravity simulation experiment system |
| CN103085992B (en) * | 2012-11-23 | 2015-11-25 | 北京理工大学 | Spatial microgravity simulation experiment system |
| CN103033351A (en) * | 2012-12-10 | 2013-04-10 | 中国飞机强度研究所 | Bunching type horizontal loading follow-up weight deducting device |
| CN103033351B (en) * | 2012-12-10 | 2015-10-28 | 中国飞机强度研究所 | The servo-actuated button refitting of burst-oriented horizontal addload is put |
| CN103287589A (en) * | 2013-04-08 | 2013-09-11 | 北京控制工程研究所 | Microgravity experimental system for component performance verification of plate type propellant management device |
| CN103287589B (en) * | 2013-04-08 | 2015-07-08 | 北京控制工程研究所 | Microgravity experimental system for component performance verification of plate type propellant management device |
| CN103466487A (en) * | 2013-08-06 | 2013-12-25 | 总装备部工程设计研究总院 | Vertical servo system |
| CN103359300B (en) * | 2013-08-06 | 2015-08-26 | 北京卫星环境工程研究所 | Satellite is free boundary condition analog machine in-orbit |
| CN103359300A (en) * | 2013-08-06 | 2013-10-23 | 北京卫星环境工程研究所 | Satellite in-orbit free boundary condition simulation device |
| CN104235382A (en) * | 2014-08-29 | 2014-12-24 | 杭州杭氧环保成套设备有限公司 | Connecting structure of heat sink container and ascending and descending platform |
| CN104235382B (en) * | 2014-08-29 | 2016-04-13 | 杭州杭氧低温容器有限公司 | The linkage structure of a kind of heat sink container and lift platform |
| CN104267779A (en) * | 2014-09-16 | 2015-01-07 | 长春理工大学 | Vertical type adjusting mechanism |
| CN104267779B (en) * | 2014-09-16 | 2016-07-06 | 长春理工大学 | Vertical guiding mechanism |
| CN104803013A (en) * | 2015-04-27 | 2015-07-29 | 重庆幻羽科技有限公司 | Three-degree-of-freedom spherical movement platform |
| CN105035366A (en) * | 2015-07-22 | 2015-11-11 | 上海卫星装备研究所 | Component separating mechanism applied to vacuum low-temperature environment |
| CN105173127A (en) * | 2015-08-06 | 2015-12-23 | 哈尔滨工业大学 | Six-freedom-degree zero-gravity simulation system based on combination of hoisting and air-suspending |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20071121 Termination date: 20121124 |