CN104724303A - Cuboid satellite orbit deployer - Google Patents
Cuboid satellite orbit deployer Download PDFInfo
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- CN104724303A CN104724303A CN201510035545.0A CN201510035545A CN104724303A CN 104724303 A CN104724303 A CN 104724303A CN 201510035545 A CN201510035545 A CN 201510035545A CN 104724303 A CN104724303 A CN 104724303A
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- hatch door
- cube satellite
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Abstract
The invention discloses a cuboid satellite orbit deployer. The cuboid satellite orbit deployer comprises a top plate, a base plate, two opposite side plates, a back plate, a cabin door arranged opposite to the back plate, a main spring and the like; the deployer forms a totally-sealed cuboid cagelike structure, the inside of the deployer is used for loading a cuboid satellite, the main spring is arranged on the back plate, and a push plate is arranged in the cagelike structure of the deployer. A door frame is fixed to the top plate, the base plate and the side plates. The main spring is in a state of compression after loading of the cuboid satellite, the satellite abuts against the push plate at the moment, the cabin door opens when the orbit is deployed, the main spring and the push plate together drive the cuboid satellite to be popped, wherein a cabin door opening mechanism is controlled by electromagnetism, by the corporation of a permanent magnet and a direct-current electromagnetic coil, the opening of the cabin door is achieved under the action of a cabin door spring arranged at the bottom of the door frame.
Description
Technical field
The invention belongs to satellite spatial Detection Techniques field, specifically, relate to a kind of satellite orbit and dispose device, be mainly used in Space environment detection, satellite constellation deployment etc.
Background technology
Current micro-thermoelectric generator receives extensive attention, particularly cube satellite.Cube satellite refers to that oad is the satellite of the cubic shaped of 10cm x 10cm x 10cm.According to the specification of cube satellite, its weight should not be greater than 1kg.Therefore the general mode adopting lift-launch, namely carries same carrier rocket and launches with Large-scale satellite.This launch mode requires that cube satellite can adapt to multiple Launch Vehicle Platform, and to cube satellite, development side proposes very high requirement.Therefore develop a kind of cube satellite launch and dispose device, most important as the interface between cube satellite and carrier rocket.On the one hand this deployment device meets the various requirement of cube satellite, makes satellite development person no longer too much consider how adaptive launching opportunity and carrier rocket characteristic; This deployment device also can be the interface of carrier rocket supplier simplification and cube satellite on the other hand, and once can launch many cube satellites.
Not yet retrieve the Patents about cube satellite launch deployment device at present.The Patents belonging to same field with this patent has Chinese patent application CN201410027585.6 " a kind of novel Multi satellite separation solution lock release " etc.
Summary of the invention
The transmitting and the track that the present invention is directed to cube satellite are disposed, and propose a kind of cube satellite orbit deployment devices.Deployment devices once can load many cube satellites, can install and adapt to multiple carrier rocket.Its normalisation, structuring, enclosed spatial structure have the advantage that cost is low, efficiency is high, can stand severe space environment.
Cube satellite orbit deployment devices of the present invention, comprise top board, base plate, two relative side plates, backboard, the hatch door that is oppositely arranged with backboard, main spring, push pedal, doorframe, hatch door opening mechanism, hatch door spring, top board, base plate, biside plate, backboard and hatch door have formed fully enclosed cube cagelike structure, inner for loading cube satellite, backboard arranges main spring.Cagelike structure inside arranges push pedal, and doorframe is fixed on top board, base plate and side plate.Main spring is in compressive state after cube satellite loads, now satellite is resisted against in push pedal, when disposing in-orbit, hatch door is opened, spring promotes cube satellite and ejects together with push pedal, along guide rail movement when top board, base plate, biside plate being respectively arranged with guide rail to make cube satellite eject from deployment device inside, wherein, hatch door opening mechanism is electromagnetic control, comprises d-c solenoid and its anchor fitting.Hatch door arranges permanent magnet, and under the effect of permanent magnet, hatch door is normally closed, after receiving carrier rocket connection d-c solenoid when disengaged, produces the application force that electromagnetic force offsets permanent magnet, opens under the effect of the hatch door spring that hatch door is arranged bottom doorframe.
Wherein, hatch door opening mechanism comprises d-c solenoid and its anchor fitting.Coil is fixed on top board by anchor fitting.The position of d-c solenoid is corresponding with the position of hatch door permanent magnet.
Further, two relative side plates are demountable panel.
Further, demountable panel is arranged with hole, to carry out maintenance maintenance to cube satellite.
Wherein, hatch door is provided with reinforced rib, to improve its rigidity.
Further, guide rail is by teflon (teflon) anodic oxydation treatment.
Wherein, base plate is provided with baffle plate to avoid hatch door open angle excessive.
Compared with prior art, cube satellite orbit of the present invention is disposed device and is adopted fully enclosed cagelike structure, and inner loading cube satellite, arranging spring by disposing in device, providing the initial driving force that cube satellite is disposed.Hatch door opening mechanism adopts non-firer's tripper, avoids the larger impact of generation and pollution.
Accompanying drawing explanation
Fig. 1 is the structural representation of cube satellite orbit deployment devices of the present invention.
In figure: 1 is top board; 2 is base plate; 3 is side plate; 4 is backboard; 5 is push pedal; 6 is main spring; 7 is doorframe; 8 is hatch door; 9 is d-c solenoid bearing; 10 is d-c solenoid; 11 is permanent magnet; 12 is hatch door spring and pin; 13 is dash plate.
Detailed description of the invention
What below introduce is detailed description of the invention as content of the present invention, further illustrates content of the present invention below by detailed description of the invention.Certainly, describe the content that following detailed description is only example different aspect of the present invention, and should not be construed as the restriction scope of the invention.
The structural representation of cube satellite orbit deployment devices of the present invention is shown see Fig. 1, Fig. 1.This deployment device comprises top board 1, base plate 2, two relative side plates 3, backboard 4, hatch door 8, main spring 6, push pedal 5, doorframe 7, the hatch door opening mechanism 9 be made up of d-c solenoid bearing 9, d-c solenoid 10, permanent magnet 11, hatch door spring and pin 12, dash plate 13, wherein, top board 1, base plate 2, biside plate 3, backboard 4, doorframe 7 and hatch door 8 have formed fully enclosed cube cagelike structure, inner for loading cube satellite, backboard 4 is fixed one end of main spring 6, the other end of main spring 6 is fixed in the push pedal 5 of cagelike structure inside.Doorframe 7 is fixed on top board 1, base plate 2 and side plate 3,4.Main spring 6 is in compressive state after cube satellite loads, and satellite is resisted against in push pedal 5, and spring 6 and push pedal 5 promote cube satellite together and eject when being separated.Along guide rail movement when top board 1, base plate 2, biside plate 3 being respectively arranged with guide rail (guide rail is preferably by teflon anodic oxydation treatment) to make cube satellite eject from deployment device inside, wherein, hatch door opening mechanism is electromagnetic control, hatch door 8 arranges permanent magnet, it top board 1 is d-c solenoid, under the effect of permanent magnet, hatch door is normally closed, after d-c solenoid connected by carrier rocket when disengaged, produce the application force that electromagnetic force offsets permanent magnet, open under the hatch door spring that hatch door 8 is arranged bottom doorframe and the effect of pin 12.
In a detailed description of the invention, hatch door opening mechanism comprises d-c solenoid and its anchor fitting.Coil is fixed on top board by anchor fitting.The position of d-c solenoid is corresponding with the position of hatch door permanent magnet.In a preferred embodiment, two relative side plates are demountable panel, and demountable panel is arranged with hole, to carry out maintenance maintenance to cube satellite.
In yet, hatch door is provided with reinforced rib, to improve its rigidity; Base plate is provided with dash plate 13 to avoid hatch door open angle excessive.
Of the present invention cube of satellite orbit is disposed device and has been formed fully enclosed cagelike structure, it has enough Rigidity and strengths, inner loading cube satellite, can ensure the safety of cube satellite, also avoid the electromagnetic interference between cube satellite and carrier rocket simultaneously.Side plate can arrange demountable panel if desired, after loading, carries out maintenance maintenance by the hole under demountable panel to cube satellite for cube satellite.
Due to top board 1, base plate 2, side plate 3 being provided with guide rail, when cube satellite ejects from deployment device inside, along guide rail movement, avoiding cube satellite and produce rotation, ensure that the stable of injection attitude.For reducing the friction between guide rail and cube satellite, guide rail adopts teflon anodic oxydation treatment.
The use procedure of the track deployment device of cube satellite of the present invention is as follows:
1) cube satellite loads deployment device;
2) dispose device and be installed on carrier rocket;
3), after arriving planned orbit, carrier rocket sends " separation " instruction to deployment device;
4) dispose the action of device hatch door opening mechanism, hatch door is opened;
5) cube satellite ejects under the effect disposing device internal main spring.If there are many cube satellites, by release spring secondary separation between cube satellite.
Adopt this deployment device, cube satellite can be disposed complete in 0.5s, and the rate of onset of cube satellite is less than 2m/s.
Although be described in detail the specific embodiment of the present invention above and illustrate, but what should indicate is, we can make various changes and modifications above-mentioned embodiment, but these do not depart from spirit of the present invention and the scope described in appended claim.
Claims (7)
1. cube satellite orbit deployment devices, comprise top board, base plate, two relative side plates, backboard, the hatch door that is oppositely arranged with backboard, main spring, push pedal, doorframe, hatch door opening mechanism, hatch door spring, top board, base plate, biside plate, backboard and hatch door have formed fully enclosed cube cagelike structure, inner for loading cube satellite, backboard arranges main spring.Cagelike structure inside arranges push pedal, and doorframe is fixed on top board, base plate and side plate.Main spring is in compressive state after cube satellite loads, now satellite is resisted against in push pedal, when disposing in-orbit, hatch door is opened, spring promotes cube satellite and ejects together with push pedal, along guide rail movement when top board, base plate, biside plate being respectively arranged with guide rail to make cube satellite eject from deployment device inside, wherein, hatch door opening mechanism is electromagnetic control, comprises d-c solenoid and its anchor fitting.Hatch door arranges permanent magnet, and under the effect of permanent magnet, hatch door is normally closed, after receiving carrier rocket connection d-c solenoid when disengaged, produces the application force that electromagnetic force offsets permanent magnet, opens under the effect of the hatch door spring that hatch door is arranged bottom doorframe.
2. cube satellite orbit deployment devices as claimed in claim 1, wherein, hatch door opening mechanism comprises d-c solenoid and its anchor fitting.
3. cube satellite orbit deployment devices as claimed in claim 1, wherein, two relative side plates are demountable panel.
4. cube satellite orbit deployment devices as claimed in claim 1, wherein, demountable panel is arranged with hole, to carry out maintenance maintenance to cube satellite.
5. cube satellite orbit deployment devices as claimed in claim 1, wherein, hatch door is provided with reinforced rib, to improve its rigidity.
6. cube satellite orbit deployment devices as claimed in claim 1, wherein, guide rail is by teflon anodic oxydation treatment.
7. cube satellite orbit deployment devices as claimed in claim 1, wherein, base plate is provided with dash plate to avoid hatch door open angle excessive.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510035545.0A CN104724303A (en) | 2015-01-23 | 2015-01-23 | Cuboid satellite orbit deployer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510035545.0A CN104724303A (en) | 2015-01-23 | 2015-01-23 | Cuboid satellite orbit deployer |
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| Publication Number | Publication Date |
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| CN104724303A true CN104724303A (en) | 2015-06-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510035545.0A Pending CN104724303A (en) | 2015-01-23 | 2015-01-23 | Cuboid satellite orbit deployer |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292525A (en) * | 2015-12-09 | 2016-02-03 | 中国人民解放军国防科学技术大学 | Non-initiating-explosive dotted connecting and separating device |
| CN105442528A (en) * | 2015-12-15 | 2016-03-30 | 浙江工业大学 | Cement grouting sheet pile with sealing ring |
| CN106516172A (en) * | 2016-11-23 | 2017-03-22 | 上海卫星工程研究所 | Device for multi-satellite on-orbit release of micro-nano satellite |
| CN106542127A (en) * | 2016-12-27 | 2017-03-29 | 哈尔滨工业大学 | One kind receive skin satellite orbit deployment device |
| CN106628273A (en) * | 2016-12-14 | 2017-05-10 | 中国科学院国家空间科学中心 | Clamping and releasing device for on-orbit mutual separation of master spacecraft and slave spacecraft |
| CN108528766A (en) * | 2018-06-04 | 2018-09-14 | 上海微小卫星工程中心 | Horizontal satellite-rocket separation mechanism |
| CN109533400A (en) * | 2019-01-10 | 2019-03-29 | 深圳航天东方红海特卫星有限公司 | A kind of cube of star compresses release device |
| CN110155376A (en) * | 2019-05-23 | 2019-08-23 | 南京理工大学 | A kind of cube star unlocking separation mechanism and its separation method |
| CN110626525A (en) * | 2019-06-25 | 2019-12-31 | 北京机械设备研究所 | Releasing device and releasing method suitable for space operation equipment |
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| CN2782866Y (en) * | 2005-01-25 | 2006-05-24 | 秦子义 | Magnetic lock |
| EP2066566B1 (en) * | 2006-09-18 | 2012-03-21 | Astro- und Feinwerktechnik Adlershof GmbH | Transportation and ejection unit for picosatellites |
| CN103010489A (en) * | 2012-12-26 | 2013-04-03 | 浙江大学 | Novel separation mechanism device for controlling nano-satellite and separation method of separation mechanism device |
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2015
- 2015-01-23 CN CN201510035545.0A patent/CN104724303A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2782866Y (en) * | 2005-01-25 | 2006-05-24 | 秦子义 | Magnetic lock |
| EP2066566B1 (en) * | 2006-09-18 | 2012-03-21 | Astro- und Feinwerktechnik Adlershof GmbH | Transportation and ejection unit for picosatellites |
| CN103010489A (en) * | 2012-12-26 | 2013-04-03 | 浙江大学 | Novel separation mechanism device for controlling nano-satellite and separation method of separation mechanism device |
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292525A (en) * | 2015-12-09 | 2016-02-03 | 中国人民解放军国防科学技术大学 | Non-initiating-explosive dotted connecting and separating device |
| CN105292525B (en) * | 2015-12-09 | 2017-09-12 | 中国人民解放军国防科学技术大学 | Non- firer's point type connects separator |
| CN105442528A (en) * | 2015-12-15 | 2016-03-30 | 浙江工业大学 | Cement grouting sheet pile with sealing ring |
| CN106516172A (en) * | 2016-11-23 | 2017-03-22 | 上海卫星工程研究所 | Device for multi-satellite on-orbit release of micro-nano satellite |
| CN106516172B (en) * | 2016-11-23 | 2019-06-07 | 上海卫星工程研究所 | A kind of device for the more star On-orbit releases of micro-nano satellite |
| CN106628273B (en) * | 2016-12-14 | 2018-11-13 | 中国科学院国家空间科学中心 | It is a kind of to be used for the in-orbit clamping and releasing device being separated from each other of principal and subordinate's spacecraft |
| CN106628273A (en) * | 2016-12-14 | 2017-05-10 | 中国科学院国家空间科学中心 | Clamping and releasing device for on-orbit mutual separation of master spacecraft and slave spacecraft |
| CN106542127A (en) * | 2016-12-27 | 2017-03-29 | 哈尔滨工业大学 | One kind receive skin satellite orbit deployment device |
| CN108528766A (en) * | 2018-06-04 | 2018-09-14 | 上海微小卫星工程中心 | Horizontal satellite-rocket separation mechanism |
| CN109533400A (en) * | 2019-01-10 | 2019-03-29 | 深圳航天东方红海特卫星有限公司 | A kind of cube of star compresses release device |
| CN110155376A (en) * | 2019-05-23 | 2019-08-23 | 南京理工大学 | A kind of cube star unlocking separation mechanism and its separation method |
| CN110155376B (en) * | 2019-05-23 | 2020-11-13 | 南京理工大学 | Cube star unlocking and separating mechanism and separating method thereof |
| CN110626525A (en) * | 2019-06-25 | 2019-12-31 | 北京机械设备研究所 | Releasing device and releasing method suitable for space operation equipment |
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Application publication date: 20150624 |
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| RJ01 | Rejection of invention patent application after publication |