CN103010489A - 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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- CN103010489A CN103010489A CN2012105737015A CN201210573701A CN103010489A CN 103010489 A CN103010489 A CN 103010489A CN 2012105737015 A CN2012105737015 A CN 2012105737015A CN 201210573701 A CN201210573701 A CN 201210573701A CN 103010489 A CN103010489 A CN 103010489A
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Abstract
The invention discloses a novel separation mechanism device for controlling 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 novel control and receive separation device device and the separation method thereof of satellite, be widely used in the microsatellite field.
Background technology
Conventional satellite and carrier rocket separate the separate mode that often adopts band and explosive bolt combination.This isolation technics is comparatively ripe, also extensively adopts on large satellite.But along with the fast development of MEMS technology, the satellite technology of receiving over past ten years has also obtained fast development.The advantage of satellite received is that its volume is little, lightweight and emission is convenient.Traditional separate mode because comparatively complicated, weight is large and cost is higher, is difficult to embody the advantage of cashier's satellite.The international most employings of satellite separation device " the side's bucket formula " structure of receiving, the satellite of namely receiving is encased in inside side's bucket of a sealing fully.The weak point of this structure is: the profile of satellite of requiring to receive can not have obvious projection, and this brings great constraint just for the size of antenna, the design of mounting means; Adopt the structure of sealing, be not easy to receive the installation of satellite.Most separation devices are celestial body outward movment under the promotion of spring just when hatch door is opened, and collision and the scraping of celestial body surface and hatch door very likely occur for this, thus the cell piece of damage 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 purpose of this invention is to provide a kind of novel control and receive separation device device and the separation method thereof of satellite disengaging movement.
The separation device device of satellite is received in a kind of novel control, comprises base plate, four stay bearing plates, four gussets, four cylindrical springs, four spring push-rods, four spring spools; Every gusset is fixed between two stay bearing plates, and every stay bearing plate is fixed two gussets, and the bottom of gusset is connected by screw and is fixed on the base plate; Spring push-rod is embedded in the cylindrical spring, and cylindrical spring is contained in the spring spool, and spring spool is connected by screw and is fixed on the base plate; Spring push-rod withstands on to be received in the corresponding circular hole of satellite celestial body square framework.
Described spring push-rod under free state by cylindrical spring jack-up, not constraint between spring push-rod and the cylindrical spring, the round platform of spring push-rod bottom drops in the cylindrical spring, the gap that 1mm is arranged between the two, this has just guaranteed when mounted just pressurized and the effect that can not be reversed of cylindrical spring, thereby has avoided receiving the rolling deviation of satellite.
There is bearing pin the upper end of described stay bearing plate, and bearing pin on the stay bearing plate embeds to receive and carries transverse load in the corresponding hole on the satellite celestial body square framework;
Described base plate utilizes two titanium bars and nut will receive the satellite celestial body and fix from receiving the diagonal position of satellite celestial body.
Described device separates the method for satellite received, receiving satellite fixedly the time, base plate links to each other with the rocket platform, receives four holes of satellite celestial body square framework bottom surface corresponding to spring push-rod, and the boss on each stay bearing plate is corresponding to receiving the aperture in four corners of satellite celestial body square framework bottom surface; When receiving satellite celestial body square frame installation when receiving the separation device device of satellite to described control, apply external force, by spring push-rod cylindrical spring is compressed, thereby utilize two titanium bars and nut will receive the satellite celestial body and be fixed on the base plate from receiving the diagonal position of satellite celestial body, when satellite arrives planned orbit, receive separation signal, the titanium bar cut off that the satellite celestial body of receiving realizes that under the combined action of four cylindrical springs the satellite and the rocket separate.
Beneficial effect of the present invention: the first, adopt the consistent cylindrical spring substantially without acceptance of persons of four elasticity moduluss, effectively reduced satellite by the eccentric phenomena in the spring push, the second, spring push-rod is embedded in the cylindrical spring, the round platform of spring push-rod bottom drops in the cylindrical spring, the gap that 1mm is arranged between the two, this has just guaranteed when mounted just pressurized and the effect that can not be reversed of cylindrical spring, thereby has avoided the rolling deviation of satellite.Three, cylindrical spring is contained in the spring spool, and spring push-rod is embedded in the spring, and spring spool can give the cylindrical spring directional tagging.Four, separation device adopts open structure, and lightweight, volume is little, has avoided hooking, and separation device and celestial body are not interfered, and separation process is more simply agile, and controllability improves.
Description of drawings
The separation device apparatus structure scheme drawing of satellite is received in a kind of novel control of Fig. 1;
The separation device device front elevation of satellite is received in a kind of novel control of Fig. 2;
The separation device device birds-eye view of satellite is received in a kind of novel control of Fig. 3;
The base arrangement scheme drawing of separation device device of satellite is received in a kind of novel control of Fig. 4;
The supporting plate structure scheme drawing of separation device device of satellite is received in a kind of novel control of Fig. 5;
The reinforcing plate structure scheme drawing of separation device device of satellite is received in a kind of novel control of Fig. 6;
Cylindrical spring, spring push-rod, the mounting structure scheme drawing of spring spool of separation device device of satellite received in a kind of novel control of Fig. 7;
The cylindrical spring structural representation of separation device device of satellite is received in a kind of novel control of Fig. 8;
The spring push-rod structural representation of separation device device of satellite is received in a kind of novel control of Fig. 9;
The spring spool structural representation of separation device device of satellite is received in a kind of novel control 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
The present invention is further illustrated below in conjunction with drawings and Examples.
As shown in Figure 1, the separation device device of satellite is received in a kind of novel control, comprises base plate 1, four stay bearing plates 2, four gussets 3, four cylindrical springs 4, four spring push-rods 5, four spring spools 6; Every gusset is fixed between two stay bearing plates 2, and every stay bearing plate 2 is fixed two gussets 3, and the bottom of gusset 3 is connected by screw and is fixed on the base plate 1; Spring push-rod 5 is embedded in the cylindrical spring 4, and cylindrical spring 4 is contained in the spring spool 6, and spring spool 6 is connected by screw and is fixed on the base plate 1; Spring push-rod 5 withstands on to be received in the corresponding circular hole of satellite celestial body square framework.
As shown in Figure 7, described spring push-rod 5 under free state by cylindrical spring 4 jack-up, not constraint between spring push-rod 5 and the cylindrical spring 4, the round platform of spring push-rod 5 bottoms drops in the cylindrical spring 4, the gap that 1mm is arranged between the two, this has just guaranteed when mounted just pressurized and the effect that can not be reversed of cylindrical spring 4, thereby has avoided receiving the rolling deviation of satellite.
As shown in Figure 5, there is bearing pin the upper end of described stay bearing plate 2, and bearing pin on the stay bearing plate 2 embeds to receive and carries transverse load in the corresponding hole on the satellite celestial body square framework;
As shown in Figure 4, described base plate 1 utilizes two titanium bars and nut will receive the satellite celestial body and fix from receiving the diagonal position of satellite celestial body.
As shown in Figure 1, described device separates the method for satellite received, receiving satellite fixedly the time, base plate 1 links to each other with the rocket platform, receive four holes of satellite celestial body square framework bottom surface corresponding to spring push-rod 5, the boss on each stay bearing plate 2 is corresponding to receiving the aperture in four corners of satellite celestial body square framework bottom surface; When receiving satellite celestial body square frame installation when receiving the separation device device of satellite to described control, apply external force, by spring push-rod 5 cylindrical spring 4 is compressed, thereby utilize two titanium bars and nut will receive the satellite celestial body and be fixed on the base plate 1 from receiving the diagonal position of satellite celestial body, when satellite arrives planned orbit, receive separation signal, the titanium bar cut off that the satellite celestial body of receiving realizes that under the combined action of four cylindrical springs 4 satellite and the rocket separate.
Claims (5)
1. the separation device device of satellite is received in a novel control, and it is characterized in that: it comprises base plate (1), four stay bearing plates (2), four gussets (3), four cylindrical springs (4), four spring push-rods (5), four spring spools (6); Every gusset (3) is fixed between two stay bearing plates (2), and every stay bearing plate (2) is fixed two gussets (3), and the bottom of gusset (3) is connected by screw and is fixed on the base plate (1); Spring push-rod (5) is embedded in the cylindrical spring (4), and cylindrical spring (4) is contained in the spring spool (6), and spring spool (6) is connected by screw and is fixed on the base plate (1); Spring push-rod (5) withstands on to be received in the corresponding circular hole of satellite celestial body square framework.
2. the separation device device of satellite is received in a kind of novel control as claimed in claim 1, it is characterized in that: described spring push-rod (5) under free state by cylindrical spring (4) jack-up, not constraint between spring push-rod (5) and the cylindrical spring (4), the round platform of spring push-rod (5) bottom drops in the cylindrical spring (4), and the gap of 1mm is arranged between the two.
3. the separation device device of satellite is received in a kind of novel control as claimed in claim 1, it is characterized in that: there is bearing pin the upper end of described stay bearing plate (2), and bearing pin on the stay bearing plate (2) embeds to receive and carries transverse load in the corresponding hole on the satellite celestial body square framework.
4. the separation device device of satellite is received in a kind of novel control as claimed in claim 1, it is characterized in that: described base plate (1) utilizes two titanium bars and nut will receive the satellite celestial body and fix from receiving the diagonal position of satellite celestial body.
5. a device as claimed in claim 1 separates the method for satellite received, it is characterized in that: receiving satellite fixedly the time, base plate (1) links to each other with the rocket platform, receive four holes of satellite celestial body square framework bottom surface corresponding to spring push-rod (5), the boss on each stay bearing plate (2) is corresponding to receiving the aperture in four corners of satellite celestial body square framework bottom surface; When receiving satellite celestial body square frame installation when receiving the separation device device of satellite to described control, apply external force, by spring push-rod (5) cylindrical spring (4) is compressed, thereby utilize two titanium bars and nut will receive the satellite celestial body and be fixed on the base plate (1) from receiving the diagonal position of satellite celestial body, when satellite arrives planned orbit, receive separation signal, the titanium bar cut off that the satellite celestial body of receiving realizes that under the combined action of four cylindrical springs (4) satellite and the rocket separate.
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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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| CN103010489B CN103010489B (en) | 2014-12-31 |
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| CN104058107A (en) * | 2014-05-23 | 2014-09-24 | 北京空间飞行器总体设计部 | Connecting device capable of reducing impact during satellite-rocket separation |
| CN104527997A (en) * | 2015-01-20 | 2015-04-22 | 浙江大学 | Synchronizing device used for being connected with and unlocking satellite |
| CN104724303A (en) * | 2015-01-23 | 2015-06-24 | 北京卫星环境工程研究所 | Cuboid satellite orbit deployer |
| CN104816841A (en) * | 2015-05-05 | 2015-08-05 | 中国人民解放军国防科学技术大学 | Satellite unlocking separation device |
| CN104816842A (en) * | 2015-05-18 | 2015-08-05 | 湖北航天技术研究院总体设计所 | Micro/nano-satellite multi-star adaption portion deploy device and application |
| CN104859870A (en) * | 2014-10-09 | 2015-08-26 | 航天东方红卫星有限公司 | Integrally-designed satellite-rocket separation mechanism |
| CN105109710A (en) * | 2015-09-11 | 2015-12-02 | 浙江大学 | Synchronous separation device for being connected with or separating from satellite |
| CN105151330A (en) * | 2015-09-18 | 2015-12-16 | 浙江大学 | Pico/Nano satellite and rocket fixing and separating device |
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| CN105346736A (en) * | 2015-11-12 | 2016-02-24 | 哈尔滨工业大学 | Modular low-impact linkage type microsatellite separating unit |
| CN105366078A (en) * | 2015-11-27 | 2016-03-02 | 中国空间技术研究院 | Holding type capture device applicable to satellite docking ring docking |
| CN106043744A (en) * | 2016-07-11 | 2016-10-26 | 上海宇航系统工程研究所 | Point type satellite and rocket connection unlocking mechanism |
| CN106052490A (en) * | 2016-07-11 | 2016-10-26 | 上海宇航系统工程研究所 | Satellite-rocket point type connection and separation module and device |
| CN106184826A (en) * | 2016-07-11 | 2016-12-07 | 上海宇航系统工程研究所 | Satellite and the rocket spring separator |
| CN106542127A (en) * | 2016-12-27 | 2017-03-29 | 哈尔滨工业大学 | One kind receive skin satellite orbit deployment device |
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| CN107512407A (en) * | 2017-08-23 | 2017-12-26 | 上海微小卫星工程中心 | Connection separation mechanism for satellite |
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| CN108528766A (en) * | 2018-06-04 | 2018-09-14 | 上海微小卫星工程中心 | Horizontal satellite-rocket separation mechanism |
| CN108583940A (en) * | 2018-06-04 | 2018-09-28 | 上海微小卫星工程中心 | A kind of four-point satellite and the rocket separating mechanism |
| CN109110162A (en) * | 2018-06-14 | 2019-01-01 | 上海卫星工程研究所 | A kind of in-orbit tunable arrangement of separating rate and preparation method thereof |
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| CN104058107A (en) * | 2014-05-23 | 2014-09-24 | 北京空间飞行器总体设计部 | Connecting device capable of reducing impact during satellite-rocket separation |
| CN104859870A (en) * | 2014-10-09 | 2015-08-26 | 航天东方红卫星有限公司 | Integrally-designed satellite-rocket separation mechanism |
| CN104527997A (en) * | 2015-01-20 | 2015-04-22 | 浙江大学 | Synchronizing device used for being connected with and unlocking satellite |
| CN104724303A (en) * | 2015-01-23 | 2015-06-24 | 北京卫星环境工程研究所 | Cuboid satellite orbit deployer |
| CN104816841A (en) * | 2015-05-05 | 2015-08-05 | 中国人民解放军国防科学技术大学 | Satellite unlocking separation device |
| CN104816842A (en) * | 2015-05-18 | 2015-08-05 | 湖北航天技术研究院总体设计所 | Micro/nano-satellite multi-star adaption portion deploy device and application |
| CN108349596B (en) * | 2015-06-22 | 2021-07-16 | 世界卫星有限公司 | Payload distribution system |
| CN108349596A (en) * | 2015-06-22 | 2018-07-31 | 世界卫星有限公司 | Payload distribution system |
| CN105109710A (en) * | 2015-09-11 | 2015-12-02 | 浙江大学 | Synchronous separation device for being connected with or separating from satellite |
| CN105151330B (en) * | 2015-09-18 | 2017-11-07 | 浙江大学 | A kind of skin Nano satellite satellite and the rocket are fixed and separator |
| CN105151330A (en) * | 2015-09-18 | 2015-12-16 | 浙江大学 | Pico/Nano satellite and rocket fixing and separating device |
| CN105292523A (en) * | 2015-10-27 | 2016-02-03 | 浙江大学 | Separating device and satellite and rocket separating device with buffering structure |
| CN105346736A (en) * | 2015-11-12 | 2016-02-24 | 哈尔滨工业大学 | Modular low-impact linkage type microsatellite separating unit |
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| CN106043744A (en) * | 2016-07-11 | 2016-10-26 | 上海宇航系统工程研究所 | Point type satellite and rocket connection unlocking mechanism |
| CN106052490A (en) * | 2016-07-11 | 2016-10-26 | 上海宇航系统工程研究所 | Satellite-rocket point type connection and separation module and device |
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| CN107512407A (en) * | 2017-08-23 | 2017-12-26 | 上海微小卫星工程中心 | Connection separation mechanism for satellite |
| CN108528766B (en) * | 2018-06-04 | 2021-03-16 | 上海微小卫星工程中心 | Horizontal satellite-rocket separation mechanism |
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| CN108583940A (en) * | 2018-06-04 | 2018-09-28 | 上海微小卫星工程中心 | A kind of four-point satellite and the rocket separating mechanism |
| CN109110162B (en) * | 2018-06-14 | 2020-11-24 | 上海卫星工程研究所 | Separation speed on-orbit adjustable device and manufacturing method thereof |
| CN109110162A (en) * | 2018-06-14 | 2019-01-01 | 上海卫星工程研究所 | A kind of in-orbit tunable arrangement of separating rate and preparation method thereof |
| CN109335029B (en) * | 2018-09-30 | 2020-08-07 | 哈尔滨工业大学 | Air-floating type aircraft on-orbit separation ground simulation and test device |
| CN109335029A (en) * | 2018-09-30 | 2019-02-15 | 哈尔滨工业大学 | A kind of in-orbit separation ground simulation of air-flotation type aircraft and test device |
| CN110304282B (en) * | 2019-06-27 | 2020-09-08 | 湖北航天技术研究院总体设计所 | Satellite and rocket separation system and separation method thereof |
| CN110304282A (en) * | 2019-06-27 | 2019-10-08 | 湖北航天技术研究院总体设计所 | A kind of satellite and the rocket separation system and its separation method |
| CN111891390A (en) * | 2020-08-11 | 2020-11-06 | 中国科学院微小卫星创新研究院 | Satellite interface, connection method thereof and satellite system |
| 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 |
| CN112697184A (en) * | 2020-11-30 | 2021-04-23 | 上海航天控制技术研究所 | Base of separation satellite of mars detector |
| CN112777001A (en) * | 2021-01-25 | 2021-05-11 | 中国人民解放军国防科技大学 | Micro-nano satellite accompanied with orbit entry |
| CN112793801A (en) * | 2021-04-02 | 2021-05-14 | 成都云鼎智控科技有限公司 | Unmanned aerial vehicle boosting structure and unmanned aerial vehicle launcher |
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| CN115626301A (en) * | 2022-09-05 | 2023-01-20 | 深圳航天东方红卫星有限公司 | Load structure integrated open satellite configuration |
Also Published As
| Publication number | Publication date |
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| CN103010489B (en) | 2014-12-31 |
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