CN204726686U - A kind of development mechanism of satellite sun windsurfing - Google Patents
A kind of development mechanism of satellite sun windsurfing Download PDFInfo
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- CN204726686U CN204726686U CN201520384925.0U CN201520384925U CN204726686U CN 204726686 U CN204726686 U CN 204726686U CN 201520384925 U CN201520384925 U CN 201520384925U CN 204726686 U CN204726686 U CN 204726686U
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- torsion spring
- hinge
- securing rod
- development mechanism
- strand
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Abstract
The utility model proposes a kind of development mechanism of satellite sun windsurfing, comprise: male hinge, rotating shaft, torsion spring axle sleeve, torsion spring, slideway, female strand, oscillating bearing, securing rod and Compress Spring; Male hinge and female strand are separately fixed on satellite main body structure and solar array; Torsion spring axle sleeve is placed in rotating shaft, and torsion spring set is placed in torsion axis and puts; Rotating shaft one end connects oscillating bearing, and the other end is arranged in public hinge; Torsion spring two ends are fixedly connected with female strand with male hinge respectively; Oscillating bearing is fixed in female strand; Male hinge and female hinge are rotationally connected by oscillating bearing, rotating shaft, torsion spring axle sleeve and torsion spring, utilize torsion spring moment to launch closed windsurfing; The reeded slideway of surface band is fixed in public hinge; Securing rod is arranged in female hinge; Compress Spring is placed on institute's securing rod, and its two ends withstand securing rod and female strand respectively; Satellite sun outspreading sailboard, female strand drives securing rod to slide into groove along slideway, and Compress Spring promotes securing rod and inserts groove, the expanded angle of locking windsurfing.
Description
Technical field
The utility model relates to a kind of development mechanism of satellite sun windsurfing, for the expansion of solar array relative to satellite body mechanism and the lock in place of expanded angle.
Background technology
The development mechanism of satellite sun windsurfing plays an important role in the transmitting and operational process of satellite, the expansion of solar array is the very important link that satellite enters real mode of operation, if solar array can not launch, satellite will diminish and come out of action ability gradually because of battery remaining power, and then have a strong impact on the life-span that satellite flies in-orbit, therefore the development mechanism of satellite sun windsurfing is the critical component ensureing that satellite normally runs.
The development mechanism more complicated of widespread use on current satellite, and require relatively high to processing and setting accuracy, thus bring high cost, some low cost small satellites are forced to adopt body dress formula cell panel, thus sacrifice a lot of function and performance because of electricity deficiency, govern the development of low cost small satellite.
Utility model content
The utility model proposes a kind of development mechanism of satellite sun windsurfing, for the expansion of solar array relative to satellite body mechanism and the lock in place of expanded angle.This development mechanism comprises with lower component: male hinge, rotating shaft, torsion spring axle sleeve, torsion spring, slideway, female strand, oscillating bearing, securing rod and Compress Spring;
Described public affairs hinge is fixedly mounted in satellite main body structure; Described mother's strand is fixedly mounted on satellite sun windsurfing;
Described torsion spring axle sleeve is placed in described rotating shaft, and described torsion spring set is placed in described torsion axis and puts; Described rotating shaft one end connects oscillating bearing, and the other end is arranged in described public affairs hinge; Described one end twists with described mother and is fixedly connected with, and the other end cuts with scissors with described public affairs and is fixedly connected with; Described oscillating bearing is fixedly mounted in described mother's strand; Described male hinge and female hinge are rotationally connected by described oscillating bearing, rotating shaft, torsion spring axle sleeve and torsion spring, thus utilize the moment of described torsion spring to launch and closed satellite sun windsurfing;
Described slideway is fixedly mounted in described public affairs hinge, and its surface band is fluted; Described securing rod is arranged in described mother's hinge; Described Compress Spring is placed on described securing rod, and its two ends withstand described securing rod and described mother's strand respectively; After satellite sun outspreading sailboard, described mother's strand drives described securing rod to slide along described slideway, and when arriving described groove, described Compress Spring promotes described securing rod and inserts described groove, thus the expanded angle of locking satellite solar array.
Preferably, described public affairs hinge has several through holes, and the described torsion spring other end selects one of them through hole to be fixed connection, by the moment selecting different through holes to regulate described torsion spring.More accurate in order to regulate, described through hole number can be 16.
Preferably, in order to obtain the expansion situation of solar array in real time, described development mechanism also comprises one for sending micro-switch and a positioning convex of telemetered signal; Described micro-switch is fixedly mounted in described public affairs hinge, and described positioning convex is fixedly mounted in described mother's strand; After satellite sun outspreading sailboard, described positioning convex makes the shell fragment of described micro-switch be in impaction state.
Preferably, in all parts that above-mentioned development mechanism comprises, the parts of movable contact adopt different metal materials each other.Described metal material can comprise aluminum alloy, titanium alloy and corrosion-resistant steel.Further, described public affairs hinge is aluminum alloy material, and described rotating shaft is titanium alloy material, and described torsion spring axle sleeve is aluminum alloy material, and described slideway is titanium alloy material, and described mother's hinge is aluminum alloy material, and described securing rod is stainless steel.
Preferably, in all parts that above-mentioned development mechanism comprises, the parts surface of movable contact all adopts the process of molybdenum disulphide solid lubricant coating each other.
Compared with existing satellite sun mechanism for outspreading sailboard: the design complexities of the development mechanism that the utility model provides is lower, to processing and setting accuracy less demanding, have that cost is low, system reliability is high and lightweight advantage, be easy to Installation And Test.
Accompanying drawing explanation
Fig. 1 is that the development mechanism of embodiment is at the structural position view of satellite main body;
Fig. 2 is the section-drawing of the public affairs hinge of the development mechanism of embodiment;
Fig. 3 is the section-drawing of mother's hinge of the development mechanism of embodiment;
Fig. 4 is the overall section-drawing of the development mechanism of embodiment;
Fig. 5 is the overall diagram of the development mechanism of embodiment;
Description of reference numerals: 1-satellite main body structure; The development mechanism of 2-satellite sun windsurfing; 3-satellite sun windsurfing; 21-public affairs hinge; 211-stepped hole; 212-first through hole; 213-second through hole; 22-mother hinge; 221-third through-hole; 222-fourth hole; 223-positioning convex; 4-fastener; 5-torsion spring axle sleeve; 6-torsion spring; 7-rotating shaft; 8-oscillating bearing; 9-slideway; 10-micro-switch; 11-securing rod; 12-Compress Spring; 13-fastener; 14-fastener.
Detailed description of the invention
For making the object of the utility model embodiment, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the utility model embodiment, technical scheme in the utility model embodiment is clearly and completely described, obviously, described embodiment is the utility model part embodiment, instead of whole embodiments; It should be noted that, when not conflicting, the embodiment in the application and the feature in embodiment can combine mutually.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.
The satellite main body structure of the present embodiment as shown in Figure 1, satellite main body structure 1 is connected with the development mechanism 2 of satellite sun windsurfing 3 by satellite sun windsurfing, and when the development mechanism of satellite sun windsurfing provides satellite sun windsurfing 3 to launch, required moment of torsion and satellite sun windsurfing 3 launch the lock in place function after putting in place.
The parts that the deployed configuration of satellite sun windsurfing comprises have: male hinge, rotating shaft, torsion spring axle sleeve, torsion spring, slideway, micro-switch, female strand, oscillating bearing, securing rod, Compress Spring and positioning convex.Fig. 2 is the section-drawing of public hinge, and Fig. 3 is the section-drawing of female hinge, and Fig. 4 is the overall section-drawing of development mechanism, and Fig. 5 is the unitary side view of development mechanism.The following detailed description of deployed configuration each parts between annexation.
Public hinge 21 is fixedly mounted in satellite main body structure by fastener 13, and female strand 22 is fixedly mounted on satellite sun windsurfing by fastener 14, is rotationally connected between male hinge 21 and female strand 22.
The bottom of public hinge has a stepped hole 211, is also evenly distributed with 16 the first through holes 212 around stepped hole, and two the second through holes 213 are arranged at the top of public hinge.Stepped hole 211 is for installing one end (other end of rotating shaft 7 connects oscillating bearing 8) of rotating shaft 7, and torsion spring axle sleeve 5 is placed in rotating shaft 7, and torsion spring 6 is placed on torsion spring axle sleeve 5.One of them selecting 16 the first through holes 212, to install one end (other end of torsion spring twist be fixedly connected with) with mother of torsion spring, is fixed by fastener 4.Two the second through holes 213 are for being fixedly mounted on public hinge by fastener by slideway 9, and the surface of slideway 9 is with a semi-circular recesses.Why the present embodiment arranges multiple first through hole is in order to the moment by selecting the first different through hole installation torsion springs to regulate torsion spring, thus eliminates because torsion spring manufactures the error produced.More accurate in order to regulate, the number of first through hole of the present embodiment is set to 16.In order to obtain Stretching of solar wings situation in real time, above slideway 9, also secure the micro-switch 10 that can send telemetered signal.
Female hinge 22 have a third through-hole 221, fourth hole 222 and a positioning convex 223.Third through-hole 221 for installing oscillating bearing 8, the other end of oscillating bearing 8 connection rotating shaft 7.Fourth hole 222 is for installing securing rod 11 and Compress Spring 12, and Compress Spring 12 is placed on securing rod 11, and its two ends withstand securing rod 11 and female strand 22 respectively.
Male hinge 21 and female hinge 22 are rotationally connected by oscillating bearing 8, rotating shaft 7, torsion spring axle sleeve 5 and torsion spring 6, thus utilize the moment of torsion spring 6 to launch and closed satellite sun windsurfing.After satellite sun outspreading sailboard, female strand 22 drives securing rod 11 to slide along slideway 9, when securing rod 11 arrives semi-circular recesses place, Compress Spring 12 promotes the semi-circular recesses that securing rod 11 inserts slideway 9, thus the expanded angle of locking satellite solar array, and the shell fragment now on micro-switch 10 is compressed by positioning convex 223, trigger micro-switch and send telemetered signal, system can obtain Stretching of solar wings situation in real time.When solar array 3 closes, only need that securing rod 11 is pulled out the semi-circular recesses departing from road slideway 9 outward and can realize again closing.
In all parts that development mechanism comprises, the parts of movable contact can adopt different metal materials each other, to avoid the problem occurring the mutual cold welding of parts in space.The adoptable metal material of parts comprises aluminum alloy, titanium alloy and corrosion-resistant steel.In the present embodiment, public hinge 21 is aluminum alloy material, and rotating shaft 7 is titanium alloy material, and torsion spring axle sleeve 5 is aluminum alloy material, and slideway 9 is titanium alloy material, and female hinge 22 is aluminum alloy material, and securing rod 11 is stainless steel.In addition, the parts surface of movable contact all adopts the process of molybdenum disulphide solid lubricant coating also can avoid cold welding problem each other.
When adopting the development mechanism of the present embodiment to carry out expansion and the lock test of solar array 3 on ground, by repeatedly Cyclic test, system reliability is high.
Last it is noted that above embodiment is only in order to illustrate the technical solution of the utility model, be not intended to limit; Although be described in detail the utility model with reference to previous embodiment, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of each embodiment technical scheme of the utility model.
Claims (8)
1. a development mechanism for satellite sun windsurfing, is characterized in that:
Described development mechanism comprises with lower component: male hinge, rotating shaft, torsion spring axle sleeve, torsion spring, slideway, female strand, oscillating bearing, securing rod and Compress Spring;
Described public affairs hinge is fixedly mounted in satellite main body structure; Described mother's strand is fixedly mounted on satellite sun windsurfing;
Described torsion spring axle sleeve is placed in described rotating shaft, and described torsion spring set is placed in described torsion axis and puts; Described rotating shaft one end connects oscillating bearing, and the other end is arranged in described public affairs hinge; Described one end twists with described mother and is fixedly connected with, and the other end cuts with scissors with described public affairs and is fixedly connected with; Described oscillating bearing is fixedly mounted in described mother's strand; Described male hinge and female hinge are rotationally connected by described oscillating bearing, rotating shaft, torsion spring axle sleeve and torsion spring, thus utilize the moment of described torsion spring to launch and closed satellite sun windsurfing;
Described slideway is fixedly mounted in described public affairs hinge, and its surface band is fluted; Described securing rod is arranged in described mother's hinge; Described Compress Spring is placed on described securing rod, and its two ends withstand described securing rod and described mother's strand respectively; After satellite sun outspreading sailboard, described mother's strand drives described securing rod to slide along described slideway, and when arriving described groove, described Compress Spring promotes described securing rod and inserts described groove, thus the expanded angle of locking satellite solar array.
2. development mechanism according to claim 1, is characterized in that:
Described public affairs hinge has several through holes, and the described torsion spring other end selects one of them through hole to be fixed connection, by the moment selecting different through holes to regulate described torsion spring.
3. development mechanism according to claim 2, is characterized in that: described through hole has 16.
4. development mechanism according to claim 1, is characterized in that:
Described development mechanism also comprises one for sending micro-switch and a positioning convex of telemetered signal; Described micro-switch is fixedly mounted in described public affairs hinge, and described positioning convex is fixedly mounted in described mother's strand; After satellite sun outspreading sailboard, described positioning convex makes the shell fragment of described micro-switch be in impaction state.
5. the development mechanism according to Claims 1 to 4 any one, is characterized in that:
In all parts that described development mechanism comprises, the parts of movable contact adopt different metal materials each other.
6. development mechanism according to claim 5, is characterized in that:
Described metal material comprises aluminum alloy, titanium alloy and corrosion-resistant steel.
7. development mechanism according to claim 6, is characterized in that:
Described public affairs hinge is aluminum alloy material, and described rotating shaft is titanium alloy material, and described torsion spring axle sleeve is aluminum alloy material, and described slideway is titanium alloy material, and described mother's hinge is aluminum alloy material, and described securing rod is stainless steel.
8. the development mechanism according to Claims 1 to 4 any one, is characterized in that:
In all parts that described development mechanism comprises, the parts surface of movable contact is molybdenum disulphide solid lubricant coating each other.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520384925.0U CN204726686U (en) | 2015-06-05 | 2015-06-05 | A kind of development mechanism of satellite sun windsurfing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520384925.0U CN204726686U (en) | 2015-06-05 | 2015-06-05 | A kind of development mechanism of satellite sun windsurfing |
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| Publication Number | Publication Date |
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| CN204726686U true CN204726686U (en) | 2015-10-28 |
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| CN201520384925.0U Expired - Fee Related CN204726686U (en) | 2015-06-05 | 2015-06-05 | A kind of development mechanism of satellite sun windsurfing |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005491A (en) * | 2016-05-31 | 2016-10-12 | 南京理工大学 | Cubesat magnetometer expanding mechanism |
| CN106275515A (en) * | 2015-06-05 | 2017-01-04 | 北京信威通信技术股份有限公司 | A kind of development mechanism of satellite sun windsurfing |
| CN107757952A (en) * | 2017-10-09 | 2018-03-06 | 长光卫星技术有限公司 | Microsatellite solar wing spreading locking device |
| CN108298108A (en) * | 2017-12-22 | 2018-07-20 | 兰州空间技术物理研究所 | A kind of expansion locking mechanism based on torsionspring |
| CN106628267B (en) * | 2016-10-28 | 2019-04-09 | 浙江大学 | A kind of expansion of skin Nano satellite solar energy turnover panel and locking device |
| CN112074457A (en) * | 2018-03-07 | 2020-12-11 | 牛津空间系统有限公司 | Deployable spacecraft body |
| CN112340068A (en) * | 2020-11-06 | 2021-02-09 | 长光卫星技术有限公司 | Solar sailboard unfolding system based on hot knife |
-
2015
- 2015-06-05 CN CN201520384925.0U patent/CN204726686U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106275515A (en) * | 2015-06-05 | 2017-01-04 | 北京信威通信技术股份有限公司 | A kind of development mechanism of satellite sun windsurfing |
| CN106005491A (en) * | 2016-05-31 | 2016-10-12 | 南京理工大学 | Cubesat magnetometer expanding mechanism |
| CN106005491B (en) * | 2016-05-31 | 2018-04-03 | 南京理工大学 | Cube star magnetometer development mechanism |
| CN106628267B (en) * | 2016-10-28 | 2019-04-09 | 浙江大学 | A kind of expansion of skin Nano satellite solar energy turnover panel and locking device |
| CN107757952A (en) * | 2017-10-09 | 2018-03-06 | 长光卫星技术有限公司 | Microsatellite solar wing spreading locking device |
| CN107757952B (en) * | 2017-10-09 | 2023-05-30 | 长光卫星技术股份有限公司 | Microsatellite solar wing span unlocking and fixing device |
| CN108298108A (en) * | 2017-12-22 | 2018-07-20 | 兰州空间技术物理研究所 | A kind of expansion locking mechanism based on torsionspring |
| CN112074457A (en) * | 2018-03-07 | 2020-12-11 | 牛津空间系统有限公司 | Deployable spacecraft body |
| CN112340068A (en) * | 2020-11-06 | 2021-02-09 | 长光卫星技术有限公司 | Solar sailboard unfolding system based on hot knife |
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Legal Events
| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PP01 | Preservation of patent right | ||
| PP01 | Preservation of patent right |
Effective date of registration: 20191121 Granted publication date: 20151028 |
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| PD01 | Discharge of preservation of patent | ||
| PD01 | Discharge of preservation of patent |
Date of cancellation: 20200710 Granted publication date: 20151028 |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151028 Termination date: 20200605 |