CN109969429A - Changeover mechanism - Google Patents
Changeover mechanism Download PDFInfo
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- CN109969429A CN109969429A CN201910113123.9A CN201910113123A CN109969429A CN 109969429 A CN109969429 A CN 109969429A CN 201910113123 A CN201910113123 A CN 201910113123A CN 109969429 A CN109969429 A CN 109969429A
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- China
- Prior art keywords
- substrate
- locking
- changeover mechanism
- single machine
- machine module
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
- Manipulator (AREA)
Abstract
Changeover mechanism of the present invention, comprising: shell, shell are hollow structure open at one end；The opening of shell is arranged in substrate, substrate, and shell and substrate form intelligent board main body, material-putting space are equipped in intelligent board main body；Interface, interface are disposed on the substrate；Electronic bolt hole, electronic bolt hole are disposed on the substrate；Positioning mechanism, positioning mechanism are disposed on the substrate.It is opposite with the prior art, the present invention have the advantage that due to single machine module and satellite it is mechanical, electrical, thermal connection relationship is complicated, is typically only capable to carry out the assembly of single machine module and satellite platform on ground, can not be directly assembled on satellite by in-orbit plug.A kind of changeover mechanism towards the in-orbit replacement of single machine module provided by the present invention, by the in-orbit replacement problem of single machine module, it is converted into the replacement problem of changeover mechanism and healthy single machine assembly, the in-orbit direct assembly of single machine module is avoided, conducive to the Project Realization of the in-orbit replacement of single machine module.
Description
Technical field
The present invention relates to a kind of mechanical structure, specially a kind of changeover mechanism towards the in-orbit replacement of single machine module.
Background technique
The lifetime of satellite in orbit is limited, when fuel consumption totally or system breaks down, the task performance of satellite will
It substantially reduces, or even is unable to complete basic task object, bring huge economic loss.The in-orbit replacement of effective single machine module
Task can carry out fuel adding, system maintenance and troubleshooting to satellite, be to ensure satellite reliability service, reduce failure damage
Lose, extend a kind of important means of the lifetime of satellite.
In order to adapt to the replacement demand of a variety of single machine modules, usually require that the method for the in-orbit replacement of satellite single machine module should
With stronger versatility, it can satisfy the in-orbit replacement demand of multiple types single machine module.Further, since current in-orbit clothes
Business operation is mostly based on space manipulator completion, it is desirable that the replacement of single machine module should be convenient for the operation of mechanical arm.It is defended in tradition
During star platform is developed, since single machine module and the mechanical, electrical of satellite, thermal connection relationship are complicated, it is typically only capable to carry out single machine on ground
The assembly of module and satellite platform, once assembly terminates, even if being difficult to complete to dismantle ground, therefore when satellite single machine occurs
Failure, when needing replacing, healthy single machine module can not be directly assembled on satellite by simple operations such as in-orbit plugs.Cause
This, whether single machine module replacing technology has versatility, whether is easy to spatial operation, whether can ensure single machine module and satellite
Platform is reliably connected, and will directly influence the success or not of satellite maintainable technology on-orbit task.Currently, single machine module is in-orbit autonomous
Replacement has become technical problem, constrains the engineering development of satellite maintainable technology on-orbit technology.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of changeover mechanisms.
In order to achieve the above object of the invention, changeover mechanism of the present invention, comprising: shell, the shell are in open at one end
Hollow structure；The opening of the shell is arranged in substrate, the substrate, and the shell and the substrate form intelligent board master
Body is equipped with material-putting space in the intelligent board main body；Interface, the interface setting is on the substrate；Electronic bolt hole,
The electronic bolt hole setting is on the substrate；Positioning mechanism, the positioning mechanism setting is on the substrate.
Preferably, the positioning mechanism includes the first positioning component and the second positioning component.
Preferably, first positioning component includes at least a guide bar.
Preferably, second positioning component includes at least a positioning pin.
Preferably, it is equipped with retaining mechanism on the substrate, the retaining mechanism includes:
Driving gear, the driving gear are arranged in the material-putting space, and driving motor is fixedly installed in the base
On plate, the driving gear is connect with driving motor, is driven and is rotated by driving motor；
Driven gear, the driven gear are arranged in the material-putting space, pass through straight tooth column with the driving gear
The mode of external toothing is driven, and the driven gear is fixedly mounted on the transmission shaft；
Transmission shaft, the transmission shaft are arranged in the substrate, and one end of the transmission shaft is connect with the driven gear；
Locking switch, the locking switch setting on the substrate, is equipped with locking member in the locking switch, described
Locking member is connect with the other end of the transmission shaft.
Preferably, the quantity of the driven gear and the locking switch is two.
Preferably, the locking switch includes:
Retaining ring, on the substrate, the center of the retaining ring is arranged in the locking member for the locking switch setting
In hole；
Locking assembly, the locking are arranged in the retaining ring.
Preferably, the quantity of the locking assembly is two groups.
Preferably, the locking assembly includes:
Locking pin, the locking pin are arranged in the retaining ring, and the locking pin stretches out or withdraw retaining ring, it is corresponding into
Enter or exit the pin hole on assembly mounting plate, completes the locking and unlocking of assembly and outer mounting structure；
Spring, the spring are set on the outside of the locking pin.
It is equipped with blasting bolt hole on the substrate.
Opposite with the prior art, the present invention has the advantage that
(1) due to single machine module and satellite it is mechanical, electrical, thermal connection relationship is complicated, is typically only capable to carry out single machine mould on ground
The assembly of block and satellite platform can not be directly assembled on satellite by in-orbit plug.One kind provided by the present invention is towards list
The in-orbit replacement problem of single machine module is converted changeover mechanism and healthy single machine mould by the changeover mechanism of the in-orbit replacement of machine module
The replacement problem of block assembly avoids the in-orbit direct assembly of single machine module, real conducive to the engineering of the in-orbit replacement of single machine module
It is existing.
(2) since single machine module individual difference is larger, be difficult to the interface of satellite platform it is unified, provided by the present invention one
Changeover mechanism of the kind towards the in-orbit replacement of single machine module, healthy single machine module to be replaced are solid with the changeover mechanism on ground
Company is assembled into assembly, and the changeover mechanism and satellite platform are all made of mechanical interfaces and the marks such as standardized mechanical interlocking switch
The electrical interface of standardization can meet the replacement demand of a variety of single machine modules, simplify the design of the in-orbit more alias of satellite platform.
(3) a kind of changeover mechanism towards the in-orbit replacement of single machine module provided by the present invention, passes through coarse positioning guide bar
The coarse positioning and fine positioning of replaceable module are respectively completed with fine positioning pin.Coarse positioning guide hole on coarse positioning guide bar and platform
Cooperation increases module capture nargin, reduces and manipulate required precision to mechanical arm；Fine positioning pin is then further on this basis
Improve module installation accuracy.
(4) mechanical interface designed by the present invention can be realized the locking of the dual mechanical between replaceable module and platform,
Respectively electronic bolt locking and mechanical switch locking, increase the reliability of mechanical connection.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature mesh of the invention
And advantage will become more apparent upon.
Fig. 1 is a kind of structural schematic diagram one of the changeover mechanism towards the in-orbit replacement of single machine module of the embodiment of the present invention；
Fig. 2 is a kind of structural schematic diagram two of the changeover mechanism towards the in-orbit replacement of single machine module of the embodiment of the present invention；
Fig. 3 is a kind of application schematic diagram of the changeover mechanism towards the in-orbit replacement of single machine module of the embodiment of the present invention；
Fig. 4 is that mechanical interlocking switchs work in a kind of changeover mechanism towards the in-orbit replacement of single machine module of the embodiment of the present invention
The schematic diagram of principle；
Fig. 5 is that mechanical interlocking switch synchronizes in a kind of changeover mechanism towards the in-orbit replacement of single machine module of the embodiment of the present invention
The schematic diagram of control.
In figure:
1- shell 2- substrate 3- interface
The electronic bolt hole 5- guide bar 6- positioning pin of 4-
7- driving gear 8- driven gear 9- transmission shaft
10- retaining ring 11- locking pin 12- spring
13- blasting bolt hole 14- locking member
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.
As shown in fig. 1~fig. 5, the present invention provides a kind of changeover mechanisms towards the in-orbit replacement of single machine module, including shell
Body 1 and substrate 2.Blasting bolt hole 13, blasting bolt hole 13 is for installing blasting bolt；Electronic bolt hole 4, electronic bolt hole 4
For with actively locked on platform electronic bolt match realization lock for the first time；Coarse positioning guide bar 5, coarse positioning guide bar 5 guide
Coarse alignment during robotic arm manipulation；Fine positioning pin 6, fine positioning pin 6 are that further essence is fixed on the basis of coarse positioning guiding
Position, guiding satellite platform and changeover mechanism precisely align；Electrical interface 3, electrical interface 3 are 60 needle jack redundant interfaces 3, grouping
Corresponding supply lines, data/address bus, direct instruction line, remote temperature sensing line etc. select wherein any amount according to module actual demand
Contact pin；Driven gear 8, driving gear 7, mechanical interlocking switch, driving gear 7 drive driven gear 8 to rotate, and driven gear 8 connects
It connects on transmission shaft 9, driven gear 8 and mechanical interlocking switch shaft are connected, by controlling the positive and negative rotation of driving gear 7, mechanical lock
The repeatable locking of switch for locking or unlock；Substrate 2,2 front installation coarse positioning guide bar 5 of substrate, fine positioning pin 6, electrical interface 3 and machine
Tool locking switch etc., 2 interlayer of substrate install driving gear 7 and driven gear 8, and single machine module is installed at 2 back side of substrate.
Healthy single machine module to be replaced has been connected on ground is assembled to the back side of changeover mechanism substrate 2.Work as fault satellites
When platform needs in-orbit replacement single machine module, the assembly of changeover mechanism and healthy single machine module will be in the operation of space manipulator
Under, by coarse positioning guide bar 5 and fine positioning pin 6, guide precisely aligning for assembly and satellite platform.It is opened by mechanical interlocking
It closes, assembly and satellite platform repeat locking or unlock；In the locked condition, assembly and satellite platform pass through electrical interface 3
Energy transmission and information exchange are carried out, ensures the normal operation of healthy single machine module.
Mechanical interlocking switch, comprising: lock body, oval locking member 14 (being arranged in retaining ring 10), 2 groups of locking pins 11
Match sleeve spring 12 with 2 groups of locking pins 11, spring 12 is in pressured state always.Ellipse of revolution shape locking member 14, makes oval lock
The major semiaxis of tight part 14 is vertical with 11 axis of locking pin, realizes the unlock of mechanical interlocking switch；Continue ellipse of revolution shape locking member
14 90 degree of rotations, keep the major semiaxis of oval locking member 14 parallel with 11 axis of locking pin, so that locking pin 11 matches sleeve spring 12
Further compression, selector pin stroke, locking pin 11 enter pin hole, realize the locking of mechanical interlocking switch.
In order to realize the synchronously control of mechanical interlocking switch, driven gear 8 and mechanical interlocking switch shaft are connected, by driving tooth
Wheel 7 drives driven gear 8 to rotate, by controlling the positive and negative rotation of driving gear 7, to realize the repeatable lock of mechanical interlocking switch
Tight or unlock.
Originally it is embodied in the in-orbit replacement of satellite single machine module, passes through the mechanical interfaces such as standardized mechanical interlocking switch
3 and standardized electrical interface 3, realize replacement of the assembly of changeover mechanism and healthy single machine module relative to satellite platform, letter
The design for changing the in-orbit more alias 3 of satellite platform, meets the replacement demand of a variety of single machine modules；Pass through 5 He of coarse positioning guide bar
Fine positioning pin 6 cooperates, and reduces the demand to robotic arm manipulation precision, while improving module installation accuracy.
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. a kind of changeover mechanism characterized by comprising
Shell, the shell are hollow structure open at one end；
The opening of the shell is arranged in substrate, the substrate, and the shell and the substrate form intelligent board main body,
Material-putting space is equipped in the intelligent board main body；
Interface, the interface setting is on the substrate；
Electronic bolt hole, the electronic bolt hole setting is on the substrate；
Positioning mechanism, the positioning mechanism setting is on the substrate.
2. changeover mechanism according to claim 1, which is characterized in that the positioning mechanism includes the first positioning component and the
Two positioning components.
3. changeover mechanism according to claim 2, which is characterized in that first positioning component includes at least a guiding
Bar.
4. changeover mechanism according to claim 2, which is characterized in that second positioning component includes at least a positioning
Pin.
5. changeover mechanism according to claim 1, which is characterized in that be equipped with retaining mechanism, the lock on the substrate
Tightly mechanism includes:
Driving gear, the driving gear are arranged in the material-putting space, and driving motor is fixedly installed on the substrate,
The driving gear is connect with driving motor, is driven and is rotated by driving motor；
Driven gear, the driven gear are arranged in the material-putting space, with the driving gear by nibbling outside straight tooth column
The mode of conjunction is driven, and the driven gear is fixedly mounted on the transmission shaft；
Transmission shaft, the transmission shaft are arranged in the substrate, and one end of the transmission shaft is connect with the driven gear；
Locking switch, the locking switch setting on the substrate, are equipped with locking member, the locking in the locking switch
Part is connect with the other end of the transmission shaft.
6. changeover mechanism according to claim 5, which is characterized in that the quantity of the driven gear and the locking switch
It is two.
7. changeover mechanism according to claim 5 or 6, which is characterized in that the locking switch includes:
Retaining ring, on the substrate, the locking member is arranged in the centre bore of the retaining ring for the locking switch setting；
Locking assembly, the locking are arranged in the retaining ring.
8. changeover mechanism according to claim 7, which is characterized in that the quantity of the locking assembly is two groups.
9. changeover mechanism according to claim 7 or 8, which is characterized in that the locking assembly includes:
Locking pin, the locking pin are arranged in the retaining ring, and the locking pin stretches out or withdraw retaining ring, it is corresponding enter or
The pin hole on assembly mounting plate is exited, the locking and unlocking of assembly and outer mounting structure are completed；
Spring, the spring are set on the outside of the locking pin.
10. changeover mechanism according to claim 1, which is characterized in that be equipped with blasting bolt hole on the substrate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910113123.9A CN109969429B (en) | 2019-02-13 | 2019-02-13 | Switching mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910113123.9A CN109969429B (en) | 2019-02-13 | 2019-02-13 | Switching mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109969429A true CN109969429A (en) | 2019-07-05 |
| CN109969429B CN109969429B (en) | 2022-03-18 |
Family
ID=67076875
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910113123.9A Active CN109969429B (en) | 2019-02-13 | 2019-02-13 | Switching mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109969429B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103378477A (en) * | 2012-04-17 | 2013-10-30 | 上海航天测控通信研究所 | Aerospace single machine on track easy plugging mechanism |
| CN103448917A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Quick assembly service capsule of high-orbit satellite platform and application of quick assembly service capsule |
| CN203714185U (en) * | 2014-03-03 | 2014-07-16 | 大连大学 | Drawer-type flexible plug mechanism for replaceable module of satellite |
| CN106927065A (en) * | 2015-12-30 | 2017-07-07 | 北京空间飞行器总体设计部 | The acceptable in-orbit service satellite of untetheredization |
| CN107284696A (en) * | 2017-05-25 | 2017-10-24 | 上海卫星工程研究所 | The repetition locking unblock of the double super platforms of noncontact and energy supply integrated apparatus |
| CN107697317A (en) * | 2017-09-14 | 2018-02-16 | 上海欧科微航天科技有限公司 | A kind of modular microfluidic Nano satellite platform |
| CN109305391A (en) * | 2018-08-08 | 2019-02-05 | 上海宇航系统工程研究所 | Compress relieving mechanism and its method |
-
2019
- 2019-02-13 CN CN201910113123.9A patent/CN109969429B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103378477A (en) * | 2012-04-17 | 2013-10-30 | 上海航天测控通信研究所 | Aerospace single machine on track easy plugging mechanism |
| CN103448917A (en) * | 2013-08-08 | 2013-12-18 | 上海卫星工程研究所 | Quick assembly service capsule of high-orbit satellite platform and application of quick assembly service capsule |
| CN203714185U (en) * | 2014-03-03 | 2014-07-16 | 大连大学 | Drawer-type flexible plug mechanism for replaceable module of satellite |
| CN106927065A (en) * | 2015-12-30 | 2017-07-07 | 北京空间飞行器总体设计部 | The acceptable in-orbit service satellite of untetheredization |
| CN107284696A (en) * | 2017-05-25 | 2017-10-24 | 上海卫星工程研究所 | The repetition locking unblock of the double super platforms of noncontact and energy supply integrated apparatus |
| CN107697317A (en) * | 2017-09-14 | 2018-02-16 | 上海欧科微航天科技有限公司 | A kind of modular microfluidic Nano satellite platform |
| CN109305391A (en) * | 2018-08-08 | 2019-02-05 | 上海宇航系统工程研究所 | Compress relieving mechanism and its method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109969429B (en) | 2022-03-18 |
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