CN110450987A - Electromagnetic absorption device and preparation method thereof between spacecraft bay section - Google Patents
Electromagnetic absorption device and preparation method thereof between spacecraft bay section Download PDFInfo
- Publication number
- CN110450987A CN110450987A CN201910749319.7A CN201910749319A CN110450987A CN 110450987 A CN110450987 A CN 110450987A CN 201910749319 A CN201910749319 A CN 201910749319A CN 110450987 A CN110450987 A CN 110450987A
- Authority
- CN
- China
- Prior art keywords
- shell
- mandrel
- bay section
- copper coil
- circle copper
- 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
- 238000010521 absorption reaction Methods 0.000 title claims abstract description 55
- 238000002360 preparation method Methods 0.000 title description 4
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 34
- 229910052802 copper Inorganic materials 0.000 claims abstract description 32
- 239000010949 copper Substances 0.000 claims abstract description 32
- 238000005461 lubrication Methods 0.000 claims description 9
- 229920006335 epoxy glue Polymers 0.000 claims description 7
- 239000011248 coating agent Substances 0.000 claims description 6
- 238000000576 coating method Methods 0.000 claims description 6
- 238000003466 welding Methods 0.000 claims description 5
- 238000004519 manufacturing process Methods 0.000 claims description 4
- 239000007787 solid Substances 0.000 claims description 4
- 239000000956 alloy Substances 0.000 claims description 3
- UGKDIUIOSMUOAW-UHFFFAOYSA-N iron nickel Chemical compound [Fe].[Ni] UGKDIUIOSMUOAW-UHFFFAOYSA-N 0.000 claims description 3
- 239000000696 magnetic material Substances 0.000 claims description 3
- 238000007711 solidification Methods 0.000 claims 1
- 230000008023 solidification Effects 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 229920006332 epoxy adhesive Polymers 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 238000001179 sorption measurement Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 229910052742 iron Inorganic materials 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Load-Engaging Elements For Cranes (AREA)
Abstract
The present invention provides the electromagnetic absorption devices between a kind of spacecraft bay section, including magnechuck component and absorption end, the magnechuck component includes shell, mandrel, around circle copper coil and capping, the mandrel is set in shell, it is described around circle copper wire snare on mandrel, the bottom end of the mandrel and the bottom of shell are fixed, the top of the mandrel passes through the centre bore of the capping, it is described to cover described on circle copper coil, the end around circle copper coil retains outgoing cable, the top actuation at the absorption end and the shell.Electromagnetic absorption device between spacecraft bay section of the invention, the big suction that is powered, the small residual suction of power-off have the characteristics that in-orbit can be multiplexed, are lightweight, easy to use, having good applicability and be widely applied range.
Description
Technical field
The present invention relates to spacecraft structure equipment technical fields, and in particular, to the electromagnetism between a kind of spacecraft bay section is inhaled
Adsorption device and preparation method thereof.
Background technique
With the development of space technology, multi cabin configuration spacecraft, in-orbit restructural spacecraft are since its configuration is flexible, mould
The features such as block is strong has gradually obtained widely concern and application increasingly in space industry.It connects-releases between Future Spacecraft bay section
Put device towards in-orbit can be multiplexed, lightweight, easy to useization, modularization direction are developed, existing routine firer connection-unlock dress
It sets, the devices such as docking mechanism are difficult to meet requirements above.
By the retrieval to the prior art, application No. is 201410027585.6 patent of invention disclose it is a kind of novel
Multi satellite separation solution lock release mainly includes bracket, adapter, satellite orbit spreader, connection ring.Adapter and delivery fire
Arrow connection, connection ring can carry out layered arrangement when user needs for providing support to increase carrying number of satellite；Branch
Frame supports satellite orbit spreader for fixed；Satellite orbit spreader is used to carry the connection and unlock separation of satellite.It is one
Kind of structure is simple, low-cost satellite connection and unlock separator.The device, which is unable to satisfy, in-orbit to be multiplexed, lightweight
Deng requirement.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide the electromagnetic absorption devices between a kind of spacecraft bay section
And preparation method thereof.
Electromagnetic absorption device between a kind of spacecraft bay section provided according to the present invention, including magnechuck component and absorption
End, the magnechuck component include shell, mandrel, around circle copper coil and capping, and the mandrel is set in shell, described around circle
Copper wire snare on mandrel, fix by the bottom end of the mandrel and the bottom of shell, and the top of the mandrel passes through the capping
Centre bore, described to cover described on circle copper coil, the end around circle copper coil retains outgoing cable, the absorption
End and the top of the shell are attracted.
Further, the capping, shell, around the mutual gap of circle copper coil using epoxy glue bond.
Further, the one side at the absorption end is circular flat, and the circular flat is the actuation face for adsorbing end, described
The part that the top of shell and the absorption end are attracted is the actuation face of shell, and the actuation face size at the absorption end is slightly larger than institute
State the actuation face size of shell.
Further, the actuation face at the absorption end carries out solid lubrication coating film treatment.
Further, the top surface for being attracted face and being higher than mandrel of the shell.
Further, the shell and mandrel are integrally formed.
Further, the shell, mandrel, absorption end are made of 1J50 iron nickel soft magnetic materials.
Further, the outgoing cable around circle copper coil end passes through the preformed hole of outer casing bottom.
Further, the lateral wall of the shell is equipped with the mounting plate being integrally machined.
The present invention also provides a kind of production methods of the electromagnetic absorption device between spacecraft bay section, include the following steps:
S1, band mandrel integrated casing, absorption end are processed using 1J50 magnetically soft alloy material, it is spare；
S2, using mold coiling around circle copper coil, coil end retains outgoing cable, spare；
S3, absorption end carry out anti-cold welding lubrication coating film treatment, spare；
S4, it will pass through around the outgoing cable of circle copper coil end with the preformed hole on mandrel integrated casing, band mandrel one
It is put into epoxy glue in body type case, will be put into shell around circle copper coil, capping, external pressure is continuously applied to capping until ring
Oxygen adhesive curing is secured.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, the electromagnetic absorption device between spacecraft bay section of the invention, the shell and central mandrel of magnechuck component use
Integrated design, the interior arrangement high density of shell use Wear Characteristics of Epoxy Adhesive knot pressure real around circle copper coil, capping, shell around circle copper coil,
Compact overall structure.
2, the electromagnetic absorption device between spacecraft bay section of the invention adsorbs the actuation for being attracted face size and being greater than shell at end
Face size is capable of the misalignment of axe of two components of effective compensation.
3, the electromagnetic absorption device between spacecraft bay section of the invention, the actuation face for adsorbing end carry out at solid lubrication plated film
Reason can adapt to the lubrication and anti-cold welding requirement of space environment.
4, the electromagnetic absorption device between spacecraft bay section of the invention, the big suction that is powered, the small residual suction of power-off, having can
In-orbit multiplexing, lightweight, it is easy to use the features such as, have and good applicability and be widely applied range.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
The structural schematic diagram of electromagnetic absorption device of the Fig. 1 between spacecraft bay section of the present invention；
The structural schematic diagram of the magnechuck component of electromagnetic absorption device of the Fig. 2 between spacecraft bay section of the present invention；
The structural schematic diagram of the attracting state of electromagnetic absorption device of the Fig. 3 between spacecraft bay section of the present invention；
The working state schematic representation (release conditions) of electromagnetic absorption device of the Fig. 4 between spacecraft bay section of the present invention；
The working state schematic representation (attracting state) of electromagnetic absorption device of the Fig. 5 between spacecraft bay section of the present invention.
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
Electromagnetic absorption device between spacecraft bay section of the invention is the electricity of a kind of big suction that is powered, the small residual suction of power-off
Magnetic adsorption device connects-release field suitable for the repetition between the spacecrafts bay section such as satellite, have in-orbit can be multiplexed, lightweight,
The features such as easy to use, has good applicability and is widely applied range.
Next the present invention is described in further detail.
As shown in Figures 1 to 5, the electromagnetic absorption device between a kind of spacecraft bay section provided by the invention, including electromagnetism are inhaled
Disk component 1 and absorption end 2, magnechuck component 1 include band mandrel integrated casing 101, around circle copper coil 102 and capping 103,
Mandrel 106 is set in shell, and around 102 sets of circle copper coil on mandrel, the top of mandrel passes through the centre bore of capping 103, capping
103 cover on circle copper coil 102, retain outgoing cable 105 around the end of circle copper coil 102, the connection of outgoing cable 105 is electrically connected
It connects device 108 and adsorbs end 2 and the top actuation with mandrel integrated casing 101.
Capping 103, shell 101 are bonded around the mutual gap of circle copper coil 102 using epoxy glue 104.Magnechuck
Shell and central mandrel use integrated design, and arrangement high density is around circle copper coil in shell, end cap, shell, around circle copper coil
Real, the compact overall structure using Wear Characteristics of Epoxy Adhesive knot pressure.
The one side for adsorbing end 2 is circular flat, and circular flat is the actuation face for adsorbing end, band mandrel integrated casing 101
Top and absorption end be attracted part be shell actuation face, absorption end 2 be attracted face size be slightly larger than shell actuation face
Size is capable of the misalignment of axe of two components of effective compensation.
Work is substituted using the 1J50 iron nickel soft magnetic materials with more low-coercivity with mandrel integrated casing 101, absorption end 2
Industry often uses the manufacture of electromagnetic pure iron material.
The actuation face for adsorbing end 2 carries out solid lubrication coating film treatment, and the lubrication and anti-cold welding that can adapt to space environment are wanted
It asks.
The top surface of mandrel 106 is lower than the actuation face outer ring 1011 (annular outer ring) of shell 101, specially the top surface ratio of mandrel
Actuation face outer ring 1011 probably low 0.1mm or so, i.e., small―gap suture is recessed or small distance is recessed.The power-off of the present apparatus can be effectively reduced
Residual suction.
Lateral wall with mandrel integrated casing 101 is equipped with mounting plate 107.
The present invention also provides a kind of production methods of the electromagnetic absorption device between spacecraft bay section, include the following steps:
S1, band mandrel integrated casing, absorption end are processed using 1J50 magnetically soft alloy material, it is spare；
S2, using mold coiling around circle copper coil, coil end retains outgoing cable, spare；
S3, absorption end carry out anti-cold welding lubrication coating film treatment, spare；
S4, it will pass through around the outgoing cable of circle copper coil end with the preformed hole on mandrel integrated casing, band mandrel one
It is put into epoxy glue in body type case, will be put into shell around circle copper coil, capping, external pressure is continuously applied to capping until ring
Oxygen adhesive curing is secured.
In the description of the present application, it is to be understood that term " on ", "front", "rear", "left", "right", " is erected at "lower"
Directly ", the orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is orientation based on the figure or position
Relationship is set, description the application is merely for convenience of and simplifies description, rather than the device or element of indication or suggestion meaning are necessary
It with specific orientation, is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (10)
1. the electromagnetic absorption device between a kind of spacecraft bay section, which is characterized in that described including magnechuck component and absorption end
Magnechuck component includes shell, mandrel, around circle copper coil and capping, and the mandrel is set in shell, described around circle copper coil
It covering on mandrel, the bottom end of the mandrel and the bottom of shell are fixed, and the top of the mandrel passes through the centre bore of the capping,
Described to cover described on circle copper coil, the end around circle copper coil retains outgoing cable, the absorption end and institute
The top for stating shell is attracted.
2. the electromagnetic absorption device between spacecraft bay section according to claim 1, which is characterized in that the capping, shell,
The gap mutual around circle copper coil is bonded using epoxy glue.
3. the electromagnetic absorption device between spacecraft bay section according to claim 1, which is characterized in that the one of the absorption end
Face is circular flat, and the circular flat is the actuation face for adsorbing end, the portion that the top of the shell and the absorption end are attracted
It is divided into the actuation face of shell, the actuation face size for being attracted face size and being greater than the shell at the absorption end.
4. the electromagnetic absorption device between spacecraft bay section according to claim 3, which is characterized in that the suction at the absorption end
Conjunction face carries out solid lubrication coating film treatment.
5. the electromagnetic absorption device between spacecraft bay section according to claim 3, which is characterized in that the actuation of the shell
Face is higher than the top surface of mandrel.
6. the electromagnetic absorption device between spacecraft bay section according to claim 1, which is characterized in that the shell and mandrel
It is integrally formed.
7. the electromagnetic absorption device between spacecraft bay section according to claim 1, which is characterized in that the shell, mandrel,
Absorption end is made of 1J50 iron nickel soft magnetic materials.
8. the electromagnetic absorption device between spacecraft bay section according to claim 1, which is characterized in that described around circle copper coil
The outgoing cable of end passes through the preformed hole of outer casing bottom.
9. the electromagnetic absorption device between spacecraft bay section according to claim 1, which is characterized in that the outside of the shell
Wall is equipped with the mounting plate being integrally machined.
10. a kind of production method of electromagnetic absorption device as described in claim 1, which comprises the steps of:
S1, band mandrel integrated casing, absorption end are processed using magnetically soft alloy material, it is spare；
S2, using mold coiling around circle copper coil, coil end retains outgoing cable, spare；
S3, absorption end carry out anti-cold welding lubrication coating film treatment, spare；
S4, it will pass through around the outgoing cable of circle copper coil end with the preformed hole on mandrel integrated casing, band mandrel integral type
It is put into epoxy glue in shell, will be put into shell around circle copper coil, capping, external pressure is continuously applied to capping until epoxy glue
Solidification is secured.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910749319.7A CN110450987A (en) | 2019-08-14 | 2019-08-14 | Electromagnetic absorption device and preparation method thereof between spacecraft bay section |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910749319.7A CN110450987A (en) | 2019-08-14 | 2019-08-14 | Electromagnetic absorption device and preparation method thereof between spacecraft bay section |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110450987A true CN110450987A (en) | 2019-11-15 |
Family
ID=68486434
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910749319.7A Pending CN110450987A (en) | 2019-08-14 | 2019-08-14 | Electromagnetic absorption device and preparation method thereof between spacecraft bay section |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110450987A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111086657A (en) * | 2019-12-16 | 2020-05-01 | 上海卫星工程研究所 | Method, system and medium for connection between small satellite cabins |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105697581A (en) * | 2016-04-16 | 2016-06-22 | 安徽昊方机电股份有限公司 | Electromagnetic clutch of automotive air conditioner |
| CN106300881A (en) * | 2015-06-01 | 2017-01-04 | 北京卫星环境工程研究所 | Spacecraft separator based on electromagnetic force |
| CN108791966A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | It is a kind of can in-orbit multiplexing the intersegmental connection of spacecraft module-release combination unit |
| US20190023419A1 (en) * | 2017-07-21 | 2019-01-24 | The Aerospace Corporation | Interlocking, reconfigurable, reconstitutable, reformable cell-based system with nested ring structures |
| CN109264034A (en) * | 2018-08-14 | 2019-01-25 | 北京航空航天大学 | A kind of spacecraft electromagnetism cross convolution butt-joint locking device |
| CN109466808A (en) * | 2018-12-14 | 2019-03-15 | 哈尔滨工业大学 | A kind of electromagnetism docking facilities and method based on linear motor |
-
2019
- 2019-08-14 CN CN201910749319.7A patent/CN110450987A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106300881A (en) * | 2015-06-01 | 2017-01-04 | 北京卫星环境工程研究所 | Spacecraft separator based on electromagnetic force |
| CN105697581A (en) * | 2016-04-16 | 2016-06-22 | 安徽昊方机电股份有限公司 | Electromagnetic clutch of automotive air conditioner |
| US20190023419A1 (en) * | 2017-07-21 | 2019-01-24 | The Aerospace Corporation | Interlocking, reconfigurable, reconstitutable, reformable cell-based system with nested ring structures |
| CN108791966A (en) * | 2018-06-15 | 2018-11-13 | 上海卫星工程研究所 | It is a kind of can in-orbit multiplexing the intersegmental connection of spacecraft module-release combination unit |
| CN109264034A (en) * | 2018-08-14 | 2019-01-25 | 北京航空航天大学 | A kind of spacecraft electromagnetism cross convolution butt-joint locking device |
| CN109466808A (en) * | 2018-12-14 | 2019-03-15 | 哈尔滨工业大学 | A kind of electromagnetism docking facilities and method based on linear motor |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111086657A (en) * | 2019-12-16 | 2020-05-01 | 上海卫星工程研究所 | Method, system and medium for connection between small satellite cabins |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20191115 |