CN106586038B - A kind of more plates compression release systems of distribution - Google Patents
A kind of more plates compression release systems of distribution Download PDFInfo
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- CN106586038B CN106586038B CN201610981284.6A CN201610981284A CN106586038B CN 106586038 B CN106586038 B CN 106586038B CN 201610981284 A CN201610981284 A CN 201610981284A CN 106586038 B CN106586038 B CN 106586038B
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- 230000006835 compression Effects 0.000 title claims abstract description 58
- 238000007906 compression Methods 0.000 title claims abstract description 58
- 230000037452 priming Effects 0.000 claims abstract description 35
- 238000005474 detonation Methods 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 4
- 238000009434 installation Methods 0.000 claims description 3
- 240000002853 Nelumbo nucifera Species 0.000 abstract description 2
- 235000006508 Nelumbo nucifera Nutrition 0.000 abstract description 2
- 235000006510 Nelumbo pentapetala Nutrition 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
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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
- B64G1/64—Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
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- Engineering & Computer Science (AREA)
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- Aviation & Aerospace Engineering (AREA)
- Automatic Assembly (AREA)
- Connection Of Plates (AREA)
Abstract
The invention discloses a kind of more plates of distribution to compress release system, takes full advantage of spacecraft self structure and undertakes the how onboard lotus of big weight in the stress of section generation of entering the orbit.The compression discharges system and is made of a certain number of compression brackets, compressor arm, pressure plate and compression release priming system, and is combined spacecraft truss and realizes compression release function to load plate.The present invention has high reliablity, and controllability is good with the big feature of compressible weight, suitable for various spacecrafts and load task.
Description
Technical field
The present invention relates to the compressions for being mounted in spaceborne load to discharge system, especially a kind of using distributed
The system that scheme discharges after realizing transmitter section compression for the plate load of multi-quantity and enter the orbit.
Background technique
Traditional compression release system mostly uses priming system form to be directly connected to be compacted load, passes through load self structure
Undertake the stress for section generation of entering the orbit.But with military with civilian demand increasingly raising, the length of load, area, quantity with
Weight etc., which has, largely to be promoted, and traditional compression release system is difficult to meet the requirement that more plates compress release；Meanwhile mistake
Carrying the stress generated can not bear by the self structure of big weight load.
Summary of the invention
For solve traditional compressions release system be difficult to meet more plates compress release requirement and overload generation stress without
The problem of method is born by load self structure, the present invention provides one kind to realize transmitter section pressure for the plate load of multi-quantity
Tightly with enter the orbit after the distributed system that discharges, make full use of spacecraft itself truss structure to realize and compress release function.
The specific technical solution of the present invention is as follows:
A kind of more plates of distribution compress release systems, for realizing multiple load plates transmitter section compress and with enter the orbit after release
It puts, multiple compression brackets for being arranged in a manner of multilayer by the length direction along the load plate two opposite flanks, multiple pressures
Tight bar, multiple pressure plates and multiple compressions release priming system composition；Wherein, it is added in each load plate and compression is installed
Release system mounting platform is used to provide the described the connecting interface for compressing bracket and the compressor arm, is used for each load
The compression bracket of plate be connected to it is described compression release system mounting platform on and it is described compress bracket installation direction with
The load plate is vertical, and the compression bracket between the adjacent load plate mutually abuts, while being connected to the described of edge
The compression bracket in load plate is connected on spacecraft truss；One end of each compressor arm is connected to the compression and releases
On place system mounting platform；The pressure plate includes I type and II type, and the I type pressure plate passes through pressure plate hinge and the boat
The connection of its device truss, the II type pressure plate are fixedly connected with the spacecraft truss, and the I type and II type pressure plate are through a pressure
Tight block and a disc spring apply pressing force to the other end of the compressor arm, and can adjust the pressing force by an adjusting nut
Size；The compression release priming system connects the I type pressure plate, II type pressure plate and spacecraft truss and to the compression
The other end of bar applies pressing force；
The spacecraft truss, is made of fixed frame and bolt, the both ends of the bolt and the fixed frame point
It is not connected by bolt hinge and bolt priming system, and there are be connected with the compression bracket on the spacecraft truss
Connecting interface.
Preferably, the compression bracket, including I type and II type, the I type and II type compress bracket and use tapered sleeve form
It realizes and compresses, and the I type and II type the compression bracket for being located at middle part are connect with the load plate, the I positioned at edge
Type compresses bracket with II type and connect respectively with the spacecraft truss and the bolt.
The bolt hinge and bolt priming system plays in transmitter section and provides the function of compressing counter-force and stress transfer, and
Bolt priming system detonates after entering the orbit, and bolt hinge pushes bolt to turn on, and plays the function of whole pressing force unloading release.
A method of release system is compressed using the above-mentioned more plates of distribution, and load plate is compressed and discharged, including
Following steps,
The first step using the bolt priming system carries out the bolt and the fixed frame before Spacecraft Launch whole
Connection；
Second step, using compression release priming system by the pressure plate to the compression bracket and the compressor arm
Apply pressing force；
Third step, after Spacecraft Launch is entered the orbit, the bolt priming system detonation；
4th step, the bolt hinge push the bolt to turn on, and unload the pressing force for compressing holder orientation and release
It puts；
5th step, the compression release priming system detonation, unloads the pressing force of the pressure plate；
6th step, the pressure plate hinge push the I type pressure plate to turn on, discharge the compressor arm；
7th step completes the release of the load plate.
The present invention has high reliablity, and controllability is good with the big feature of compressible weight, suitable for various spacecrafts and
Load task.
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,
Fig. 1 show figure of the invention；
Fig. 2 show figure of the invention；
Fig. 3 show figure of the invention；
Fig. 4 show the figure that the more plates of distribution of the invention compress release system；
Fig. 5 show the figure that the more plates of distribution of the invention compress release system；
Fig. 6 show the figure of one embodiment of the invention.
Specific embodiment
The invention discloses a kind of more plates of distribution to compress release system, and spacecraft self structure is made full use of to undertake big weight
How onboard lotus is measured in the stress of section generation of entering the orbit.The system has high reliablity, and controllability is good and the big spy of compressible weight
Point is suitable for various spacecrafts and load task.In domestic and international paper, patent, data and the news report that inventor retrieves
In do not find technology similar to the present invention.
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, various modifications and improvements can be made, these belong to the present invention
Protection scope.
Embodiment
A kind of more plates of distribution provided in this embodiment compress release systems, by a certain number of compression brackets, compressor arm,
Pressure plate and compression release priming system composition, and be combined spacecraft truss and compression release function is realized to load plate.This
The more plates of distribution of embodiment compress the composition of release system, including fixed frame 1, bolt 2, bolt priming system 3, bolt hinge
4, bracket 5, compressor arm 6, pressure plate 7, compression release priming system 8 etc. are compressed；Wherein, bolt priming system 3 will be consolidated with bolt hinge 4
Determine frame 1 and bolt 2 is connected to become entirety, load plate 9 is fixed frame 1 and bolt 2 surrounds wherein.Also, it is mounted on load
Compression bracket 5 on plate 9 is compressed by bolt 2；And the compressor arm 6 in load plate 9 is mounted on then by pressure plate 7 and pressure
Tight release priming system 8 is pressed on fixed frame 1, specifically, in the load plate 9 adds to be equipped with compressing release system peace
Assembling platform, to provide the connecting interface for compressing bracket 5 and compressor arm 6.The spacecraft truss, by fixed frame 1 and bolt 2
Composition, be connected between bolt 2 and fixed frame 1 by bolt hinge 4 and bolt priming system 3, thereon there are with compress 5 phase of bracket
The connecting interface of connection.Bolt hinge 4 and bolt priming system 3 are played in transmitter section provides the function for compressing counter-force and stress transfer
Can, bolt priming system 3 detonates after entering the orbit, and bolt hinge 4 pushes bolt 2 to turn on, and plays the whole pressing force for compressing holder orientation
Unload the function of release.
Fig. 3, the compression bracket 5, including I type and II type are referred to, bracket 5 is compressed using tapered sleeve form and realizes pressure
Tightly, and with the fixed frame 1 of load plate 9 or spacecraft truss it connect, specifically, the compression bracket 5 in the load plate of middle part
Connect with the compression release system mounting platform in load plate 9 and compress bracket 5 installation direction and the load plate 9 hang down
Directly, the compression bracket 5 being located on edge loading plate then connect with the fixed frame 1 of spacecraft truss or connect with bolt 2, and
And it is mutually abutted between the compression bracket being arranged in adjacent load plate.The compressor arm 6 uses bulb round rod type, and its
The compression release system mounting platform being arranged on one end and load plate 9 is connect.
Fig. 4, Fig. 5 and Fig. 6, the pressure plate 7, including I type and II type are referred to, the I type pressure plate passes through pressure plate
Hinge 10 is connect with the fixed frame 1 of spacecraft truss, and the fixed frame 1 of the II type pressure plate and spacecraft truss is fixed to be connected
It connects.Fig. 6 is referred to, the I type is applied with II type pressure plate through a compact heap 11 and the other end of the disc spring 12 to the compressor arm 6
Compressive force, and the size of the pressing force can be adjusted by an adjusting nut 13, specifically, it is equipped on I type pressure plate
Compressor arm 6 is pressed on II type pressure plate by compact heap 11, disc spring 12 and adjusting nut 13, and wherein disc spring 12 provides pressing force,
And the adjustment of pressing force size can be realized by adjusting nut 13.The compression release priming system 8 plays the connection I type
Pressure plate, the fixed frame 1 of II type pressure plate and spacecraft truss and the work for applying pressing force to the other end of the compressor arm 6
With.
Fig. 2 show distributed more plates and compresses release system overall configuration, and the more plates of the distribution compress as can be seen from Fig. 2
Release system includes four layers, and every layer according to above-mentioned set-up mode setting bolt 2, bolt priming system 3, bolt hinge 4, compression
Bracket 5, pressure plate 7, compresses release priming system 8 etc. at compressor arm 6, and for upper layer, the setting of pressure plate 7 and its
Remaining layer is different.For the present invention, the number of plies that the more plates of the distribution compress release system is not limited, above-mentioned specific
The explanation of the number of plies is not also construed as limiting the invention.Wherein, for more plates distributed for the upper layer compress, release fire is compressed
After work product 8 detonate, pressure plate hinge 10 pushes I type pressure plate integrally to turn up, and the release of compressor arm 6 is realized in pressing force unloading.It is right
For the distributed more plates of the lower layer compress, after compressing the release detonation of priming system 8, pressure plate hinge 10 pushes I type pressure plate to turn
It opens, the release of compressor arm 6 is realized in pressing force unloading.The design of the upper and lower distributed more plate clamping plans of layer is intended to avoid spacecraft
The interference of truss.
When the more plates of distribution being applicable in for specific multiple load plates designs compress release system, by needing to press
The load plate and spacecraft truss tightly discharged is analyzed, and the demand of pressing force is refined, and determines that distributed more plates compress release system
The compression number of plies that system needs, and then determine every layer of compression bracket, compressor arm, pressure plate, compress the quantity such as release priming system.
The workflow that the more plates of distribution compress release system is as follows:
The first step is connected before Spacecraft Launch with fixed frame 1 using 3 pair of latches 2 of bolt priming system；
Second step applies pressing force by 7 pairs of compression brackets 5 of pressure plate and compressor arm 6 using release priming system 8 is compressed；
Third step, after Spacecraft Launch is entered the orbit, bolt priming system 3 detonates；
4th step, bolt hinge 4 push bolt 2 to turn on, and unloading compresses the pressing force of holder orientation and release；
5th step compresses release priming system 8 and detonates, unloads the pressing force of pressure plate 7；
6th step, pressure plate hinge 10 push I type pressure plate to turn on, and discharge compressor arm 6；
7th step completes the release of load plate.
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 various deformations or amendments within the scope of the claims, this not shadow
Ring substantive content of the invention.
Claims (3)
1. a kind of more plates of distribution compress release system, discharged after transmitter section compresses and enters the orbit for realizing multiple load plates,
It is characterized in that, the multiple compression branch being arranged in a manner of multilayer by the length direction along the load plate two opposite flanks
Frame, multiple compressor arms, multiple pressure plates and multiple compressions release priming system composition；Wherein, it is added in each load plate
It is equipped with and compresses release system mounting platform, be used to provide the described the connecting interface for compressing bracket and the compressor arm, for every
The compression bracket of one load plate is connected on the compression release system mounting platform and described compresses bracket
Installation direction is vertical with the load plate, and the compression bracket between the adjacent load plate mutually abuts, and is connected to simultaneously
The compression bracket in the load plate at edge is connected on spacecraft truss；One end of each compressor arm is connected to
On the compression release system mounting platform；The pressure plate includes I type and II type, and the I type pressure plate is cut with scissors by pressure plate
Chain is connect with the spacecraft truss, and the II type pressure plate is fixedly connected with the spacecraft truss, the I type and II type pressure
Tight plate applies pressing force to the other end of the compressor arm through a compact heap and a disc spring, and can be adjusted by an adjusting nut
The size of the pressing force；The compression release priming system connects the I type pressure plate, II type pressure plate and spacecraft truss simultaneously
Pressing force is applied to the other end of the compressor arm；
The spacecraft truss, is made of fixed frame and bolt, and the both ends of the bolt lead to respectively with the fixed frame
It crosses bolt hinge and bolt priming system is connected, and there are the companies being connected with the compression bracket on the spacecraft truss
Connection interface.
2. the more plates of distribution according to claim 1 compress release system, which is characterized in that the compression bracket, including I
Type and II type, the I type and II type are compressed bracket and are realized the I type and II for compressing, and being located at middle part using tapered sleeve form
Type compresses bracket and connect with the load plate, positioned at edge the I type and II type compression bracket respectively with the fixed frame
Or the bolt connection.
3. a kind of compress load plate using the more plates compression release systems of distribution of any of claims 1-2
With the method for release, which is characterized in that include the following steps,
The first step carries out whole connect to the bolt and the fixed frame using the bolt priming system before Spacecraft Launch
It connects；
Second step applies the compression bracket and the compressor arm by the pressure plate using compression release priming system
Pressing force；
Third step, after Spacecraft Launch is entered the orbit, the bolt priming system detonation；
4th step, the bolt hinge push the bolt to turn on, and unload the pressing force for compressing holder orientation and release；
5th step, the compression release priming system detonation, unloads the pressing force of the pressure plate；
6th step, the pressure plate hinge push the I type pressure plate to turn on, discharge the compressor arm；
7th step completes the release of the load plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610981284.6A CN106586038B (en) | 2016-11-08 | 2016-11-08 | A kind of more plates compression release systems of distribution |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610981284.6A CN106586038B (en) | 2016-11-08 | 2016-11-08 | A kind of more plates compression release systems of distribution |
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| Publication Number | Publication Date |
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| CN106586038A CN106586038A (en) | 2017-04-26 |
| CN106586038B true CN106586038B (en) | 2019-02-01 |
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| CN201610981284.6A Active CN106586038B (en) | 2016-11-08 | 2016-11-08 | A kind of more plates compression release systems of distribution |
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Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109305391B (en) * | 2018-08-08 | 2021-12-21 | 上海宇航系统工程研究所 | Compression release mechanism and method thereof |
| CN109818130B (en) * | 2019-02-14 | 2020-12-08 | 上海卫星工程研究所 | Antenna plate limiting type pressing system and method thereof |
| CN112373734B (en) * | 2020-11-24 | 2022-02-15 | 东方红卫星移动通信有限公司 | Low-orbit satellite group emission satellite-arrow separation unlocking module and satellite-arrow separation method |
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|---|---|---|---|---|
| US6102339A (en) * | 1998-04-17 | 2000-08-15 | Turbosat Technology, Inc. | Sun-synchronous sun ray blocking device for use in a spacecraft having a directionally controlled main body |
| CN102145753A (en) * | 2010-02-10 | 2011-08-10 | 上海卫星工程研究所 | Unstressed installation method for solar cell array driving mechanism |
| CN102616388A (en) * | 2011-06-08 | 2012-08-01 | 清华大学 | Solar cell array unfolding device capable of being unfolded in large area |
| CN103662098A (en) * | 2012-08-31 | 2014-03-26 | 上海宇航系统工程研究所 | Semi-rigid solar battery wing of spacecraft |
| CN103754391A (en) * | 2014-01-02 | 2014-04-30 | 上海宇航系统工程研究所 | Large space mechanism compressing and releasing device |
-
2016
- 2016-11-08 CN CN201610981284.6A patent/CN106586038B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6102339A (en) * | 1998-04-17 | 2000-08-15 | Turbosat Technology, Inc. | Sun-synchronous sun ray blocking device for use in a spacecraft having a directionally controlled main body |
| CN102145753A (en) * | 2010-02-10 | 2011-08-10 | 上海卫星工程研究所 | Unstressed installation method for solar cell array driving mechanism |
| CN102616388A (en) * | 2011-06-08 | 2012-08-01 | 清华大学 | Solar cell array unfolding device capable of being unfolded in large area |
| CN103662098A (en) * | 2012-08-31 | 2014-03-26 | 上海宇航系统工程研究所 | Semi-rigid solar battery wing of spacecraft |
| CN103754391A (en) * | 2014-01-02 | 2014-04-30 | 上海宇航系统工程研究所 | Large space mechanism compressing and releasing device |
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| CN106586038A (en) | 2017-04-26 |
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