CN108116697B - A spherical satellite separation and unlocking device - Google Patents
A spherical satellite separation and unlocking device Download PDFInfo
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- CN108116697B CN108116697B CN201711296549.XA CN201711296549A CN108116697B CN 108116697 B CN108116697 B CN 108116697B CN 201711296549 A CN201711296549 A CN 201711296549A CN 108116697 B CN108116697 B CN 108116697B
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- 238000000926 separation method Methods 0.000 title claims abstract description 69
- 239000002360 explosive Substances 0.000 claims description 22
- 230000006835 compression Effects 0.000 claims description 12
- 238000007906 compression Methods 0.000 claims description 12
- 238000004880 explosion Methods 0.000 claims description 12
- 230000008878 coupling Effects 0.000 claims description 4
- 238000010168 coupling process Methods 0.000 claims description 4
- 238000005859 coupling reaction Methods 0.000 claims description 4
- 238000009434 installation Methods 0.000 description 6
- 230000007246 mechanism Effects 0.000 description 6
- 230000003313 weakening effect Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 239000003721 gunpowder Substances 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000003999 initiator Substances 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000000977 initiatory effect Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000002452 interceptive effect Effects 0.000 description 1
- 238000001612 separation test Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
- B64G1/645—Separators
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- Aviation & Aerospace Engineering (AREA)
- Geophysics And Detection Of Objects (AREA)
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Abstract
本发明公开了一种球形卫星分离解锁装置，包括分离底座、锁紧分离模块以及顶推模块，所述锁紧分离模块包括至少两个固定在所述分离底座上且沿卫星周向分布的锁紧分离单元，每个锁紧分离单元包括：锁紧杆底座，固定在所述分离底座上；摆杆，通过转轴安装在锁紧杆底座上，内侧带有插入所述卫星的锁孔的锁销以将卫星压紧在所述顶推模块上；锁定件，将所述摆杆定位在所述锁销插入锁孔位置，所述锁定件带有解锁状态，在所述解锁状态下所述顶推模块推动所述卫星分离，分离过程中所述锁孔脱出所述锁销并使摆杆向外转动；本发明整体结构更简单，运行可靠，可以有效在火箭上固定及分离球形卫星。
The invention discloses a spherical satellite separation and unlocking device, comprising a separation base, a locking separation module and a push module, wherein the locking separation module comprises at least two locks fixed on the separation base and distributed along the satellite circumference Tightening and separating units, each locking and separating unit includes: a locking rod base, which is fixed on the separation base; a pendulum rod, which is installed on the locking rod base through a rotating shaft, and has a lock inserted into the locking hole of the satellite inside. a pin to press the satellite on the push module; a locking piece to position the swing rod at the position where the lock pin is inserted into the lock hole, the locking piece has an unlocked state, and in the unlocked state the The push module pushes the satellite to separate, and the lock hole escapes from the lock pin during the separation process and makes the swing rod rotate outward; the invention has simpler overall structure and reliable operation, and can effectively fix and separate spherical satellites on the rocket.
Description
Technical Field
The invention relates to a separation unlocking device for an aviation aircraft, in particular to a separation unlocking device for a spherical satellite.
Background
In recent years, the hot tide of satellite development has rapidly risen worldwide. The unlocking separation technology, which is one of the key technologies of the satellite, is a core technology related to successful launching and normal orbit entering of the satellite, and has an important influence on the overall performance of the satellite. Therefore, the unlocking and separating device with small separating impact and high reliability has important significance.
Satellite unlocking mechanisms in the prior art are mostly directed at square satellites, for example, patent document with publication number CN105151330A discloses a pico-satellite and satellite arrow fixing and separating device, which includes a bottom plate, a satellite support seat, a pull rod cutting mechanism and a satellite ejection mechanism are fixed on the bottom plate, the satellite support seat is provided with at least one pair, any one pair of satellite support seats is arranged in pairs, the pull rod is provided with at least one pair, each pair of pull rods is respectively installed in any one pair of satellite support seats, each pull rod extends out of a satellite support surface corresponding to the satellite support seat to be connected with a satellite and tightly presses the satellite on the satellite support surface; the pico-nano satellite and satellite fixing and separating device sets the tension and pressure borne by the bottom plate on the same straight line when the satellite and the bottom plate are connected, so that the interaction force between the bottom plate and the satellite is reasonably distributed, the whole structure is simple and stable, the mounting is convenient, and the manufacturing cost is low.
For another example, patent document CN104527997A discloses a synchronization device for connecting and unlocking a satellite, which includes a pair of pin grooves fixedly installed on both sides of the satellite, and a pair of movable lock pins installed on a satellite separation member through a synchronization driving mechanism and respectively engaged with the pair of pin grooves, the synchronization driving mechanism including: a base fixed to the satellite separation member; one end of the supporting rod is hinged on the base; one end of the straight push rod is hinged with the free end of the support rod; the middle part of the horizontal push rod is hinged with the free end of the straight push rod; and the linkage mechanisms are symmetrically arranged at two sides of the straight push rod, are correspondingly connected with two ends of the movable lock pins and the transverse push rod, and are used for simultaneously transmitting the horizontal push force of the transverse push rod to the movable lock pins to drive the movable lock pins to be separated from the corresponding pin grooves. The separation satellite is connected through pure mechanical structure, simple to operate, job stabilization is particularly suitable for replacing the initiating explosive device on the ground to carry out the satellite separation test to greatly reduced test cost.
However, the unlocking and separating device is not suitable for the spherical satellite because the surface of the spherical satellite is arc-shaped and is not easy to fix, so that a separating and unlocking device suitable for the spherical satellite needs to be researched for solving the problems of small volume, heavy weight and difficulty in locking and separating of the spherical satellite.
Disclosure of Invention
The invention discloses a spherical satellite separation unlocking device which is simpler in overall structure and reliable in operation and can effectively fix and separate a spherical satellite on a rocket.
The utility model provides a spherical satellite separation unlocking device, includes separation base, locking separation module and top pushes away the module, locking separation module includes that at least two are fixed last and along the locking separation unit that satellite circumference distributes of separation base, every locking separation unit includes:
the locking rod base is fixed on the separating base;
the swing rod is arranged on the locking rod base through a rotating shaft, and the inner side of the swing rod is provided with a lock pin inserted into a lock hole of the satellite so as to tightly press the satellite on the pushing module;
the locking piece is used for positioning the swing rod at the position where the lock pin is inserted into the lock hole, the locking piece is in an unlocking state, the pushing module pushes the satellite to be separated in the unlocking state, and the lock hole is separated from the lock pin in the separation process and enables the swing rod to rotate outwards.
The side of the swing rod close to the satellite is the inner side, the side far away from the satellite is the outer side, and the swing rod rotates outwards means that the inner side rotates upwards, and the outer side rotates downwards.
The invention realizes the compression and the unlocking of the spherical satellite through the oscillating bar and the locking piece with simple structures, has reliable operation and can effectively fix and separate the spherical satellite on the rocket.
For convenient manufacture and installation, effective positioning and unlocking is achieved, and preferably, the locking member includes:
the explosive bolt penetrates through a bolt hole formed in the outer side of the swing rod;
the locking nut is connected with one end of the explosive bolt in a matched mode and is arranged on one side, far away from the locking rod base, of the bolt hole;
one end of the locking rod penetrates out of the back face of the locking rod base and is connected with the other end of the explosion bolt through a connecting nut, and the other end of the locking rod is provided with a step which is abutted against the back face of the locking rod base.
After the initiator at the input end of the explosive bolt works, the explosive in the explosive bolt is detonated, the explosive in the explosive bolt explodes to generate high-pressure gas and shock waves to act on the bolt body, so that the stress at the weakening groove exceeds the strength limit of the material, and the bolt body is broken from the weakening groove, so that the two connected objects are unlocked.
Above-mentioned structure can conveniently carry out pendulum rod ground locking, and coupling nut connects check lock lever and explosion bolt, the other end of check lock lever with the back of check lock lever base supports and leans on, and the location of the complete pendulum rod position of rethread check lock nut adjustment. When unlocking is carried out, the explosive bolt is disconnected, the locking rod falls down due to gravity, and the swing rod rotates outwards. The connecting nut can enable the locking rod to be reserved on the locking rod base when the explosive bolt is cut off.
In order to adjust the locking degree conveniently, preferably, the back of the locking rod base is provided with a locking sleeve sleeved on the locking rod, a compression spring sleeved on the locking rod is arranged in the locking sleeve, and the compression spring abuts against the inner step of the locking sleeve and the step of the locking rod. The compression spring is used for pulling the locking rod to be separated from the explosive bolt when the explosive bolt is cut off, the locking rod can be pushed to be away from the swing rod quickly after unlocking, normal movement of the swing rod is avoided being influenced, and unlocking can be normally completed when the satellite is not horizontally arranged.
In order to mount the explosion bolt in place, it is preferable that the explosion bolt is fitted with a safety nut disposed between the coupling nut and the bolt hole.
When the satellite is unlocked, the swing rod is pushed to rotate outwards, in order to enable the swing rod to move without affecting the satellite, preferably, opposite surfaces perpendicular to the rotating shaft are arranged between the base of the locking rod and the swing rod, one of the opposite surfaces is provided with a mounting groove and a limiting bolt, an elastic piece is arranged between the mounting groove and the tail end of the limiting bolt, the top end of the limiting bolt is abutted against the other opposite surface, and a bolt hole matched with the limiting bolt is arranged on the other opposite surface so as to position the swing rod which rotates outwards. The limit bolt positions the swing rod to prevent the swing rod from interfering with the separation of the satellites.
In order to achieve stable installation and separation of the spherical satellite, preferably, the jacking module comprises:
the sleeve is fixed on the separating base;
the inner sleeve push rod is arranged in the sleeve, and the top of the inner sleeve push rod supports the satellite;
and the separation spring is arranged between the sleeve and the inner sleeve push rod and is compressed by the inner sleeve push rod. The inner sleeve push rod is cylindrical similar to the sleeve in shape, and a circular opening at the top can be attached to and supported by the spherical satellite.
In order to prevent the pushing module from separating from the separation base, preferably, a limiting rod is further arranged between the inner sleeve push rod and the sleeve. The limiting rod is used for limiting the stroke of the push rod of the inner sleeve and keeping the push rod on the separation base after the satellite is separated. One end of the limiting rod is fixedly connected with the push rod, and the other end of the limiting rod is provided with a nut.
In order to facilitate installation and manufacture and improve the stability of the supporting satellite, preferably, the top of the inner sleeve push rod is an annular opening, the annular opening is provided with an everted flanging, and the flanging is abutted to the separation spring.
In order to ensure that the bolt can be smoothly released from the lock hole, preferably, the lock pin and the lock hole are in the shape of circular arcs.
When the invention is installed, firstly, the sleeve is installed on the separation base, the separation spring and the push rod of the inner sleeve are placed in the sleeve, the limiting rod is pulled to a designated position, the separation spring is in a compressed state, the spherical satellite is placed on the top of the push rod to be contacted, the locking rod base is fixed on the base, then the limiting spring and the limiting bolt are installed on the swing rod, the swing rod is fixed on the locking rod base through the rotating shaft, when the installation is carried out, the small push rod is used for pushing the small hole on the locking fixing base to push the locking rod, so that the swing rod reaches the designated position, at the moment, the lock pin on the swing rod is contacted with the lock hole on the satellite, then the explosion bolt is fixed on the swing rod through the safety nut and the lock nut, the locking sleeve is installed on the locking rod base, the compression spring is placed in the locking sleeve, the locking rod is connected, the satellite is in the locking state, and during the separation, the explosion bolt cuts off the check lock lever, and the check lock lever is downstream under compression spring's effect, and the pendulum rod begins the swing under the effect of separation spring, and when swinging to a certain position, the pendulum rod is locked by spacing bolt, and the satellite separation.
Preferably, the locking rod base is arranged to be slidable and positionable along the radial direction of the spherical satellite, thereby enabling the device to be used with spherical satellites of different sizes.
The invention has the beneficial effects that:
the spherical satellite separating and unlocking device has a simpler overall structure and reliable operation, and can effectively fix and separate the spherical satellite on the rocket.
Drawings
Fig. 1 is a schematic structural diagram of a locking state of the spherical satellite separation unlocking device.
Fig. 2 is a schematic cross-sectional structural diagram of the locking state of the spherical satellite separation unlocking device.
Fig. 3 is a schematic structural diagram of an unlocking state of the spherical satellite separation unlocking device.
Fig. 4 is a schematic sectional structural view of the unlocking state of the spherical satellite separation unlocking device.
Fig. 5 is an enlarged schematic view of a pendulum part of the present invention.
Fig. 6 is a schematic structural view of the locking plug of the present invention.
Fig. 7 is a schematic structural view of the swing link of the present invention after being rotated outward.
Fig. 8 is a schematic cross-sectional view of an explosive bolt of the present invention.
Detailed Description
As shown in fig. 1 to 8, the separation unlocking device for a spherical satellite of the present embodiment includes a separation base 1, a locking separation module 2 and a pushing module 3.
The locking and separating module 2 includes four (one of which is hidden in fig. 1) locking and separating units fixed on the separating base and uniformly distributed along the circumference of the satellite, and each locking and separating unit includes:
a locking lever base 201 fixed on the separation base 1;
the swing rod 202 is installed on the locking rod base 1 through a rotating shaft 2011, and the inner side of the swing rod is provided with a lock pin 203 inserted into a lock hole 401 of the satellite 4 so as to press the satellite 4 on the pushing module 3;
and the locking piece is used for positioning the swing rod 202 at the position where the lock pin 203 is inserted into the lock hole, the locking piece is in an unlocking state, the pushing module pushes the satellite to be separated in the unlocking state, and the lock hole is separated from the lock pin in the separation process and enables the swing rod to rotate outwards. The lock pin 203 and the lock hole 401 are circular arc-shaped.
The locking piece includes: the explosion bolt 204 penetrates through a bolt hole 205 arranged on the outer side of the swing rod 202; a locking nut 206 which is connected with one end of the explosive bolt 204 in a matching way and is arranged on one side of the bolt hole 205 far away from the locking rod base 201; one end of the locking rod 207 penetrates out of the back of the locking rod base 201 and is connected with the other end of the explosive bolt 204 through a connecting nut 2014.
The back of the locking rod base 201 is provided with a locking sleeve 208 sleeved on the locking rod 207, a compression spring 209 sleeved on the locking rod is arranged in the locking sleeve 208, and the compression spring 209 abuts between the inner step of the locking sleeve 208 and the step of the locking rod 207.
A safety nut 2010 disposed between the coupling nut 2014 and the bolt hole 205 is fitted to the explosion bolt 204. Explosive bolt 204 is provided with gunpowder 2041 and weakening groove 2042 therein. After the initiator at the input end of the explosive bolt works, the gunpowder 2041 is detonated, the gunpowder 2041 explodes to generate high-pressure gas and shock waves to act on the explosive bolt 204, so that the stress at the weakening groove 2042 exceeds the strength limit of the material, and the explosive bolt 204 is broken from the weakening groove 2042, thereby realizing unlocking.
The opposite surface that has perpendicular pivot 2011 between check lock lever base 201 and the pendulum rod 202, the opposite surface of pendulum rod 202 is equipped with mounting groove and spacing bolt 2012, is equipped with reset spring 2013 between the tail end of mounting groove and spacing bolt 2012, and the top of spacing bolt 2012 and the opposite surface butt of check lock lever base 201 and be equipped with on the opposite surface of check lock lever base 201 with spacing bolt 2012 complex bolt hole 2015 with the pendulum rod 202 of location outwards rotation.
The pushing module 3 comprises: a sleeve 301 fixed to the separation base 1; an inner sleeve push rod 302 which is arranged in the sleeve 301 and the top of which supports the satellite 4; and a separation spring 303 installed between the sleeve 301 and the inner sleeve push rod 302.
A limiting rod 304 is further arranged between the inner sleeve push rod 302 and the sleeve 301. The top of the inner sleeve push rod 302 is an annular opening, the annular opening is provided with an everted flange 305, and the flange 305 is abutted with the separation spring 303.
When the installation of the embodiment is carried out, firstly, the sleeve 301 is installed on the separation base, the separation spring 303 and the inner sleeve push rod 302 are placed in the sleeve 301, the limit rod 304 is pulled to a designated position, the separation spring 303 is in a compressed state, the spherical satellite is placed on the top of the inner sleeve push rod 302 to contact, the locking rod base 201 is fixed on the separation base 1, then the limit spring 2013 and the limit bolt 2013 are installed on the swing rod 202, the swing rod 202 is fixed on the locking rod base 201 through the rotating shaft 2011, when the installation is carried out, the small push rod is used for pushing the small hole on the locking fixing base 201 to push the locking rod 207, so that the swing rod 202 reaches the designated position, the lock pin 203 on the swing rod 202 is in contact with the lock hole 401 on the satellite, then the explosive bolt 204 is fixed on the swing rod 202 through the safety nut 2010 and the lock nut 206, the locking sleeve 208, the locking rod 207 is connected with the explosion bolt 204 through the connecting nut 2014, the other end of the locking rod 207 is screwed by a nut (the nut is used as a step and is abutted against the compression spring 209), the satellite 4 is in a locking state, when the satellite is separated, the explosion bolt 204 cuts off the locking rod 207, the locking rod 207 moves downwards under the action of the compression spring 209, the swing rod 202 starts to swing backwards under the action of the separation spring 303, and when the swing rod swings to a certain position p equal to 16 degrees, the swing rod 202 is locked by the limiting bolt 2012, and the satellite is separated.
In conclusion, the spherical satellite separating and unlocking device for the rocket is simpler in overall structure and reliable in operation, and can effectively fix and separate the spherical satellite on the rocket.
Claims (8)
1. The utility model provides a spherical satellite separation unlocking device, includes separation base, locking separation module and top pushes away the module, its characterized in that, locking separation module includes that at least two are fixed last and along the locking separation element that satellite circumference distributes of separation base, every locking separation element includes:
the locking rod base is fixed on the separating base;
the swing rod is arranged on the locking rod base through a rotating shaft, and the inner side of the swing rod is provided with a lock pin inserted into a lock hole of the satellite so as to tightly press the satellite on the pushing module;
the locking piece is used for positioning the swing rod at the position where the lock pin is inserted into the lock hole, the locking piece is in an unlocking state, the pushing module pushes the satellite to be separated in the unlocking state, and the lock hole is separated from the lock pin and the swing rod rotates outwards in the separation process;
the locking member includes:
the explosive bolt penetrates through a bolt hole formed in the outer side of the swing rod;
the locking nut is connected with one end of the explosive bolt in a matched mode and is arranged on one side, far away from the locking rod base, of the bolt hole;
one end of the locking rod penetrates out of the back face of the locking rod base and is connected with the other end of the explosion bolt through a connecting nut, and the other end of the locking rod is provided with a step which is abutted against the back face of the locking rod base.
2. The spherical satellite separation unlocking device according to claim 1, wherein a locking sleeve sleeved on the locking rod is arranged on the back of the locking rod base, a compression spring sleeved on the locking rod is arranged in the locking sleeve, and the compression spring abuts between an inner step of the locking sleeve and a step of the locking rod.
3. The spherical satellite separation unlocking device according to claim 1, wherein a safety nut disposed between the coupling nut and the bolt hole is fittingly mounted on the explosion bolt.
4. The global satellite separation unlocking device as claimed in claim 1, wherein the base of the locking lever and the swing link have opposite surfaces perpendicular to the rotation axis, one of the opposite surfaces is provided with a mounting groove and a limit bolt, an elastic member is provided between the mounting groove and the tail end of the limit bolt, the top end of the limit bolt abuts against the other opposite surface, and the other opposite surface is provided with a bolt hole engaged with the limit bolt to position the swing link to rotate outwards.
5. The spherical satellite separation unlocking device according to claim 1, wherein the pushing module comprises:
the sleeve is fixed on the separating base;
the inner sleeve push rod is arranged in the sleeve, and the top of the inner sleeve push rod supports the satellite;
and the separation spring is arranged between the sleeve and the inner sleeve push rod and is compressed by the inner sleeve push rod.
6. The spherical satellite separation unlocking device according to claim 5, wherein a limit rod is further provided between the inner sleeve push rod and the sleeve.
7. The release device for separating spherical satellites according to claim 5, wherein the top of the push rod of the inner sleeve is an annular opening, the annular opening is provided with a flanging, and the flanging abuts against the separation spring.
8. The spherical satellite separation unlocking device as defined in claim 1, wherein the locking pin and the locking hole are circular arc shaped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711296549.XA CN108116697B (en) | 2017-12-08 | 2017-12-08 | A spherical satellite separation and unlocking device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711296549.XA CN108116697B (en) | 2017-12-08 | 2017-12-08 | A spherical satellite separation and unlocking device |
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| Publication Number | Publication Date |
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| CN108116697A CN108116697A (en) | 2018-06-05 |
| CN108116697B true CN108116697B (en) | 2021-06-15 |
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| CN201711296549.XA Active CN108116697B (en) | 2017-12-08 | 2017-12-08 | A spherical satellite separation and unlocking device |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109737831A (en) * | 2019-02-19 | 2019-05-10 | 北京星际荣耀空间科技有限公司 | A kind of non-firer's separator based on blasting bolt |
| CN109941463B (en) * | 2019-02-27 | 2022-08-26 | 哈尔滨工业大学（威海） | Active-passive butt-joint locking type cell connection robot unit and using method thereof |
| CN111284731B (en) * | 2020-01-16 | 2020-11-10 | 清华大学 | Electromagnetic locking and releasing mechanism for separating star from arrow and electromagnetic locking and releasing method |
| CN113955157B (en) * | 2021-11-26 | 2023-08-29 | 深圳力合精密装备科技有限公司 | Space flight repeated locking system |
| CN115140320A (en) * | 2022-08-18 | 2022-10-04 | 北京中科宇航技术有限公司 | Pneumatic separation unlocking device and system |
| CN118062268B (en) * | 2024-04-17 | 2024-07-09 | 东方蓝天钛金科技有限公司 | Double-insurance quick separation device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204355287U (en) * | 2014-11-25 | 2015-05-27 | 上海宇航系统工程研究所 | A kind of Space Double priming system backup locking releasing device |
| 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 |
| JP2017007529A (en) * | 2015-06-23 | 2017-01-12 | 株式会社Ｉｈｉエアロスペース | Artificial satellite separator |
| CN106628274A (en) * | 2017-01-23 | 2017-05-10 | 浙江大学 | General locking and separating device for cubesat |
| CN107054700A (en) * | 2017-03-30 | 2017-08-18 | 哈尔滨工业大学（威海） | A kind of satellite and the rocket separation locking releasing device |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2757466B2 (en) * | 1989-06-22 | 1998-05-25 | 日産自動車株式会社 | Buffer structure of the pyrotechnic coupling / separation device |
| DE102008022467A1 (en) * | 2008-05-07 | 2009-11-12 | Astrium Gmbh | Spring-damper system |
| CN101645534B (en) * | 2009-08-31 | 2012-09-26 | 西安空间无线电技术研究所 | Turnover space-borne antenna locking releasing device |
-
2017
- 2017-12-08 CN CN201711296549.XA patent/CN108116697B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN204355287U (en) * | 2014-11-25 | 2015-05-27 | 上海宇航系统工程研究所 | A kind of Space Double priming system backup locking releasing device |
| JP2017007529A (en) * | 2015-06-23 | 2017-01-12 | 株式会社Ｉｈｉエアロスペース | Artificial satellite separator |
| CN106628274A (en) * | 2017-01-23 | 2017-05-10 | 浙江大学 | General locking and separating device for cubesat |
| CN107054700A (en) * | 2017-03-30 | 2017-08-18 | 哈尔滨工业大学（威海） | A kind of satellite and the rocket separation locking releasing device |
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