CN106586039B - A kind of anti-error trapping docking facilities in space - Google Patents
A kind of anti-error trapping docking facilities in space Download PDFInfo
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- CN106586039B CN106586039B CN201611155485.7A CN201611155485A CN106586039B CN 106586039 B CN106586039 B CN 106586039B CN 201611155485 A CN201611155485 A CN 201611155485A CN 106586039 B CN106586039 B CN 106586039B
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- extension assembly
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- bar
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- 238000003032 molecular docking Methods 0.000 title claims abstract description 40
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims abstract description 21
- 238000009434 installation Methods 0.000 claims abstract description 4
- 230000000694 effects Effects 0.000 claims description 3
- 238000007373 indentation Methods 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims 1
- 230000008878 coupling Effects 0.000 abstract 1
- 238000010168 coupling process Methods 0.000 abstract 1
- 238000005859 coupling reaction Methods 0.000 abstract 1
- 230000002035 prolonged effect Effects 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000004064 recycling Methods 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
- B64G1/646—Docking or rendezvous systems
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Geophysics And Detection Of Objects (AREA)
Abstract
A kind of anti-error trapping docking facilities in space, are related to satellite capture and the field of docking；Satellite, satellite base assembly, level-one extension assembly, second level extension assembly, three-level extension assembly and capture bar；Wherein, satellite base assembly is fixedly mounted on the outer surface of satellite one end；Level-one extension assembly is fixedly mounted on the inside of satellite base assembly；Second level extension assembly is fixedly mounted on the inside of level-one extension assembly；Three-level extension assembly is fixedly mounted on the inside of second level extension assembly；Capture bar is fixedly mounted on the inside of three-level extension assembly；Its Satellite pedestal is ring structure, and the both ends of satellite pedestal are provided with cylindrical groove；2 line packets are respectively and fixedly installed in cylindrical groove；Female bar is axially fixed the inside that installation is wrapped online；Female bar spring is axially mounted to the inside of female bar；The present invention enormously simplifies the demand of satellites coupling, improves efficiency, and allows the satellite rapid abutting joint within the scope of certain error and full cone angle.
Description
Technical field
The present invention relates to a kind of satellite capture and the field of docking, especially a kind of anti-error trapping docking facilities in space.
Background technique
Docking between existing satellite or aircraft needs to carry out complicated posture tune using optical instrument and sensor etc.
It is whole, so as to the small error docking between aircraft.Structure is relatively complicated, and occupancy volume weight is larger, and it is small to be unsatisfactory for satellite
The application demand of type.
Summary of the invention
It is an object of the invention to overcome the above-mentioned deficiency of the prior art, a kind of anti-error trapping in space is provided to tipping
It sets, enormously simplifies the docking demand of satellite, improve efficiency, allow the satellite within the scope of certain error and full cone angle quickly right
It connects.
Above-mentioned purpose of the invention is achieved by following technical solution:
A kind of anti-error trapping docking facilities in space, including satellite, satellite base assembly, level-one extension assembly, second level are prolonged
Stretch component, three-level extension assembly and capture bar；Wherein, satellite base assembly is fixedly mounted on the outer surface of satellite one end；Level-one
Extension assembly is fixedly mounted on the inside of satellite base assembly；Second level extension assembly is fixedly mounted on the interior of level-one extension assembly
Portion；Three-level extension assembly is fixedly mounted on the inside of second level extension assembly；Capture bar is fixedly mounted on the interior of three-level extension assembly
Portion.
In a kind of above-mentioned anti-error trapping docking facilities in space, the level-one extension assembly, second level extension assembly, three
Grade extension assembly is hollow cylindrical structure, and capture bar is cylindrical structure；Level-one extension assembly is wrapped in second level extension assembly
Outer wall；Second level extension assembly is wrapped in the outer wall of three-level extension assembly；Three-level extension assembly is wrapped in the outer wall of capture bar；One
Grade extension assembly can be axially extending and be collapsible into satellite base assembly；Second level extension assembly can axially extending and retraction level-one
Extension assembly；Three-level extension assembly can axially extending and retraction second level extension assembly；Capturing bar can axially extending and retraction
Three-level extension assembly.
In a kind of above-mentioned anti-error trapping docking facilities in space, when level-one extension assembly, second level extension assembly, three-level are prolonged
Component and capture bar are stretched when being indentation state, level-one extension assembly, second level extension assembly, three-level extension assembly and capture bar
End face is generally aligned in the same plane with satellite base assembly.
In a kind of above-mentioned anti-error trapping docking facilities in space, the satellite base assembly includes satellite pedestal, 2
Line packet, female bar and female bar spring；Its Satellite pedestal is ring structure, and the both ends of satellite pedestal are provided with cylindrical groove；2 lines
Packet is respectively and fixedly installed in cylindrical groove；Female bar is axially fixed the inside that installation is wrapped online；Female bar spring is along axially mounted
In the inside of female bar.
In a kind of above-mentioned anti-error trapping docking facilities in space, 2 line packets are hollow cylindrical structure, satellite
The cylindrical groove inner wall of pedestal wraps up the outer wall wrapped online.
In a kind of above-mentioned anti-error trapping docking facilities in space, female bar is hollow cylindrical structure；Line packet
Inner wall is wrapped in the outer wall of female bar, and female bar spring is fixedly mounted in the through-hole of female bar.
In a kind of above-mentioned anti-error trapping docking facilities in space, level-one extension assembly, second level extension assembly and three-level are prolonged
Stretch that modular construction form is identical as satellite base assembly, inside is the structure of rod piece and spring cooperation.
In a kind of above-mentioned anti-error trapping docking facilities in space, the line of 2 line packets is by annular satellite pedestal
Heart point.
In a kind of above-mentioned anti-error trapping docking facilities in space, satellite capture docking operation are as follows: when satellite is undocked, one
Grade extension assembly, second level extension assembly, three-level extension assembly and capture bar are shunk in the inside of satellite base assembly, female bar spring
In compressive state；When two satellites are up to predetermined docking distance and docked, level-one extension assembly, second level extension assembly,
Three-level extension assembly and capture bar are fully extended under spring force effect；Then the line packet in satellite base assembly is powered,
It realizes and becomes level-one extension assembly, second level extension assembly, three-level extension assembly and capture bar with magnetic electromagnet；Two
Polarity at the top of intersatellite capture bar is mutually attracted on the contrary, realizes the capture docking of two satellites.
In a kind of above-mentioned anti-error trapping docking facilities in space, the series of the extension assembly according to actually dock away from
From can be increased or be reduced.
The invention has the following advantages over the prior art:
(1) arresting structure of the present invention due to using electromagnetic drive type guide bar, may be implemented oneself of remote satellite
Main capture, the engagement range compared to traditional approach greatly improve；
(2) present invention has larger improvement in terms of allowable error docking, can permit satellite drift in a big way
In the case where, complete the acquisition procedure of satellite；
(3) what the present invention took is to capture and dock integral structure, (is divided into two moulds of capture and docking compared to traditional structure
Block), volume and space are saved, docking complexity is reduced.
Detailed description of the invention
Fig. 1 is outline drawing of the invention；
Fig. 2 is schematic diagram of internal structure of the invention；
Fig. 3 is satellite base assembly structure chart；
Fig. 4 is initial makeup location schematic diagram of the present invention；
Fig. 5 is working state schematic representation of the present invention.
Specific embodiment
The present invention is described in further detail in the following with reference to the drawings and specific embodiments:
It is as shown in Figure 1 outline drawing, as seen from the figure, a kind of anti-error trapping docking facilities in space, including satellite 1, satellite
Base assembly 2, level-one extension assembly 3, second level extension assembly 4, three-level extension assembly 5 and capture bar 6；Wherein, satellite pedestal group
Part 2 is fixedly mounted on the outer surface of 1 one end of satellite；Level-one extension assembly 3 is fixedly mounted on the inside of satellite base assembly 2；Two
Grade extension assembly 4 is fixedly mounted on the inside of level-one extension assembly 3；Three-level extension assembly 5 is fixedly mounted on second level extension assembly 4
Inside；Capture bar 6 is fixedly mounted on the inside of three-level extension assembly 5.The series of the extension assembly is according to actually docking
Distance can be increased or be reduced.
It is illustrated in figure 2 schematic diagram of internal structure, as seen from the figure, level-one extension assembly 3, second level extension assembly 4, three-level are prolonged
Stretching component 5 is hollow cylindrical structure, and capture bar 6 is cylindrical structure；Level-one extension assembly 3 is wrapped in second level extension assembly 4
Outer wall；Second level extension assembly 4 is wrapped in the outer wall of three-level extension assembly 5；Three-level extension assembly 5 is wrapped in the outer of capture bar 6
Wall；Level-one extension assembly 3 can be axially extending and be collapsible into satellite base assembly 2；Second level extension assembly 4 can it is axially extending and
It is retracted level-one extension assembly 3；Three-level extension assembly 5 can axially extending and retraction second level extension assembly 4；Capturing bar 6 can be along axis
To extended and retracted three-level extension assembly 5.
When level-one extension assembly 3, second level extension assembly 4, three-level extension assembly 5 and capture bar 6 are indentation state, one
Grade extension assembly 3, second level extension assembly 4, three-level extension assembly 5 and the end face for capturing bar 6 and satellite base assembly 2 are positioned at same
Plane.
It is illustrated in figure 3 satellite base assembly structure chart, as seen from the figure, satellite base assembly 2 includes satellite pedestal 7,2
Line packet 8, female bar 9 and female bar spring 10；Its Satellite pedestal 7 is ring structure, and the both ends of satellite pedestal 7 are provided with cylinder
Slot；2 line packets 8 are respectively and fixedly installed in cylindrical groove；Female bar 9 is axially fixed the inside of the online packet 8 of installation；Female bar spring
10 are axially mounted to the inside of female bar 9.
Wherein, 2 line packets 8 are hollow cylindrical structure, and the cylindrical groove inner wall of satellite pedestal 7 wraps up the outer of online packet 8
Wall, and the line of 2 line packets 8 is by the central point of annular satellite pedestal 7.
Female bar 9 is hollow cylindrical structure；The inner wall of line packet 8 is wrapped in the outer wall of female bar 9, and female bar spring 10 is fixedly mounted
In the through-hole of female bar 9.
Level-one extension assembly 3, second level extension assembly 4,5 structure type of three-level extension assembly are identical as satellite base assembly 2,
Inside is the structure of rod piece and spring cooperation.
Satellite capture docking operation are as follows: be illustrated in figure 4 initial makeup location schematic diagram, as seen from the figure, satellite is undocked
When, level-one extension assembly 3, second level extension assembly 4, three-level extension assembly 5 and capture bar 6 are shunk in satellite base assembly 2
Portion, female bar spring 10 are in compressive state；
It is illustrated in figure 5 working state schematic representation, as seen from the figure, when two satellites up to predetermined docking distance and are docked
When, level-one extension assembly 3, second level extension assembly 4, three-level extension assembly 5 and capture bar 6 are stretched completely under spring force effect
Out；Then the line packet 8 in satellite base assembly 2 is powered, level-one extension assembly 3, second level extension assembly 4, three-level are prolonged in realization
It stretches component 5 and capture bar 6 becomes with magnetic electromagnet；Polarity at the top of two intersatellite capture bars 6 is mutual on the contrary
It is attracted, realizes the capture docking of two satellites.
After the completion of the capture bar 6 of two satellites is contacted and is attracted, continue to be powered, according to minimum energy principle, bar group can be produced
The active force of raw recycling, and then the distance between two satellites of realization are close, until satellite reaches locked position, it is complete by locking mechanism
At locking function.
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (7)
1. a kind of anti-error trapping docking facilities in space, it is characterised in that: including satellite (1), satellite base assembly (2), level-one
Extension assembly (3), second level extension assembly (4), three-level extension assembly (5) and capture bar (6)；Wherein, satellite base assembly (2) is solid
Dingan County is mounted in the outer surface of satellite (1) one end；Level-one extension assembly (3) is fixedly mounted on the inside of satellite base assembly (2)；Two
Grade extension assembly (4) is fixedly mounted on the inside of level-one extension assembly (3)；Three-level extension assembly (5) is fixedly mounted on second level and prolongs
Stretch the inside of component (4)；Capture bar (6) is fixedly mounted on the inside of three-level extension assembly (5)；
The level-one extension assembly (3), second level extension assembly (4), three-level extension assembly (5) are hollow cylindrical structure, are caught
Obtaining bar (6) is cylindrical structure；Level-one extension assembly (3) is wrapped in the outer wall of second level extension assembly (4)；Second level extension assembly
(4) it is wrapped in the outer wall of three-level extension assembly (5)；Three-level extension assembly (5) is wrapped in the outer wall of capture bar (6)；Level-one extends
Component (3) can be axially extending and be collapsible into satellite base assembly (2)；Second level extension assembly (4) can axially extending and retraction
Level-one extension assembly (3)；Three-level extension assembly (5) can axially extending and retraction second level extension assembly (4)；Capturing bar (6) can
Axially extending and retraction three-level extension assembly (5)；
When level-one extension assembly (3), second level extension assembly (4), three-level extension assembly (5) and capture bar (6) are indentation state
When, level-one extension assembly (3), second level extension assembly (4), three-level extension assembly (5) and capture bar (6) end face and satellite pedestal
Component (2) is generally aligned in the same plane；
The satellite base assembly (2) includes satellite pedestal (7), 2 line packets (8), female bar (9) and female bar spring (10)；Its
Satellite pedestal (7) is ring structure, and the both ends of satellite pedestal (7) are provided with cylindrical groove；2 line packets (8) are fixed respectively to pacify
In cylindrical groove；Female bar (9) is axially fixed the inside of the online packet (8) of installation；Female bar spring (10) is axially mounted to
The inside of female bar (9).
2. the anti-error trapping docking facilities in a kind of space according to claim 1, it is characterised in that: 2 line packets
It (8) is hollow cylindrical structure, the outer wall of the online packet (8) of cylindrical groove inner wall package of satellite pedestal (7).
3. the anti-error trapping docking facilities in a kind of space according to claim 2, it is characterised in that: female bar (9)
For hollow cylindrical structure；The inner wall of line packet (8) is wrapped in the outer wall of female bar (9), and female bar spring (10) is fixedly mounted on female bar
(9) in through-hole.
4. the anti-error trapping docking facilities in a kind of space according to claim 3, it is characterised in that: level-one extension assembly
(3), second level extension assembly (4) and three-level extension assembly (5) structure type are identical as satellite base assembly (2), and inside is bar
The structure of part and spring cooperation.
5. the anti-error trapping docking facilities in a kind of space according to claim 4, it is characterised in that: the company of 2 line packets (8)
Line passes through the central point of annular satellite pedestal (7).
6. a kind of anti-error trapping docking facilities in space described in one of -5 according to claim 1, it is characterised in that: satellite capture
Docking operation are as follows: when satellite is undocked, level-one extension assembly (3), second level extension assembly (4), three-level extension assembly (5) and capture
Bar (6) is shunk in the inside of satellite base assembly (2), and female bar spring (10) is in compressive state；When two satellites are up to predetermined pair
When connecing distance and being docked, level-one extension assembly (3), second level extension assembly (4), three-level extension assembly (5) and capture bar (6)
It is fully extended under spring force effect；Then the line packet (8) in satellite base assembly (2) is powered, realization extends level-one
Component (3), second level extension assembly (4), three-level extension assembly (5) and capture bar (6) become with magnetic electromagnet；Two are defended
Polarity at the top of capture bar (6) between star is mutually attracted on the contrary, realizes the capture docking of two satellites.
7. the anti-error trapping docking facilities in a kind of space according to claim 6, it is characterised in that: the extension assembly
Series can be increased or be reduced according to actually docking distance.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611155485.7A CN106586039B (en) | 2016-12-14 | 2016-12-14 | A kind of anti-error trapping docking facilities in space |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611155485.7A CN106586039B (en) | 2016-12-14 | 2016-12-14 | A kind of anti-error trapping docking facilities in space |
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| Publication Number | Publication Date |
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| CN106586039A CN106586039A (en) | 2017-04-26 |
| CN106586039B true CN106586039B (en) | 2019-07-09 |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108213898A (en) * | 2018-01-12 | 2018-06-29 | 中国科学院长春光学精密机械与物理研究所 | A kind of in-orbit assembling docking facilities |
| CN109398767B (en) * | 2018-12-14 | 2021-07-27 | 哈尔滨工业大学 | Electromagnetic docking device and method based on high-speed motor |
| CN113738895A (en) * | 2021-10-11 | 2021-12-03 | 东光阀门(温州)有限公司 | Five-eccentric butterfly valve and air tightness detection device thereof |
| CN113682485B (en) * | 2021-10-20 | 2022-01-25 | 四川迅联达智能科技有限公司 | Positioning method of precise positioning device of aircraft |
| CN114212281B (en) * | 2021-12-10 | 2023-04-18 | 哈尔滨工业大学 | Electromagnetic-triggered repeated connection and separation release device for primary and secondary satellites and working method of electromagnetic-triggered repeated connection and separation release device |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4381092A (en) * | 1981-05-01 | 1983-04-26 | Martin Marietta Corporation | Magnetic docking probe for soft docking of space vehicles |
| JP2738368B2 (en) * | 1995-09-29 | 1998-04-08 | 日本電気株式会社 | Telescopic device |
| CN100475651C (en) * | 2007-04-19 | 2009-04-08 | 上海交通大学 | Awl-rod type butt and releasing gear for spacing micro-nano star station |
| US8979034B2 (en) * | 2011-12-06 | 2015-03-17 | Altius Space Machines | Sticky boom non-cooperative capture device |
| CN103407586B (en) * | 2013-08-30 | 2016-04-20 | 中国人民解放军国防科学技术大学 | Electromagnetic butt joint system |
| CN104149992B (en) * | 2014-08-22 | 2016-05-25 | 哈尔滨工业大学 | Capture mechanism and multistage leading screw noncooperative target docking mechanism |
| CN104494846B (en) * | 2014-12-16 | 2016-05-04 | 中国空间技术研究院 | A kind of general arresting agency of weak shock that is applicable to high rail satellite |
| CN105460239B (en) * | 2015-11-30 | 2018-04-10 | 上海宇航系统工程研究所 | A kind of retractor device with pooling feature |
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