CN106005492A - Ultra-light type simple locking device for space navigation - Google Patents
Ultra-light type simple locking device for space navigation Download PDFInfo
- Publication number
- CN106005492A CN106005492A CN201610552754.7A CN201610552754A CN106005492A CN 106005492 A CN106005492 A CN 106005492A CN 201610552754 A CN201610552754 A CN 201610552754A CN 106005492 A CN106005492 A CN 106005492A
- Authority
- CN
- China
- Prior art keywords
- seat
- locking device
- stay
- simple locking
- microlight
- 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
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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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Clamps And Clips (AREA)
Abstract
The invention relates to an ultra-light type simple locking device for space navigation. The ultra-light type simple locking device comprises a fixed seat, an expanding seat, a rotating shaft, a torsion spring, a locking piece and a nut. When expanding in place, the expanding seat can be easily ejected into the inner side of the locking piece and is locked into the inner side of the locking piece due to the sufficient rigidity of a stressed part of the locking piece during the ejection, thereby realizing locking. The fixed seat is fixedly connected with an expandable structure through a bolt, and the expanding seat is fixedly connected with another part of the expandable structure; the fixed seat, the expanding seat and the torsion spring are mounted on the rotating shaft; and the locking piece is fixed at the bottom of the fixed seat through a bolt and is adjusted to a proper locking position by moving the mounting position of the locking piece. A traditional locking device is locked by virtue of a torsion spring and is generally matched with an expanded volute spiral spring for use. Compared with a traditional manner, the ultra-light type simple locking device has the advantages of simple structure, small volume, lightness, low cost, strong portability and the like and further has very wide application prospect.
Description
Technical field
The present invention relates to a kind of microlight-type, small and exquisite reliable, simple locking device that transplantability is strong, particularly relate to a kind of aerospace
With small-sized Satellite Unfurlable Antenna structure locking device.
Background technology
Nowadays the deployable structure application of aeronautical field is more and more extensive, and the requisite composition of deployable structure is exactly
Launching and locking device, traditional locking device that launches reaches to launch and launch by the way of scroll spring with torsion spring combination
Spacing purpose after putting in place.This mechanism not only structure is complicated, volume is big, cost is high, and the weight of single mechanism just can reach 200
~ 300g, and be generally employed in pairs, between two mechanisms, CCL to be connected controls to launch track simultaneously.But aerospace product pair
Physical dimension, weight and reliability requirement are harsh, and the most this mechanism is greatly limited in application.
Summary of the invention
It is an object of the invention to provide a kind of microlight-type, small and exquisite reliable, simple locking device that transplantability is strong, be used for solving
The certainly shortcoming of tradition aerospace locking device.Compared with tradition locking device, this device has that simple in construction, volume be little, weight
The advantages such as gently, low cost, transplantability be strong.
To achieve these goals, the invention discloses a kind of simple locking device of aerospace microlight-type, described device institute
State simple locking device to include fixing seat, launch seat, rotary shaft, torsion spring, stay, nut；Described fixing seat and expansion seat divide
It is not connected with two parts of deployable structure；A part for deployable structure is connected on fixing seat, and another part is connected to exhibition
Open on seat；Fixing seat, expansion seat and torsion spring are installed on the rotary shaft, and stay is fixed on fixing seat bottom portion by nut.Make
For preferably, described fixing seat is different and different from described expansion holder structure form meeting foundation deployable structure.
As preferably, fixing seat is affixed with a part for deployable structure by screw, and described expansion seat passes through screw
Affixed with another part of deployable structure.The various location of described stay uses rigidity of structure difference, by plain cushion, bullet
Pad realizes launching seat and easily snaps into and no longer eject.
As preferably, described stay perforate is strip, can according to circumstances regulate on one direction of stay
Installation site.Described expansion mode is that torsion spring launches, and does not limit this specific expansion mode.
Due to the fact that the above technical scheme of employing, compared with prior art, have the following advantages that and good effect:
1) present invention utilizes the construction features of stay self, after expansion seat launches to put in place so that it is stuck inside stay,
To reach to lock purpose.
2) stay of the present invention can with multiple expansion mode with the use of, transplantability is stronger.
3) to have simple in construction, small and exquisite reliable, lightweight, low cost etc. compared with traditional approach excellent for device of the present invention
Point, has the highest promotional value.
Accompanying drawing explanation
Fig. 1 is a kind of simple locking device of aerospace microlight-type of present invention structural representation when not locking；
Fig. 2 is structural representation during a kind of aerospace microlight-type simple locking device locking of the present invention；
Fig. 3 is the detail view of the aerospace microlight-type simple locking device stay of the embodiment of the present invention.
Detailed description of the invention
The present invention is further illustrated with reference to the accompanying drawings with specific embodiment.
As shown in Figure 1, as the one simple locking device of aerospace microlight-type of the present invention, it is used for solving middle-size and small-size exhibition
Locking problem after opening structure expansion.This device include fixing seat 1, launch seat 2, stay 3, rotary shaft 4, torsion spring 5, plain cushion 6,
Spring washer 7, nut 8.Fixing seat 1 and launch seat 2 and be connected with two parts of deployable structure respectively by screw, fix simultaneously seat 1,
Launch seat 2 and torsion spring 5 is arranged in rotary shaft 4.Stay 3 is fixed on the bottom of fixing seat 1 by nut 8.Utilize locking
The rigidity of structure difference of sheet 3 various location, realizes launching seat 2 by plain cushion 6, spring washer 7 and easily snaps into and no longer eject
Thus reach to lock purpose.Wherein the open-cellular form of stay is as it is shown on figure 3, the installation of itself and fixing seat can according to circumstances be regulated
Position.
Further, depending on the version of fixing seat 1 and expansion seat 2 is according to the form of deployable structure.Launch seat 2 and can
Deployed configuration starts around rotary shaft rotary expansion under the driving of torsion spring 5, launches seat 2 and come into contact with lock after being deployed into certain angle
Tight sheet 3, continues to launch, and launches seat 2 and will down extrude stay 3, the portion being now connected with fixing seat 1 due to stay 3 root
Point rigidity is more weak, launches seat 2 and down extrude stay 3 and be rotated further inside through entrance stay 3 and launch to put in place.Further,
Owing to there is expansion impact after launching to put in place, expansion seat 2, by by certain bounce, launches seat 2 and will extrude stay backward
3, and now the force part rigidity of stay 3 is relatively big, by stuck inside stay for expansion seat 2, thus reaches to lock purpose.
Further, state during locking is as shown in Figure 2.
In sum, the present invention devises a microlight-type, the simplest small and exquisite locking device, compared with traditional approach
There is simple in construction, small and exquisite reliable, lightweight, low cost and other advantages, there is the highest promotional value.
The disclosed above specific embodiment being only the present invention, this embodiment only used by the clearer explanation present invention,
And not limitation of the invention, the changes that any person skilled in the art can think of, all should fall in protection domain.
Claims (5)
1. the simple locking device of aerospace microlight-type, it is characterised in that described simple locking device includes fixing seat, expansion
Seat, rotary shaft, torsion spring, stay, nut；
Described fixing seat and expansion seat are connected with two parts of deployable structure respectively；A part for deployable structure is connected to solid
In reservation, another part is connected to launch on seat；Fixing seat, expansion seat and torsion spring are installed on the rotary shaft, and stay passes through
Nut is fixed on fixing seat bottom portion.
2. the simple locking device of aerospace microlight-type as claimed in claim 1, it is characterised in that described fixing seat passes through screw
Affixed with a part for deployable structure, described expansion seat is affixed with another part of deployable structure by screw.
3. the simple locking device of aerospace microlight-type as claimed in claim 1 or 2, it is characterised in that described stay is not
Use rigidity of structure difference at co-located, realize launching seat by plain cushion, spring washer and easily snap into and no longer eject.
4. the simple locking device of aerospace microlight-type as claimed in claim 1 or 2, it is characterised in that described expansion seat and can
Deployed configuration around rotary shaft rotary expansion, launches seat and comes into contact with stay under the driving of torsion spring after being deployed into certain angle.
5. the simple locking device of aerospace microlight-type as claimed in claim 1, it is characterised in that described stay perforate is for long
Bar shaped, described expansion seat is entered by extruding stay and launches to put in place inside stay.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610552754.7A CN106005492A (en) | 2016-07-14 | 2016-07-14 | Ultra-light type simple locking device for space navigation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610552754.7A CN106005492A (en) | 2016-07-14 | 2016-07-14 | Ultra-light type simple locking device for space navigation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106005492A true CN106005492A (en) | 2016-10-12 |
Family
ID=57118729
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610552754.7A Pending CN106005492A (en) | 2016-07-14 | 2016-07-14 | Ultra-light type simple locking device for space navigation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106005492A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112977885A (en) * | 2021-04-23 | 2021-06-18 | 中国科学院微小卫星创新研究院 | Elastic hot knife unlocking device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1191271A2 (en) * | 2000-09-20 | 2002-03-27 | Sener, Ingenieria Y Sistemas, S.A. | Remote activation mechanism for equipment hold down and release |
| KR20040043358A (en) * | 2002-11-18 | 2004-05-24 | 한국항공우주연구원 | Cam-plate Driving Array Deployment Mechanisms of Satellite |
| CN201264746Y (en) * | 2008-09-04 | 2009-07-01 | 许友福 | Seal clip with spoon |
| CN105114442A (en) * | 2015-09-06 | 2015-12-02 | 南京理工大学 | Hinge for expandable solar cell array of cubesat |
| CN105673677A (en) * | 2014-11-18 | 2016-06-15 | 中国科学院沈阳自动化研究所 | Solar cell panel unfolding locking mechanism |
-
2016
- 2016-07-14 CN CN201610552754.7A patent/CN106005492A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1191271A2 (en) * | 2000-09-20 | 2002-03-27 | Sener, Ingenieria Y Sistemas, S.A. | Remote activation mechanism for equipment hold down and release |
| KR20040043358A (en) * | 2002-11-18 | 2004-05-24 | 한국항공우주연구원 | Cam-plate Driving Array Deployment Mechanisms of Satellite |
| CN201264746Y (en) * | 2008-09-04 | 2009-07-01 | 许友福 | Seal clip with spoon |
| CN105673677A (en) * | 2014-11-18 | 2016-06-15 | 中国科学院沈阳自动化研究所 | Solar cell panel unfolding locking mechanism |
| CN105114442A (en) * | 2015-09-06 | 2015-12-02 | 南京理工大学 | Hinge for expandable solar cell array of cubesat |
Non-Patent Citations (1)
| Title |
|---|
| 任守志 等: "立方体卫星太阳翼技术综述", 《航天器工程》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112977885A (en) * | 2021-04-23 | 2021-06-18 | 中国科学院微小卫星创新研究院 | Elastic hot knife unlocking device |
| CN112977885B (en) * | 2021-04-23 | 2023-06-23 | 中国科学院微小卫星创新研究院 | Elastic hot knife unlocking device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into 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: 20161012 |