CN209321291U - A kind of in-orbit unlocking separation mechanism of satellite - Google Patents
A kind of in-orbit unlocking separation mechanism of satellite Download PDFInfo
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- CN209321291U CN209321291U CN201821974788.6U CN201821974788U CN209321291U CN 209321291 U CN209321291 U CN 209321291U CN 201821974788 U CN201821974788 U CN 201821974788U CN 209321291 U CN209321291 U CN 209321291U
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Abstract
The utility model discloses a kind of in-orbit unlocking separation mechanism of satellite, including bearing body, the bearing body has and undersetting optics load rigidly connected upper bracket and connect with Platform Machinery structural rigidity；The pretightning force locking that load-carrying construction component, the upper bracket and the undersetting are linked together by the load-carrying construction component and the load-carrying construction component passes through blasting bolt thereon；And locked component is collapsed, the locked component that collapses is to limit motion profile in load-carrying construction component separation and collapse the load-carrying construction component after separation in the gatherings locked component inside.The unlocking separation mechanism structural strength of the utility model is good, rigidity is high, carrying is big, realizes quick release, the unlock and separation that multiple unlocking separation mechanism synchronisms are preferable and the unlocking separation mechanism is suitable for middle-size and small-size satellite.Using the release of blasting bolt pretightning force and tension spring tension double copies, securely and reliably.
Description
Technical field
The utility model relates to space technology fields, and in particular to a kind of in-orbit unlocking separation mechanism of satellite.
Background technique
In satellite launch technology, unlock separator would generally be assembled between Platform Machinery structure and optics load, the solution
On the one hand Platform Machinery structure and optics load can be rigidly attached and are integrated in satellite launch by lock separator, with reality
The delivery of existing optics load；On the other hand, unlock separator can realize unlock and separation after satellite reaches designated position
Above-mentioned Platform Machinery structure and optics load, to achieve the purpose that appropriate optics load.Therefore, unlock separator is to guarantee
The key mechanism that satellite launch success or not and function can be realized.
In the prior art, in order to realize the unlock and separation of Platform Machinery structure and optics load, separator is unlocked
Form also there are many kinds of, such as:
One, hot knife compresses release structure, which is using hot knife as separation unit, and when loading utilizes cleavable constraint
Optics load is directly anchored in Platform Machinery structure by element, with delivery, utilizes the fervent of hot knife after reaching designated position
Effect cuts off constraint element and discharges optics load, to achieve the purpose that unlock and separation；But through a long time uses discovery,
Although compressing the structure discharged to optics load with lesser impact force and with light-weight, small in size etc. excellent with hot knife
Point, but its to unlock release time longer, while it is lower to require power supply to continue work done, reliability, so, compressed and discharged with hot knife
Form is only applicable to the unlock release of side crops industry；
Two, separation nut structure type, this kind of structure type is axial in the presence of displacement when bolt pretightening discharges, and
Impact force along Sensitive Apparatus direction is larger, so, this kind of structure type is not suitable in optics load-carrying at this stage yet
Unlock release；
Three, blasting bolt direct coupled structure, although being directly connected to using blasting bolt, structure is simple, and gunpowder explosion causes
Impact it is larger, be easy to impact Sensitive Apparatus, therefore, higher shock resistance requirement needed for structural member.
In conclusion optics load and platform mechanical structure are mainly attached with above-mentioned three kinds of structures in the prior art,
I.e. existing unlock separator is mostly above-mentioned three kinds of structures.And in view of needing to eliminate the in-orbit in-flight Platform Machinery knot of satellite
Influence, satellite posture adjustment component micro-vibration effect to optics load of the structure power thermal deformation to optics load, the three kinds of above structures
Form is unable to satisfy the unlock release request of optics load in satellite launch at this stage, and therefore, it is necessary to those skilled in the art
It is innovated and is improved.
Utility model content
The purpose of the utility model is to provide a kind of structure novel, intensity is good, rigidity is high, carrying is big, load-bearing is rapid,
Synchronism is preferable and is suitable for the unlock of middle-size and small-size satellite and the isolated in-orbit unlocking separation mechanism of satellite.
To achieve the goals above, the utility model provides the following technical solutions:
The in-orbit unlocking separation mechanism of a kind of satellite disclosed by the utility model, the unlocking separation mechanism are carried to connect optics
Lotus and platform mechanical structure, the unlocking separation mechanism specifically include that
Bearing body, the bearing body have rigid with the rigidly connected upper bracket of optics load and with Platform Machinery structure
Property connection undersetting；
Load-carrying construction component, the upper bracket and the undersetting are linked together by the load-carrying construction component and institute
It states load-carrying construction component to lock by the pretightning force of blasting bolt thereon, in delivery, the load-carrying construction component passes through described
The fracture of blasting bolt is to discharge the constraint to the bearing body and separate the optics load and platform mechanical structure；And
Collapse locked component, the movement rail for collapsing locked component to limit in the load-carrying construction component separation
Mark and the load-carrying construction component after separation is collapsed in gatherings locked component inside.
Further, the load-carrying construction component includes two bands being hinged, respectively right band and left band；
Wherein, the right band and left band are semi-circular cylindrical structure, and one end of the semi-circular cylindrical structure is formed
For the first connecting pin, it is formed with band axis hole on first connecting pin, is equipped with shaft in the band axis hole；
The right band and left band can be rotated around the shaft；
Separate described shaft one end of the right band and left band is formed with the flange extended towards outside, and two institutes
State the second connection end that flange is right band and left band；
The bearing body clamping fastener is in the semi-circular cylindrical structure of the right band and left band, and two flange
It is bonded to each other, the blasting bolt is assemblied on the flange.
Further, the upper bracket includes the upper bracket interconnecting piece for being placed in upper end, to be formed in the upper bracket connection
Upper bracket mounting portion below portion；
The undersetting includes being placed in the undersetting interconnecting piece of lower end and being formed in above the undersetting interconnecting piece
Undersetting mounting portion；
Optics load and the upper bracket are rigidly connected in the upper bracket interconnecting piece, and the upper bracket peace of the upper bracket
Dress portion extends in installation space cylindric composed by right band and left band；
Platform Machinery structure and the undersetting are rigidly connected in the undersetting interconnecting piece, and the lower branch of the undersetting
Seat mounting portion extends in installation space cylindric composed by right band and left band.
Further, four have been axially formed along it in installation space cylindric composed by the right band and left band
Group annular V-shaped contact surface, V-type contact surface described in four groups be from top to bottom followed successively by the first V-type contact surface, the second V-type contact surface,
Third V-type contact surface and the 4th V-type contact surface；
When the upper bracket and undersetting are anchored on the installation space, the lower end of the upper bracket mounting portion and it is described under
The upper end of support mounting portion is reserved with gap, which is first gap；
The upper bracket mounting portion and the first V-type contact surface and the second V-type contact surface are snugly anchored on the peace
It fills in space, and the upper bracket mounting portion offers upper bracket wedge groove, the inner wall of the installation space and institute along its circumferential direction
It states and is reserved with gap between upper bracket wedge groove, which is Second gap；
The undersetting mounting portion and the third V-type contact surface and the 4th V-type contact surface are snugly anchored on the peace
It fills in space, and the undersetting mounting portion offers undersetting wedge groove, the inner wall of the installation space and institute along its circumferential direction
It states and is reserved with gap between undersetting wedge groove, which is third gap.
Further, the gathering locked component includes the baffle being symmetrically arranged on the outside of the right band and left band,
And the baffle and the undersetting are connected；
The gathering locked component further includes the rotary shaft rack for being placed in the right band and left band, the rotary shaft rack with
The undersetting is connected, and the top of the rotary shaft rack is equipped with shaft screw, and the rotary shaft rack and the shaft screw are used
To limit the rotational angle of the right band and left band after unlock；
The gathering locked component has a tension spring, one end of the tension spring and connected, the described tension spring of the baffle
The other end is connected by spring joint and the adjacent band；
When the right band and left band lock state, the tension spring is in tensional state；
The outer peripheral surface of the band is stained with thread gluing by Wear Characteristics of Epoxy Adhesive, when the right band and left band separate, the right side
Band and left band rotate synchronously to two sides by the tension spring and fit in the inside of the baffle；
The baffle of the right band and left band by the thread gluing respectively at two sides after separation bonds.
In the above-mentioned technical solutions, the in-orbit unlocking separation mechanism of a kind of satellite provided by the utility model has with following
Beneficial effect:
1, the unlocking separation mechanism of the utility model devises load-carrying construction component, and is distinguished by upper bracket and undersetting
The optics load that is rigidly connected and platform mechanical structure, meanwhile, load-carrying construction component is fastened as fastener by blasting bolt,
And the drive force source that the blasting bolt is also isolated as unlock, the momentum effect generated after explosion fracture is in load-carrying construction component
On, it avoids and impact force is generated to sensitive gas source, it is more novel to arrange structure；
2, the unlocking separation mechanism structural strength of the utility model is good, rigidity is high, carrying is big, realizes quick release, is more
The unlock and separation that a unlocking separation mechanism synchronism is preferable and the unlocking separation mechanism is suitable for middle-size and small-size satellite.Using
The release of blasting bolt pretightning force and tension spring tension double copies, securely and reliably.
Detailed description of the invention
In order to illustrate the technical solutions in the embodiments of the present application or in the prior art more clearly, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only to record in the utility model
Some embodiments be also possible to obtain other drawings based on these drawings for those of ordinary skill in the art.
Fig. 1 is a kind of structural schematic diagram of the in-orbit unlocking separation mechanism of satellite provided by the embodiment of the utility model；
Fig. 2 is a kind of cross-sectional view of the in-orbit unlocking separation mechanism of satellite provided by the embodiment of the utility model；
Fig. 3 be a kind of in-orbit unlocking separation mechanism of satellite provided by the embodiment of the utility model right band and left band solution
Structural schematic diagram under lock status.
Description of symbols:
101, upper bracket；102, undersetting；
201, right band；202, left band；203, shaft；
3, blasting bolt；
301, instead of screw；302, priming system flange；303, pin is installed；
401, baffle；402, tension spring；403, rotary shaft rack；404, shaft screw；405, spring joint；406, thread gluing；
501, first gap；502, Second gap；503, third gap；
601, the first V-type contact surface；602, the second V-type contact surface；603, third V-type contact surface；604, the 4th V-type connects
Contacting surface；
10101, upper bracket interconnecting piece；10102, upper bracket mounting portion；
10201, undersetting interconnecting piece；10202, undersetting mounting portion；
7, flange.
Specific embodiment
In order to make those skilled in the art more fully understand the technical solution of the utility model, below in conjunction with attached drawing pair
The utility model is further detailed.
Referring to shown in FIG. 1 to FIG. 3, a kind of in-orbit unlocking separation mechanism of satellite provided by the embodiment of the utility model, the solution
Lock separating mechanism is specifically included that connect optics load and platform mechanical structure, unlocking separation mechanism
Bearing body, bearing body have with the rigidly connected upper bracket 101 of optics load and with Platform Machinery structural rigidity
The undersetting 102 of connection；
Load-carrying construction component, upper bracket 101 and undersetting 102 is linked together by load-carrying construction component and load-carrying construction
Component is by the pretightning force locking of blasting bolt 3 thereon, in delivery, load-carrying construction component by the fracture of blasting bolt 3 with
It discharges the constraint to bearing body and separates optics load and platform mechanical structure；And
Locked component is collapsed, collapses locked component to limit the motion profile in the separation of load-carrying construction component and incite somebody to action
Load-carrying construction component after separation collapses on the inside of gathering locked component.
Specifically, present embodiment discloses the solutions of a kind of optics load (not shown) and Platform Machinery structure (not shown)
Lock separating mechanism, be different from the prior art in tripper, the present embodiment using above-mentioned load-carrying construction component to bearing body
It is formed and is reinforced, while the assembly of blasting bolt 3 and load-carrying construction component is for the optics load and Platform Machinery knot of upper and lower ends
It is configured to be indirectly connected with.Load-carrying construction component is realized release and is divided under the driving for collapsing locked component after blasting bolt 3 is broken
From, and optics load and platform mechanical structure is driven to separate, optics load is discharged, though and due to the blasting bolt of the present embodiment 3
So as unlock driving force source, but its be it is direct-connected with above-mentioned load-carrying construction component, explosion time generation impact force not
It can be applied directly on Sensitive Apparatus, efficiently solve technical problem excessive to Sensitive Apparatus impact force in the prior art.
Preferably, load-carrying construction component includes two bands being hinged in the present embodiment, respectively right 201 He of band
Left band 202；
Wherein, right band 201 and left band 202 are semi-circular cylindrical structure, and one end of semi-circular cylindrical structure is formed as
First connecting pin is formed with band axis hole on the first connecting pin, is equipped with shaft 203 in the band axis hole；
Right band 201 and left band 202 being capable of 203 rotations around the shaft；
203 one end of separate shaft of right band 201 and left band 202 is formed with the flange 7 extended towards outside, and two
Flange 7 is the second connection end of right band 201 and left band 202；
Bearing body clamping fastener is in the semi-circular cylindrical structure of right band 201 and left band 202, and two flange 7 are mutual
Fitting, blasting bolt 3 are assemblied on flange 7.
The present embodiment specifically describes the structure of load-carrying construction component, wherein the load-carrying construction component includes two mutual
The right band 201 and left band 202 of rotation connection, and right band 201 and left band 202 form one by its architectural characteristic
The cylindric installation space of above-mentioned bearing body can be gripped；And the outer skidding of right band 201 and left band 202 forms
Outwardly extending flange 7 also provides sufficient behaviour while providing installation site to blasting bolt 3 to mount and dismount
Make space.In addition, the edge of band is required to do round corner treatment (shown in Figure 3) in order to avoid band stress concentration.
Preferably, above-described embodiment is accepted, upper bracket 101 includes the upper bracket interconnecting piece for being placed in upper end in the present embodiment
10101, the upper bracket mounting portion 10102 to be formed in below upper bracket interconnecting piece 10101；
Undersetting 102 includes being placed in the undersetting interconnecting piece 10201 of lower end and being formed in undersetting interconnecting piece 10201
The undersetting mounting portion 10202 of top；
Optics load and upper bracket 101 are rigidly connected in upper bracket interconnecting piece 10101, and the upper bracket peace of upper bracket 101
Dress portion 10102 extends in installation space cylindric composed by right band 201 and left band 202；
Platform Machinery structure and undersetting 102 are rigidly connected in undersetting interconnecting piece 10201, and the lower branch of undersetting 102
Seat mounting portion 10202 extends in installation space cylindric composed by right band 201 and left band 202.
The present embodiment shown in referring to fig. 2~Fig. 3 mainly describes the structure of bearing body, which is divided into two parts, point
Wei not be placed in top and with the rigidly connected upper bracket 101 of optics load, and be placed in lower part and with Platform Machinery structural rigidity
The undersetting 102 of connection；Meanwhile being connect to realize with load-carrying construction component, upper bracket 101 and undersetting 102 are respectively formed
There is the upper bracket mounting portion 10102 and undersetting mounting portion 10202 extended towards installation space, and utilizes the folder of installation space
Realization is held to fix.
In addition, being axially formed in installation space cylindric composed by above-mentioned right band 201 and left band 202 along it
There are four groups of annular V-shaped contact surfaces, four groups of V-type contact surfaces are from top to bottom followed successively by the first V-type contact surface 601, the second V-type contact surface
602, third V-type contact surface 603 and the 4th V type contact surface 604；
When upper bracket 101 and undersetting 102 are anchored on installation space, the lower end of upper bracket mounting portion 10102 and undersetting
The upper end of mounting portion 10202 is reserved with gap, which is first gap 501；
Upper bracket mounting portion 10102 and the first V-type contact surface 601 and the second V-type contact surface 602 are snugly anchored on installation
In space, and upper bracket mounting portion 10102 offers upper bracket wedge groove, the inner wall and upper bracket wedge of installation space along its circumferential direction
It is reserved with gap between shape slot, which is Second gap 502；
Undersetting mounting portion 10202 and third V-type contact surface 603 and the 4th V-type contact surface 604 are snugly anchored on installation
In space, and undersetting mounting portion 10202 offers undersetting wedge groove, the inner wall and undersetting wedge of installation space along its circumferential direction
It is reserved with gap between shape slot, which is third gap 503.
In order to lock after guaranteeing band stress, also for ensuring that is unlocked go on smoothly, two in the present embodiment
A band is formed by cylindric installation space and support body portion is formed away from structure, and when fastening, main firm contact
Face is four groups of above-mentioned annular V-shaped contact surfaces.And in fastening, upper bracket 101 and undersetting 102, upper bracket 101 and installation are empty
Between, between undersetting 102 and installation space be reserved with above-mentioned first gap 501, Second gap 502, third gap 503 respectively
Ensure that upper bracket 101, undersetting 102, band can be smoothly detached when purpose is unlock, is not in locked.
Preferably, it includes being symmetrically arranged in 202 outside of right band 201 and left band that locked component is collapsed in the present embodiment
Baffle 401, and baffle 401 and undersetting 102 are connected；
Collapsing locked component further includes the rotary shaft rack 403 for being placed in right band 201 and left band 202, rotary shaft rack 403 with
Undersetting 102 be connected, the top of rotary shaft rack 403 be equipped with shaft screw 404, rotary shaft rack 403 and shaft screw 404 to
The rotational angle of right band 201 and left band 202 after limitation unlock；
Collapsing locked component has a tension spring 402, and one end of tension spring 402 and baffle 401 are connected, tension spring 402 another
End is connected by spring joint 405 and adjacent band；
When right band 201 and left 202 lock state of band, tension spring 402 is in tensional state；
The outer peripheral surface of band is stained with thread gluing 406 by Wear Characteristics of Epoxy Adhesive, when right band 201 and left band 202 separate, right packet
It is rotated synchronously by tension spring 402 to two sides with 201 and left band 202 and fits in the inside of baffle 401；
The baffle 401 of right band 201 and left band 202 by thread gluing 406 respectively at two sides after separation bonds.
The gathering lock of rotary shaft rack 403, baffle 401, tension spring 402 as load-carrying construction component after unlock in the present embodiment
Determine structure, after the gunpowder in blasting bolt 3 is ignited, high temperature and high pressure gas expansion working promotion piston push rod to spacing place, due to
There are stress concentrations, as bonding strength weak link for incision, and brittle fracture occurs at screw rod edge notches, connected
Two band component separation.It is in tensional state after above-mentioned tension spring installation, after blasting bolt 3 is broken, two bands explode
It 203 being rotated around the shaft to two sides respectively under the action of momentum, the pulling force that tension spring 402 generates is identical as band separating rate, direction,
Therefore, tension spring 402 plays the role of redundancy backup.Finally, band is collapsed by the tension of tension spring 402 in baffle 401
Side.In addition, the outer surface of above-mentioned band is stained with thread gluing 406 by Wear Characteristics of Epoxy Adhesive, once tension spring 402 drives band and baffle
The contact of 401 inner walls, it is firm that thread gluing 406 is bonded, and completes locking.And as the separation of band, upper bracket 101 and undersetting 102 divide
From function is realized.
Finally, it should be understood that since blasting bolt 3 belongs to explosive dangerous material, it during transportation, can be with
Blasting bolt 3 is replaced to fasten two bands using replacement screw 301, and in actually delivering, blasting bolt 3 is replaced back
Come.
The unlocking separation mechanism of the present embodiment needs excessively to be taken turns test, including mechanics vibration examination before being applied to spacecraft
It tests, spatial heat environment test, Release separation test, to improve structural reliability comprehensively.
In the above-mentioned technical solutions, the in-orbit unlocking separation mechanism of a kind of satellite provided by the utility model has with following
Beneficial effect:
The unlocking separation mechanism of the utility model devises load-carrying construction component, and passes through upper bracket 101 and undersetting 102
Be rigidly connected optics load and platform mechanical structure respectively, meanwhile, it is used as fastener by load-carrying construction component by blasting bolt 3
Fastening, and the drive force source that the blasting bolt 3 is also isolated as unlock, the momentum effect generated after explosion fracture is in load-carrying construction
It on component, avoids and impact force is generated to sensitive gas source, it is more novel to arrange structure；
The unlocking separation mechanism structural strength of the utility model is good, rigidity is high, carrying is big, realizes quick release, is multiple
The unlock and separation that unlocking separation mechanism synchronism is preferable and the unlocking separation mechanism is suitable for middle-size and small-size satellite.Using quick-fried
Fried 3 pretightning force of bolt release and 402 pulling force double copies of tension spring, securely and reliably.
It is above that certain exemplary embodiments of the utility model are only described by way of explanation, undoubtedly, for
Those skilled in the art can be with a variety of different without departing from the spirit and scope of the utility model
Mode is modified described embodiment.Therefore, above-mentioned attached drawing and description are regarded as illustrative in nature, and should not be construed as
Limitation to the utility model claims protection scope.
Claims (5)
1. a kind of in-orbit unlocking separation mechanism of satellite, the unlocking separation mechanism to connect optics load and platform mechanical structure,
It is characterized in that, the unlocking separation mechanism specifically includes that
Bearing body, the bearing body have rigid with the rigidly connected upper bracket of optics load (101) and with Platform Machinery structure
Property connection undersetting (102)；
Load-carrying construction component, the upper bracket (101) and the undersetting (102) are linked as one by the load-carrying construction component
The pretightning force that body and the load-carrying construction component pass through blasting bolt (3) thereon is locked, in delivery, the load-carrying construction group
Part is discharged the constraint to the bearing body by the fracture of the blasting bolt (3) and separates the optics load and platform
Mechanical structure；And
Locked component is collapsed, collapses locked component to limit the motion profile in the load-carrying construction component separation and incite somebody to action
The load-carrying construction component after separation collapses on the inside of the gathering locked component.
2. the in-orbit unlocking separation mechanism of a kind of satellite according to claim 1, which is characterized in that the load-carrying construction component
Including two bands being hinged, respectively right band (201) and left band (202)；
Wherein, the right band (201) and left band (202) are semi-circular cylindrical structure, and the one of the semi-circular cylindrical structure
End is formed as the first connecting pin, being formed with band axis hole on first connecting pin, is equipped with shaft in the band axis hole
(203)；
The right band (201) and left band (202) can be rotated around the shaft (203)；
The right band (201) and being formed with far from the shaft (203) one end towards what outside extended for left band (202) are turned over
Side (7), and two flange (7) are the second connection end of right band (201) and left band (202)；
The bearing body clamping fastener is in the semi-circular cylindrical structure of the right band (201) and left band (202), and two institutes
It states flange (7) to be bonded to each other, the blasting bolt (3) is assemblied on the flange (7).
3. the in-orbit unlocking separation mechanism of a kind of satellite according to claim 2, which is characterized in that the upper bracket (101)
Upper bracket interconnecting piece (10101) including being placed in upper end, the upper bracket to be formed in below the upper bracket interconnecting piece (10101)
Mounting portion (10102)；
The undersetting (102) includes being placed in the undersetting interconnecting piece (10201) of lower end and being formed in the undersetting to connect
Undersetting mounting portion (10202) above portion (10201)；
Optics load and the upper bracket (101) are rigidly connected in the upper bracket interconnecting piece (10101), and the upper bracket
(101) upper bracket mounting portion (10102) extends to installation cylindric composed by right band (201) and left band (202)
In space；
Platform Machinery structure and the undersetting (102) are rigidly connected in the undersetting interconnecting piece (10201), and the lower branch
The undersetting mounting portion (10202) of seat (102) extends to peace cylindric composed by right band (201) and left band (202)
It fills in space.
4. the in-orbit unlocking separation mechanism of a kind of satellite according to claim 3, which is characterized in that the right band (201)
Four groups of annular V-shaped contact surfaces, four groups of institutes have been axially formed along it in installation space cylindric composed by left band (202)
It states V-type contact surface and is from top to bottom followed successively by the first V-type contact surface (601), the second V-type contact surface (602), third V-type contact surface
(603) and the 4th V-type contact surface (604)；
When the upper bracket (101) and undersetting (102) are anchored on the installation space, the upper bracket mounting portion (10102)
Lower end and the upper end of the undersetting mounting portion (10202) be reserved with gap, which is first gap (501)；
The upper bracket mounting portion (10102) and the first V-type contact surface (601) and the second V-type contact surface (602) are snugly
It is anchored in the installation space, and the upper bracket mounting portion (10102) offers upper bracket wedge groove along its circumferential direction, it is described
It is reserved with gap between the inner wall of installation space and the upper bracket wedge groove, which is Second gap (502)；
The undersetting mounting portion (10202) and the third V-type contact surface (603) and the 4th V-type contact surface (604) are snugly
It is anchored in the installation space, and the undersetting mounting portion (10202) offers undersetting wedge groove along its circumferential direction, it is described
It is reserved with gap between the inner wall of installation space and the undersetting wedge groove, which is third gap (503).
5. the in-orbit unlocking separation mechanism of a kind of satellite according to claim 2, which is characterized in that the gathering locked component
Including the baffle (401) being symmetrically arranged on the outside of the right band (201) and left band (202), and the baffle (401) and institute
Undersetting (102) are stated to be connected；
The gathering locked component further includes the rotary shaft rack (403) for being placed in the right band (201) and left band (202), institute
It states rotary shaft rack (403) and the undersetting (102) to be connected, the top of the rotary shaft rack (403) is equipped with shaft screw
(404), the rotary shaft rack (403) and the shaft screw (404) are to limit the right band (201) and a left side after unlocking
The rotational angle of band (202)；
The gathering locked component has a tension spring (402), one end of the tension spring (402) and the baffle (401) are connected,
The other end of the tension spring (402) is connected by spring joint (405) and the adjacent band；
When the right band (201) and left band (202) lock state, the tension spring (402) is in tensional state；
The outer peripheral surface of the band is stained with thread gluing (406) by Wear Characteristics of Epoxy Adhesive, the right band (201) and left band (202) point
From when, the right band (201) and left band (202) are rotated synchronously to two sides by the tension spring (402) and described in fitting in
The inside of baffle (401)；
The right band (201) and left band (202) after separation by the thread gluing (406) respectively at two sides baffle
(401) it bonds.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821974788.6U CN209321291U (en) | 2018-11-28 | 2018-11-28 | A kind of in-orbit unlocking separation mechanism of satellite |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821974788.6U CN209321291U (en) | 2018-11-28 | 2018-11-28 | A kind of in-orbit unlocking separation mechanism of satellite |
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| CN201821974788.6U Active CN209321291U (en) | 2018-11-28 | 2018-11-28 | A kind of in-orbit unlocking separation mechanism of satellite |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110481817A (en) * | 2019-09-04 | 2019-11-22 | 北京微分航宇科技有限公司 | A kind of in-orbit retaining mechanism of repetition |
| CN111864470A (en) * | 2020-08-07 | 2020-10-30 | 国网江苏省电力有限公司常州供电分公司 | Universal power interface convenient for replacing and locking |
| CN113184226A (en) * | 2021-04-22 | 2021-07-30 | 上海宇航系统工程研究所 | Belting type space locking and releasing device |
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2018
- 2018-11-28 CN CN201821974788.6U patent/CN209321291U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110481817A (en) * | 2019-09-04 | 2019-11-22 | 北京微分航宇科技有限公司 | A kind of in-orbit retaining mechanism of repetition |
| CN110481817B (en) * | 2019-09-04 | 2024-03-26 | 北京微分航宇科技有限公司 | Repeated on-orbit locking mechanism |
| CN111864470A (en) * | 2020-08-07 | 2020-10-30 | 国网江苏省电力有限公司常州供电分公司 | Universal power interface convenient for replacing and locking |
| CN113184226A (en) * | 2021-04-22 | 2021-07-30 | 上海宇航系统工程研究所 | Belting type space locking and releasing device |
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