CN107054700A - A kind of satellite and the rocket separation locking releasing device - Google Patents
A kind of satellite and the rocket separation locking releasing device Download PDFInfo
- Publication number
- CN107054700A CN107054700A CN201710203183.0A CN201710203183A CN107054700A CN 107054700 A CN107054700 A CN 107054700A CN 201710203183 A CN201710203183 A CN 201710203183A CN 107054700 A CN107054700 A CN 107054700A
- Authority
- CN
- China
- Prior art keywords
- bottom plate
- claw
- satellite
- connecting seat
- swing rod
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000926 separation method Methods 0.000 title claims abstract description 19
- 210000000078 claw Anatomy 0.000 claims abstract description 43
- 238000010276 construction Methods 0.000 abstract description 5
- 238000005516 engineering process Methods 0.000 abstract description 4
- 240000000560 Citrus x paradisi Species 0.000 abstract description 2
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical group [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 6
- 238000005422 blasting Methods 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 238000010030 laminating Methods 0.000 description 2
- 230000009466 transformation Effects 0.000 description 2
- 230000009194 climbing Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000037452 priming Effects 0.000 description 1
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Clamps And Clips (AREA)
Abstract
A kind of satellite and the rocket separation locking releasing device, it is related to the satellite and the rocket separation technology field of grapefruit satellite, including bottom plate, connecting seat, claw and connecting rod, rotary shaft is provided with the middle part of bottom plate, rotary shaft on the upside of bottom plate is provided with spill spin block, bottom plate is provided with least three connecting seats, and connecting seat is provided with body cradle；L-type tabular claw is upside down on body cradle, and claw upper arm is provided with neck, and connecting rod one end is provided with clamping joint；Provided with release swing rod is locked between connecting seat and spill spin block, the middle part of locking release swing rod is hinged with bottom plate, and locking discharges one end of swing rod and spill spin block is hinged, the other end is against on the side arm of claw；Rotary shaft is provided with release torsion spring, and one end of release torsion spring is fixed on bottom plate, the other end is fixed on spill spin block, and the rotary shaft of baseplate underside is provided with positioning lockhole, and bottom plate is provided with the sliding electromagnet being engaged with positioning lockhole.The present invention has simple in construction, small volume, lightweight, high reliability.
Description
Technical field
The present invention relates to the satellite and the rocket separation technology field of grapefruit satellite, say it is a kind of simple in construction, small volume, weight in detail
Gently, the high satellite and the rocket separation locking releasing device of reliability.
Background technology
It is known that the satellite and the rocket separate, be exactly in a general sense spacecraft or satellite after the scope of terrestrial gravitation is left, with fortune
Carry the separation process of rocket.Locking releasing device is the device for realizing satellite and the rocket separation function, is widely used in boat all the time
In empty space mission, it can provide pretightning force for space flight annex makes its not loose or dislocation in emission process, it can be allowed to reach again
Release is separated during desired track position.
Existing satellite and the rocket piece-rate system is mainly several typical combination sides such as band, spring, blasting bolt, retro-rocket
Formula, satellite and the rocket separator traditional at present is generally Fire load and blasting bolt, large impact can be produced during release, simultaneously
Seriously polluted, priming system experimental cost is higher and is difficult to transport and deposits, and with the development of moonlet and cube star technology,
Traditional satellite and the rocket separator is because its intrinsic shortcoming is dfficult to apply to the transmitting of moonlet.
The content of the invention
Present invention aim to address above-mentioned the deficiencies in the prior art, there is provided a kind is simple in construction, small volume, weight
Gently, the high satellite and the rocket separation locking releasing device of reliability.
The present invention solves the technical scheme that above-mentioned the deficiencies in the prior art are used：
In a kind of satellite and the rocket separation locking releasing device, it is characterised in that including bottom plate, connecting seat, claw and connecting rod, bottom plate
The rotary shaft that portion is provided with the upside of rotary shaft, bottom plate is provided with rotary shaft on spill spin block, bottom plate and is surrounded by least three connecting seats,
On connecting seat body cradle is provided with spill spin block opposite side；The L-shaped tabular of described claw, L-type tabular claw is inverted to be hinged
On body cradle, claw upper arm is provided with neck, and connecting rod one end is provided with clamping joint；Provided with locking between connecting seat and spill spin block
Swing rod is discharged, the middle part of locking release swing rod is hinged through rotating shaft with bottom plate, locks the one end for discharging swing rod with spill spin block through bearing pin
It is hinged, the other end is against on the side arm of claw；Rotary shaft provided with release torsion spring, release torsion spring one end be fixed on bottom plate,
The other end is fixed on spill spin block, and the rotary shaft of baseplate underside is provided with positioning lockhole, and bottom plate is provided with to match with positioning lockhole
The sliding electromagnet of conjunction.
Heretofore described connecting seat is vertically arranged on bottom plate in sleeve-shaped, pretension stage clip is provided with connecting seat, even
Provided with positioning supporting plate above joint chair, pretension stage clip two ends are connected with positioning supporting plate and connecting seat bottom respectively.
Heretofore described connecting seat is vertically arranged on bottom plate in sleeve-shaped, and the inwall of connecting seat bottom is provided with limit
Provided with the pressure pin that can slide up and down in position bulge loop, position limiting convex ring, the pressure pin on the downside of position limiting convex ring is provided with can be under position limiting convex ring
It is spacing provided with the positioning supporting plate being fixedly connected with pressure pin upper end above the limiting plate moved up and down in the connecting seat of side, connecting seat
Pretension stage clip is provided between bulge loop and positioning supporting plate.
With relative swing rod of the place provided with rectangular frame-shaped, lock in the middle part of locking release swing rod on heretofore described bottom plate
Tight release swing rod is interspersed in swing rod, middle part is hinged through rotating shaft and swing rod.
Heretofore described connecting rod is screw rod, and described clamping joint is the horizontal cylinder in screw rod lower end, claw
The downside of upper arm is in the arc coordinated with clamping joint.Laminating is closer, and connection is reliable；Clamping joint is more easy to from arc during release
Skidded off on the downside of clamping joint.
Optimal technical scheme in the present invention：By the rounded array-like in the center of circle of spill spin block provided with three connections on bottom plate
Seat.Employ simplest structure and realize firm connection.
The present invention is in use, rotate spill spin block, make locking discharge swing link end part to be against on the side arm of claw, now claw
Upper arm in level, release torsion spring be in twisting states, sliding electromagnet dynamic iron core insertion positioning lockhole in, sliding electromagnet with
Controller is connected；Base is fixedly connected with rocket, connecting rod and moonlet are connected；Connecting rod top and the bottom are slipped into neck, card
Joint is stuck on the downside of the upper arm of claw, and claw firmly catches on connecting rod, moonlet is fixedly connected with rocket.Divide when needing the satellite and the rocket
From when, controller control sliding electromagnet work, the dynamic iron core of sliding electromagnet is extracted out out of positioning lockhole, and rotary shaft is in release
Rotated in the presence of torsion spring, drive the side arm of the swing of locking release swing rod, end and claw to depart from, it is released the pact to claw
Beam, claw rotates in the presence of load, discharges clamping joint and connecting rod, and moonlet is released, reached the action of satellite and the rocket separation,
The present invention is by the way of non-firer, it is possible to achieve the locking of satellite and release function, with simple in construction, small volume, weight
Gently, the release impact low advantage of small, pollution-free, experimental cost, while sliding electromagnet matches with rocket rocket body voltage, without
Power supply is additionally matched, and innovative three connecting rods of use of the present apparatus are connected with satellite, only need to open three holes on satellite i.e.
It can be connected with the present apparatus, improve suitability, simplify the design and transformation difficulty of satellite.
Brief description of the drawings
Fig. 1 is the structural representation of the present invention.
Fig. 2 is Fig. 1 top view.
Fig. 3 is the dimensional structure diagram of the present invention.
Embodiment
Satellite and the rocket separation locking releasing device as shown in Figure 1, 2, 3, including bottom plate 14, connecting seat 1, claw 6 and connection
Bar 5, the middle part of bottom plate 14 is provided with vertical rotary shaft 10 through bearing, and the rotary shaft 10 of the upside of bottom plate 14 is provided with spill spin block 9, bottom plate
It is provided with 14 with rotary shaft 10 for the rounded array-like in the center of circle at least three connecting seats 1, connecting seat 1 and the opposite side of spill spin block 9
It is provided with body cradle 13；From figure 1 it appears that connecting seat 1 is vertically arranged on bottom plate in sleeve-shaped, the bottom of connecting seat 1
Inwall is provided with position limiting convex ring 11, position limiting convex ring 11 provided with the pressure pin 2 that can slide up and down, the pressure pin 2 of the downside of position limiting convex ring 11
Provided with the limiting plate 12 that can be slided up and down in the connecting seat 1 of the downside of position limiting convex ring 11, the top of connecting seat 1 is provided with and pressure pin 2
The positioning supporting plate 3 that upper end is fixedly connected, the pressure pin between position limiting convex ring and positioning supporting plate 3 is provided with pretension stage clip 4.Described claw
6 L-shaped tabulars, L-type tabular claw 6 is inverted to be hinged on body cradle 13, load-bearing axle and body cradle of the middle part of claw 6 through level
13 are hinged, and the upper arm of claw 6 is provided with the neck 19 that front end is opened wide, and the lower end of connecting rod 5 is provided with clamping joint 7；The upper arm level of claw 6
When, connecting rod 5 is placed vertically, and connecting rod can slide into and out from the front end of neck 19 of claw upper arm, and connecting rod 5 is from claw upper arm
Front end is slipped into when in neck 19, clamping joint 7 is stuck in the lower section of the upper arm of claw 6；One is each provided between connecting seat 1 and spill spin block 9
Locking release swing rod 15, rotating shaft of the middle part through being vertically arranged of locking release swing rod 15 is hinged with bottom plate, can be with from Fig. 2, Fig. 3
Find out, it is relative with 15 middle parts of locking release swing rod on bottom plate to locate the swing rod 16 provided with rectangular frame-shaped, locking release swing rod 15
It is interspersed in swing rod 16, middle part is hinged through rotating shaft and swing rod 16.One end of locking release swing rod 15 is with spill spin block 9 through vertical
Hinge, the other end is against on the side arm of claw 6（Now, the upper arm of claw is in level）；Rotary shaft 10 is provided with release
Torsion spring 8, release torsion spring 8 one end be fixed on bottom plate 14, the other end is fixed on spill spin block 9, the rotary shaft 10 of baseplate underside
Provided with positioning lockhole, baseplate underside is provided with the sliding electromagnet 18 being engaged with positioning lockhole；Sliding electromagnet 18 it is dynamic
Iron core is relative with positioning lockhole, and the dynamic iron core front end of sliding electromagnet 18 is provided with the dead bolt 17 being engaged with positioning lockhole, dead bolt
17 can be inserted into or extract positioning lockhole.
Of the invention further to improve, described connecting rod 5 is screw rod, and described clamping joint 7 is horizontal in screw rod lower end
Cylinder, the downside of claw upper arm is in the arc coordinated with clamping joint.Laminating is closer, and connection is reliable；Clamping joint during release
It is more easy to skid off on the downside of the clamping joint of arc.By the rounded array-like in the center of circle of spill spin block provided with three connections on described bottom plate
Seat.Employ simplest structure and realize firm connection.
The present invention is in use, rotate spill spin block, make locking discharge swing link end part to be against on the side arm of claw, now claw
Upper arm in level, release torsion spring be in twisting states, sliding electromagnet dynamic iron core insertion positioning lockhole in, sliding electromagnet with
Controller is connected；Base is fixedly connected with rocket, connecting rod and moonlet are connected；Connecting rod top and the bottom are slipped into neck, card
Joint is stuck on the downside of the upper arm of claw, and moonlet is pressed against on positioning supporting plate, pretension stage clip 4 have to it outside elastic force,
Make to produce pretightning force between clamping joint and claw, claw firmly catches on connecting rod, and moonlet is fixedly connected with rocket.When needing star
When arrow is separated, controller control sliding electromagnet work, the dynamic iron core of sliding electromagnet is extracted out out of positioning lockhole, and rotary shaft exists
Rotation in the presence of release torsion spring, drive that locking release swing rod is swung, the side arm of end and claw departs from, it is released to claw
Constraint, claw rotated in the presence of the pretightning force of pretension stage clip 4 and load, discharges clamping joint and connecting rod, and moonlet is released
The action of satellite and the rocket separation is put, reaches, the present invention is by the way of non-firer, it is possible to achieve the locking of satellite and release function, tool
Have simple in construction, small volume, it is lightweight, release impact the low advantage of small, pollution-free, experimental cost, while sliding electromagnet with
Rocket rocket body voltage matches, and power supply, and the present apparatus innovative three connecting rods of use and satellite phase are matched without extra
Even, only needing to open three holes on satellite can be connected with the present apparatus, improve suitability, simplify the design and transformation hardly possible of satellite
Degree.Present invention may also apply in the releasable connecting device in other fields, the protection device for outdoor exercises of such as climbing the mountain and large-scale
The connection of separable equipment.
Claims (6)
1. a kind of satellite and the rocket separation locking releasing device, it is characterised in that including bottom plate, connecting seat, claw and connecting rod, bottom plate
The rotary shaft that middle part is provided with the upside of rotary shaft, bottom plate is provided with rotary shaft on spill spin block, bottom plate and is surrounded by least three connections
On seat, connecting seat body cradle is provided with spill spin block opposite side；The L-shaped tabular of described claw, the inverted hinge of L-type tabular claw
It is connected on body cradle, claw upper arm is provided with neck, connecting rod one end is provided with clamping joint；Provided with lock between connecting seat and spill spin block
Tight release swing rod, the middle part of locking release swing rod is hinged through rotating shaft with bottom plate, and one end of locking release swing rod is sold with spill spin block
Axle is hinged, the other end is against on the side arm of claw；Rotary shaft is fixed on bottom plate provided with release torsion spring, one end of release torsion spring
The upper, other end is fixed on spill spin block, and the rotary shaft of baseplate underside is provided with positioning lockhole, and bottom plate is provided with and positioning lockhole phase
The sliding electromagnet of cooperation.
2. satellite and the rocket separation locking releasing device according to claim 1, it is characterised in that described connecting seat is in sleeve
Shape is vertically arranged on bottom plate, is provided with connecting seat above pretension stage clip, connecting seat provided with positioning supporting plate, pretension stage clip two ends point
It is not connected with positioning supporting plate and connecting seat bottom.
3. satellite and the rocket separation locking releasing device according to claim 1, it is characterised in that described connecting seat is in sleeve
Shape is vertically arranged on bottom plate, and the inwall of connecting seat bottom is provided with to be provided with position limiting convex ring, position limiting convex ring and can slide up and down
Pressure pin on the downside of pressure pin, position limiting convex ring is provided with the limiting plate that can be moved up and down in the connecting seat on the downside of position limiting convex ring, connection
Seat top is provided with pretension stage clip provided with the positioning supporting plate being fixedly connected with pressure pin upper end between position limiting convex ring and positioning supporting plate.
4. the satellite and the rocket separation locking releasing device according to claim 1 or 2 or 3, it is characterised in that on described bottom plate
Relative swing rod of the place provided with rectangular frame-shaped with the middle part of locking release swing rod, locking release swing rod is interspersed in swing rod, in
Portion is hinged through rotating shaft with swing rod.
5. the satellite and the rocket separation locking releasing device according to claim 1 or 2 or 3, it is characterised in that described connecting rod
For screw rod, described clamping joint is the horizontal cylinder in screw rod lower end, and the downside of claw upper arm is in coordinate with clamping joint
Arc.
6. the satellite and the rocket separation locking releasing device according to claim 1 or 2 or 3, it is characterised in that on described bottom plate
By the rounded array-like in the center of circle of spill spin block provided with three connecting seats.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710203183.0A CN107054700A (en) | 2017-03-30 | 2017-03-30 | A kind of satellite and the rocket separation locking releasing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710203183.0A CN107054700A (en) | 2017-03-30 | 2017-03-30 | A kind of satellite and the rocket separation locking releasing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107054700A true CN107054700A (en) | 2017-08-18 |
Family
ID=59602996
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710203183.0A Pending CN107054700A (en) | 2017-03-30 | 2017-03-30 | A kind of satellite and the rocket separation locking releasing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107054700A (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107826271A (en) * | 2017-12-07 | 2018-03-23 | 上海宇航***工程研究所 | Jack catchs type satellite and the rocket connection separation mechanism |
| CN108116697A (en) * | 2017-12-08 | 2018-06-05 | 浙江大学 | A kind of spheric satellite separates tripper |
| CN108528739A (en) * | 2018-03-09 | 2018-09-14 | 芜湖翼讯飞行智能装备有限公司 | A kind of quick-disassembly structure for unmanned machine head |
| CN109353549A (en) * | 2018-10-30 | 2019-02-19 | 哈尔滨工业大学 | A kind of big bearer connection relieving mechanism of body bay section |
| CN110239747A (en) * | 2019-05-24 | 2019-09-17 | 南京理工大学 | A kind of point type microsatellite separation tripper |
| CN110239746A (en) * | 2019-05-24 | 2019-09-17 | 南京理工大学 | A kind of hexagon microsatellite separation tripper |
| WO2021143428A1 (en) * | 2020-01-16 | 2021-07-22 | 清华大学 | Electromagnetic locking and releasing mechanism for satellite-rocket separation and electromagnetic locking and releasing method |
| CN113800012A (en) * | 2021-09-30 | 2021-12-17 | 北京中科宇航技术有限公司 | Drag release device and system thereof |
| CN113911405A (en) * | 2021-11-26 | 2022-01-11 | 深圳力合精密装备科技有限公司 | Space repeated locking system |
| CN114353603A (en) * | 2022-01-13 | 2022-04-15 | 北京中科宇航技术有限公司 | Separation unlocking device for non-explosive device star and arrow |
| CN114735250A (en) * | 2022-06-09 | 2022-07-12 | 北京劢亚科技有限公司 | Satellite launching box ejection device |
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Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107826271A (en) * | 2017-12-07 | 2018-03-23 | 上海宇航***工程研究所 | Jack catchs type satellite and the rocket connection separation mechanism |
| CN108116697A (en) * | 2017-12-08 | 2018-06-05 | 浙江大学 | A kind of spheric satellite separates tripper |
| CN108116697B (en) * | 2017-12-08 | 2021-06-15 | 浙江大学 | Spherical satellite separation unlocking device |
| CN108528739A (en) * | 2018-03-09 | 2018-09-14 | 芜湖翼讯飞行智能装备有限公司 | A kind of quick-disassembly structure for unmanned machine head |
| CN109353549A (en) * | 2018-10-30 | 2019-02-19 | 哈尔滨工业大学 | A kind of big bearer connection relieving mechanism of body bay section |
| CN109353549B (en) * | 2018-10-30 | 2021-07-13 | 哈尔滨工业大学 | Large-bearing connection releasing mechanism for missile body cabin |
| CN110239747A (en) * | 2019-05-24 | 2019-09-17 | 南京理工大学 | A kind of point type microsatellite separation tripper |
| CN110239746A (en) * | 2019-05-24 | 2019-09-17 | 南京理工大学 | A kind of hexagon microsatellite separation tripper |
| WO2021143428A1 (en) * | 2020-01-16 | 2021-07-22 | 清华大学 | Electromagnetic locking and releasing mechanism for satellite-rocket separation and electromagnetic locking and releasing method |
| US11597540B2 (en) | 2020-01-16 | 2023-03-07 | Tsinghua University | Electromagnetic lock release mechanism and method for separating satellite from rocket |
| CN113800012A (en) * | 2021-09-30 | 2021-12-17 | 北京中科宇航技术有限公司 | Drag release device and system thereof |
| CN113800012B (en) * | 2021-09-30 | 2023-09-19 | 北京中科宇航技术有限公司 | Drag release device and system thereof |
| CN113911405A (en) * | 2021-11-26 | 2022-01-11 | 深圳力合精密装备科技有限公司 | Space repeated locking system |
| CN113911405B (en) * | 2021-11-26 | 2024-06-11 | 深圳力合精密装备科技有限公司 | Space flight repeated locking system |
| CN114353603A (en) * | 2022-01-13 | 2022-04-15 | 北京中科宇航技术有限公司 | Separation unlocking device for non-explosive device star and arrow |
| CN114353603B (en) * | 2022-01-13 | 2023-11-14 | 北京中科宇航技术有限公司 | Non-initiating explosive device satellite and rocket separation unlocking device |
| CN114735250A (en) * | 2022-06-09 | 2022-07-12 | 北京劢亚科技有限公司 | Satellite launching box ejection device |
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