CN103010489B - Novel separation mechanism device for controlling nano-satellite and separation method of separation mechanism device - Google Patents
Novel separation mechanism device for controlling nano-satellite and separation method of separation mechanism device Download PDFInfo
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- CN103010489B CN103010489B CN201210573701.5A CN201210573701A CN103010489B CN 103010489 B CN103010489 B CN 103010489B CN 201210573701 A CN201210573701 A CN 201210573701A CN 103010489 B CN103010489 B CN 103010489B
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Abstract
The invention discloses a novel separation mechanism device for controlling separation movement of a nano-satellite and a separation method of the separation mechanism device. A separation mechanism adopts a fully-open structure. The bottom plate of the separation mechanism is connected with a rocket platform. During fixation of a satellite body, the satellite body is tensioned and fixed by using titanium rods and by compressing springs through pushrods; and during separation, an initiating explosive device cuts off the titanium rods and the compressed springs release elastic force to push the pushrods to act on the satellite body, so the separation of the separation mechanism and the satellite can be realized. The novel separation mechanism device for controlling the nano-satellite and the separation method of the separation mechanism device have the advantages that the satellite can be separated from the separation mechanism at normal speed when the satellite arrives at a pre-selected orbit, the separation mechanism device and the separation method thereof are suitable for the separation of nano-satellites with different shapes, the weight of the satellite separation mechanism is reduced, the satellite and the separation mechanism are enabled to be more convenient, rapid and reliable to install, and the safety of the satellite and the separation mechanism is guaranteed.
Description
Technical field
The present invention relates to a kind of separation device device and separation method thereof of Novel control Nano satellite, be widely used in microsatellite field.
Background technology
Conventional satellite is separated with carrier rocket the separate mode often adopting band and explosive bolt to combine.This isolation technics is comparatively ripe, and large satellite also extensively adopts.But along with the fast development of MEMS technology, Nano satellite technology have also been obtained fast development nearly ten years.The advantage of Nano satellite is that its volume is little, lightweight and it is convenient to launch.Traditional separate mode due to comparatively complicated, weight is comparatively large and cost is higher, is difficult to the advantage embodying Nano satellite.International Nano satellite separation device majority adopts " square tub " structure, and namely Nano satellite is encased in inside a closed square bucket completely.The weak point of this structure is: require that the profile of Nano satellite can not have obvious projection, and this just gives the size of antenna, the design of mounting means brings great constraint; Adopt the structure closed, be not easy to the installation of Nano satellite.Most separation devices celestial body just outward movment under the promotion of spring when hatch door is opened, very likely there is collision and the scraping of celestial body surface and hatch door in this, thus damages the cell piece of satellite surface.In addition, if adopt this structure, its size and weight will inevitably increase along with the increase of celestial body volume.
Summary of the invention
In order to overcome the deficiencies in the prior art, the object of this invention is to provide separation device device and the separation method thereof of a kind of Novel control Nano satellite disengaging movement.
A separation device device for Novel control Nano satellite, comprises base plate, four pieces of stay bearing plates, four pieces of gussets, four cylindrical springs, four spring push-rods, four spring spools; Every block gusset is fixed between two pieces of stay bearing plates, and every block stay bearing plate fixes two pieces of gussets, and the bottom of gusset is connected by screw and is fixed on base plate; Spring push-rod is embedded in cylindrical spring, and cylindrical spring is contained in spring spool, and spring spool is connected by screw and is fixed on base plate; Spring push-rod withstands in the circular hole corresponding to Nano satellite celestial body square framework.
Described spring push-rod is in a free state by cylindrical spring jack-up, not constraint between spring push-rod and cylindrical spring, round platform bottom spring push-rod drops in cylindrical spring, there is the gap of 1mm between the two, this guarantees cylindrical spring just pressurized and the effect that can not be reversed when mounted, thus avoid the rolling deviation of Nano satellite.
There is bearing pin the upper end of described stay bearing plate, and the bearing pin on stay bearing plate embeds carrying transverse load in hole corresponding on Nano satellite celestial body square framework;
Described base plate utilizes two titanium bars and nut to be fixed by Nano satellite celestial body from the diagonal position of Nano satellite celestial body.
Described device is separated the method for Nano satellite, when Nano satellite is fixed, base plate is connected with rocket platform, and four holes of Nano satellite celestial body square framework bottom surface correspond to spring push-rod, and the boss on each stay bearing plate corresponds to the aperture in four corners of Nano satellite celestial body square framework bottom surface; When Nano satellite celestial body square frame installation is to the separation device device of described control Nano satellite, apply external force, by spring push-rod, cylindrical spring is compressed, thus utilize two titanium bars and nut to be fixed on base plate from the diagonal position of Nano satellite celestial body by Nano satellite celestial body, when satellite arrives planned orbit, receive separation signal, cut off by titanium bar, Nano satellite celestial body realizes the satellite and the rocket and is separated under the combined action of four cylindrical springs.
Beneficial effect of the present invention: the first, adopt the consistent cylindrical spring substantially without acceptance of persons of four elasticity moduluss, efficiently reduce satellite by the eccentric phenomena in spring push, the second, spring push-rod is embedded in cylindrical spring, round platform bottom spring push-rod drops in cylindrical spring, there is the gap of 1mm between the two, this guarantees cylindrical spring just pressurized and the effect that can not be reversed when mounted, thus avoid the rolling deviation of satellite.Three, cylindrical spring is contained in spring spool, and spring push-rod is embedded in spring, and spring spool can give cylindrical spring directional tagging.Four, separation device adopts open structure, lightweight, and volume is little, avoids hooking, and separation device and celestial body are not interfered, and separation process is more simply agile, and controllability improves.
Accompanying drawing explanation
The separation device apparatus structure schematic diagram of a kind of Novel control Nano satellite of Fig. 1;
The separation device device front elevation of a kind of Novel control Nano satellite of Fig. 2;
The separation device device birds-eye view of a kind of Novel control Nano satellite of Fig. 3;
The base arrangement schematic diagram of the separation device device of a kind of Novel control Nano satellite of Fig. 4;
The supporting plate structure schematic diagram of the separation device device of a kind of Novel control Nano satellite of Fig. 5;
The reinforcing plate structure schematic diagram of the separation device device of a kind of Novel control Nano satellite of Fig. 6;
The mounting structure schematic diagram of the cylindrical spring of the separation device device of a kind of Novel control Nano satellite of Fig. 7, spring push-rod, spring spool;
The cylindrical spring structural representation of the separation device device of a kind of Novel control Nano satellite of Fig. 8;
The spring push-rod structural representation of the separation device device of a kind of Novel control Nano satellite of Fig. 9;
The spring spool structural representation of the separation device device of a kind of Novel control Nano satellite of Figure 10;
Description of reference numerals: 1, base plate; 2, stay bearing plate; 3, gusset; 4, cylindrical spring; 5, spring push-rod; 6, spring spool.
Specific embodiments
Below in conjunction with drawings and Examples, the present invention is further illustrated.
As shown in Figure 1, a kind of separation device device of Novel control Nano satellite, comprises base plate 1, four pieces of stay bearing plates 2, four pieces of gussets 3, four cylindrical springs 4, four spring push-rods 5, four spring spools 6; Every block gusset is fixed between two pieces of stay bearing plates 2, and every block stay bearing plate 2 fixes two pieces of gussets 3, and the bottom of gusset 3 is connected by screw and is fixed on base plate 1; Spring push-rod 5 is embedded in cylindrical spring 4, and cylindrical spring 4 is contained in spring spool 6, and spring spool 6 is connected by screw and is fixed on base plate 1; Spring push-rod 5 withstands in the circular hole corresponding to Nano satellite celestial body square framework.
As shown in Figure 7, described spring push-rod 5 is in a free state by cylindrical spring 4 jack-up, not constraint between spring push-rod 5 and cylindrical spring 4, round platform bottom spring push-rod 5 drops in cylindrical spring 4, there is the gap of 1mm between the two, this guarantees cylindrical spring 4 just pressurized and the effect that can not be reversed when mounted, thus avoid the rolling deviation of Nano satellite.
As shown in Figure 5, there is bearing pin the upper end of described stay bearing plate 2, and the bearing pin on stay bearing plate 2 embeds carrying transverse load in hole corresponding on Nano satellite celestial body square framework;
As shown in Figure 4, described base plate 1 utilizes two titanium bars and nut to be fixed by Nano satellite celestial body from the diagonal position of Nano satellite celestial body.
As shown in Figure 1, described device is separated the method for Nano satellite, when Nano satellite is fixed, base plate 1 is connected with rocket platform, four holes of Nano satellite celestial body square framework bottom surface correspond to spring push-rod 5, and the boss on each stay bearing plate 2 corresponds to the aperture in four corners of Nano satellite celestial body square framework bottom surface; When Nano satellite celestial body square frame installation is to the separation device device of described control Nano satellite, apply external force, by spring push-rod 5, cylindrical spring 4 is compressed, thus utilize two titanium bars and nut to be fixed on base plate 1 from the diagonal position of Nano satellite celestial body by Nano satellite celestial body, when satellite arrives planned orbit, receive separation signal, cut off by titanium bar, Nano satellite celestial body realizes the satellite and the rocket and is separated under the combined action of four cylindrical springs 4.
Claims (1)
1. a separation device device for Novel control Nano satellite, is characterized in that: it comprises base plate (1), four pieces of stay bearing plates (2), four pieces of gussets (3), four cylindrical springs (4), four spring push-rods (5), four spring spools (6); Every block gusset (3) is fixed between two pieces of stay bearing plates (2), and every block stay bearing plate (2) fixes two pieces of gussets (3), and the bottom of gusset (3) is connected by screw and is fixed on base plate (1); Spring push-rod (5) is embedded in cylindrical spring (4), and cylindrical spring (4) is contained in spring spool (6), and spring spool (6) is connected by screw and is fixed on base plate (1); Spring push-rod (5) withstands in the circular hole corresponding to Nano satellite celestial body square framework;
Described spring push-rod (5), in a free state by cylindrical spring (4) jack-up, does not retrain between spring push-rod (5) and cylindrical spring (4), and the round platform of spring push-rod (5) bottom drops in cylindrical spring (4), has the gap of 1mm between the two;
There is bearing pin the upper end of described stay bearing plate (2), and the bearing pin on stay bearing plate (2) embeds carrying transverse load in hole corresponding on Nano satellite celestial body square framework;
Described base plate (1) utilizes two titanium bars and nut to be fixed by Nano satellite celestial body from the diagonal position of Nano satellite celestial body.
2.a kind of device as claimed in claim 1 is separated the method for Nano satellite, it is characterized in that: when Nano satellite is fixed, base plate (1) is connected with rocket platform, four holes of Nano satellite celestial body square framework bottom surface correspond to spring push-rod (5), and the boss on each stay bearing plate (2) corresponds to the aperture in four corners of Nano satellite celestial body square framework bottom surface; When Nano satellite celestial body square frame installation is to the separation device device of described control Nano satellite, apply external force, by spring push-rod (5), cylindrical spring (4) is compressed, thus utilize two titanium bars and nut to be fixed on base plate (1) from the diagonal position of Nano satellite celestial body by Nano satellite celestial body, when satellite arrives planned orbit, receive separation signal, cut off by titanium bar, Nano satellite celestial body realizes the satellite and the rocket and is separated under the combined action of four cylindrical springs (4).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210573701.5A CN103010489B (en) | 2012-12-26 | 2012-12-26 | Novel separation mechanism device for controlling nano-satellite and separation method of separation mechanism device |
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| CN201210573701.5A CN103010489B (en) | 2012-12-26 | 2012-12-26 | Novel separation mechanism device for controlling nano-satellite and separation method of separation mechanism device |
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| CN103010489A CN103010489A (en) | 2013-04-03 |
| CN103010489B true CN103010489B (en) | 2014-12-31 |
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Families Citing this family (29)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104058107B (en) * | 2014-05-23 | 2015-12-02 | 北京空间飞行器总体设计部 | A kind of satellite and the rocket are separated impact-reducing connecting device |
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| CN111891390B (en) * | 2020-08-11 | 2021-08-10 | 中国科学院微小卫星创新研究院 | Satellite interface, connection method thereof and satellite system |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102009746A (en) * | 2010-11-08 | 2011-04-13 | 航天东方红卫星有限公司 | Octagonal battery-equipped array upright post micro satellite configuration |
| CN202054146U (en) * | 2011-04-18 | 2011-11-30 | 孟宪红 | Inside bayonet separating unlocking device |
| RU2442728C1 (en) * | 2010-10-25 | 2012-02-20 | Учреждение Российской академии наук Институт космических исследований РАН (ИКИ РАН) | Adapter for connection of small spacecraft and its final orbital injection device |
| CN202320803U (en) * | 2011-10-23 | 2012-07-11 | 佳木斯大学 | Memorial alloy unlocking mechanism |
| CN202320802U (en) * | 2011-10-13 | 2012-07-11 | 孟宪红 | Nano-satellite separating and unlocking device |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6227493B1 (en) * | 1999-04-06 | 2001-05-08 | Planetary Systems Corporation | Reusable, separable, structural connector assembly |
| DE102006043660B4 (en) * | 2006-09-18 | 2008-07-10 | Astro- Und Feinwerktechnik Adlershof Gmbh | Transport and ejection unit for picosatellites |
-
2012
- 2012-12-26 CN CN201210573701.5A patent/CN103010489B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2442728C1 (en) * | 2010-10-25 | 2012-02-20 | Учреждение Российской академии наук Институт космических исследований РАН (ИКИ РАН) | Adapter for connection of small spacecraft and its final orbital injection device |
| CN102009746A (en) * | 2010-11-08 | 2011-04-13 | 航天东方红卫星有限公司 | Octagonal battery-equipped array upright post micro satellite configuration |
| CN202054146U (en) * | 2011-04-18 | 2011-11-30 | 孟宪红 | Inside bayonet separating unlocking device |
| CN202320802U (en) * | 2011-10-13 | 2012-07-11 | 孟宪红 | Nano-satellite separating and unlocking device |
| CN202320803U (en) * | 2011-10-23 | 2012-07-11 | 佳木斯大学 | Memorial alloy unlocking mechanism |
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