CN108825600B - Be applied to no external force installation device of spacecraft steel wire component - Google Patents
Be applied to no external force installation device of spacecraft steel wire component Download PDFInfo
- Publication number
- CN108825600B CN108825600B CN201810623977.7A CN201810623977A CN108825600B CN 108825600 B CN108825600 B CN 108825600B CN 201810623977 A CN201810623977 A CN 201810623977A CN 108825600 B CN108825600 B CN 108825600B
- Authority
- CN
- China
- Prior art keywords
- steel wire
- wire component
- spacecraft
- external force
- plane base
- 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.)
- Active
Links
- 229910000831 Steel Inorganic materials 0.000 title claims abstract description 61
- 239000010959 steel Substances 0.000 title claims abstract description 61
- 238000009434 installation Methods 0.000 title claims abstract description 24
- 238000005452 bending Methods 0.000 claims abstract description 6
- 230000009471 action Effects 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000004026 adhesive bonding Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B1/00—Devices for securing together, or preventing relative movement between, constructional elements or machine parts
- F16B1/02—Means for securing elements of mechanisms after operation
-
- 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)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Clamps And Clips (AREA)
- Connection Of Plates (AREA)
Abstract
The invention discloses a non-external force installation device applied to a spacecraft steel wire component, which comprises a steel wire component, a plane base,Tabletting; the pressing sheet is glued on the plane base and forms a U-shaped slot with a slot area on the plane base, the fixed installation surface of the steel wire component is placed in the U-shaped slot in a U-shaped state, and two ends of the steel wire component respectively penetrate through two strips of the pressing sheet
The shape edge and the two side edges of the plane base form a socket. The invention can realize the installation of the steel wire component subjected to bending treatment in the spacecraft structure without external force through a simple structure, the steel wire component is not subjected to the action of external force after being installed, the main structure of the steel wire component cannot deform due to installation, and the whole device has the characteristics of simplicity, practicability and high reliability.
Description
Technical Field
The invention relates to a spacecraft structure and a spacecraft mechanism, in particular to a non-external-force installation device applied to a spacecraft steel wire component, which is suitable for non-external-force installation of steel wire components formed by bending in spacecrafts such as satellites and the like, and ensures the shape precision of the steel wire components.
Background
With the development of spacecraft technology, the application of steel wire members to spacecrafts is becoming more and more extensive, the requirements on the shape accuracy of the bent steel wire members are increasing day by day, but the shape accuracy of the steel wire members is easy to change due to the conventional steel wire member installation method, and the steel wire members are not suitable for being applied to spacecraft mechanisms.
The above technical problems provide a demand for the installation of a steel wire member on a spacecraft without external force.
Disclosure of Invention
Aiming at the technical problems, the invention designs the installation device without external force, which is applied to the steel wire component of the spacecraft, from the aspects of product simplicity and practicability.
In order to achieve the purpose, the invention is realized by the following technical scheme:
a no-external-force installation device applied to a spacecraft steel wire component comprises a steel wire component, a plane base and a pressing sheet; the pressing sheet is glued on the plane base and forms a U-shaped slot with a slot area on the plane base, the fixed installation surface of the steel wire component is placed in the U-shaped slot in a U-shaped state, and two ends of the steel wire component respectively penetrate through two strips of the pressing sheet
The shape edge and the two side edges of the plane base form a socket.
Further, the steel wire member is in clearance fit with the U-shaped slot, and the fixing mounting surface of the steel wire member is positioned in the U-shaped slot which is slightly larger than the external dimension of the steel wire member.
Furthermore, a semicircular frame is arranged in the plane base, and the semicircular frame and the semicircular end part of the pressing sheet form a matching relation.
Further, the steel wire member is formed by bending a steel wire having a diameter d of 1.0mm to 2.0mm, and the cross-sectional dimension of the U-shaped slot formed by the flat base and the pressing piece is in the range of (d +0.2mm) to (d +0.4 mm).
The invention can realize the installation of the steel wire component subjected to bending treatment in the spacecraft structure without external force through a simple structure, the steel wire component is not subjected to the action of external force after being installed, the main structure of the steel wire component cannot deform due to installation, and the whole device has the characteristics of simplicity, practicability and high reliability.
Drawings
Fig. 1 is a schematic view of an external appearance configuration of a spacecraft steel wire member installation device without external force according to an embodiment of the invention;
fig. 2 is an appearance diagram of a steel wire member applied to a spacecraft steel wire member installation device without external force according to an embodiment of the invention.
Fig. 3 is an appearance diagram of a pressing sheet applied to a spacecraft steel wire member installation device without external force according to an embodiment of the invention.
Fig. 4 is an external view of a planar base applied to a spacecraft steel wire member installation device without external force according to an embodiment of the invention.
Fig. 5 is a working principle block diagram of a no-external-force installation device applied to a spacecraft steel wire member in an embodiment of the invention.
In the figure: 1-a steel wire member; 2-a planar base; and 3-tabletting.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1-5, an embodiment of the present invention provides a non-external force installation device applied to a spacecraft steel wire member, which includes a steel wire member 1, a planar base 2, and a pressing sheet 3; the pressing sheet 3 is glued on the plane base 2 and forms a U-shaped slot with the slot area on the plane base 2, the fixed installation surface of the steel wire component is placed in the U-shaped slot in a U-shaped state, and the two ends of the steel wire component respectively penetrate through the two strips of the pressing sheet 3
The shape edge and the two side edges of the plane base 2 form a socket. The steel wire component 1 is in clearance fit with the U-shaped slot, the fixing and mounting surface of the steel wire component is positioned in the U-shaped slot which is slightly larger than the external dimension of the steel wire component, the steel wire component has certain displacement allowance in the external force eliminating device, so that the steel wire component cannot deform in the fixing process, the shape precision of the steel wire component is kept, a semicircular frame is arranged in the plane base 2, the semicircular frame and the semicircular end part of the pressing sheet 3 form a fit relation, the relative position relation of the semicircular frame and the pressing sheet is determined in the mounting and gluing processes, the dimension of the U-shaped slot formed by the semicircular frame and the pressing sheet is ensured to be determined, and the unique state of the external shape of the steel wire mounting component is also ensured to.
The steel wire member may be formed by bending a steel wire having a diameter d of 1.0mm to 2.0mm, and the cross-sectional dimension of the U-shaped groove formed by the flat base and the pressing plate is in the range of (d +0.2mm) to (d +0.4 mm).
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes and modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention.
Claims (2)
1. The utility model provides a be applied to no external force installation device of spacecraft steel wire component which characterized in that: comprises a steel wire component (1), a plane base (2) and a pressing sheet (3); the pressing sheet (3) is glued on the plane base (2) to form a U-shaped slot with a slot area on the plane base (2), the fixed mounting surface of the steel wire component is placed in the U-shaped slot in a U-shaped state, and two ends of the steel wire component respectively penetrate through a socket formed by two L-shaped edges of the pressing sheet (3) and two side edges of the plane base (2);
the steel wire member (1) is in clearance fit with the U-shaped slot, and the fixed mounting surface of the steel wire member is positioned in the U-shaped slot with the external dimension slightly larger than that of the steel wire member;
a semicircular frame is arranged in the plane base (2), and the semicircular frame and the semicircular end part of the pressing sheet (3) form a matching relation.
2. A non-external force installation device applied to a spacecraft steel wire member as claimed in claim 1, wherein: the steel wire component is formed by bending a steel wire with the diameter d of 1.0-2.0 mm, and the section size of a U-shaped slot formed by the planar base and the pressing sheet is in the range of (d +0.2mm) - (d +0.4 mm).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810623977.7A CN108825600B (en) | 2018-06-15 | 2018-06-15 | Be applied to no external force installation device of spacecraft steel wire component |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810623977.7A CN108825600B (en) | 2018-06-15 | 2018-06-15 | Be applied to no external force installation device of spacecraft steel wire component |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108825600A CN108825600A (en) | 2018-11-16 |
| CN108825600B true CN108825600B (en) | 2021-02-19 |
Family
ID=64141635
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810623977.7A Active CN108825600B (en) | 2018-06-15 | 2018-06-15 | Be applied to no external force installation device of spacecraft steel wire component |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108825600B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102516038B1 (en) | 2016-04-05 | 2023-03-31 | 이뮨 센서, 엘엘씨 | cGAS antagonist compounds |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204207207U (en) * | 2014-11-24 | 2015-03-18 | 福建浔兴拉链科技股份有限公司 | Loosing core of horse hook can be clamped |
| CN106704485A (en) * | 2016-11-17 | 2017-05-24 | 上海卫星工程研究所 | Spacecraft rope constraint and release clamping hoop |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201106658Y (en) * | 2007-11-05 | 2008-08-27 | 中航勘察设计研究院 | Wire rope fast joint |
| CN201475250U (en) * | 2009-07-25 | 2010-05-19 | 李超 | Novel steel wire rope lockset |
-
2018
- 2018-06-15 CN CN201810623977.7A patent/CN108825600B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204207207U (en) * | 2014-11-24 | 2015-03-18 | 福建浔兴拉链科技股份有限公司 | Loosing core of horse hook can be clamped |
| CN106704485A (en) * | 2016-11-17 | 2017-05-24 | 上海卫星工程研究所 | Spacecraft rope constraint and release clamping hoop |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108825600A (en) | 2018-11-16 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20130314867A1 (en) | Display Device for Notebook Computer | |
| US10168733B2 (en) | Foldable body and foldable display apparatus | |
| US9955597B1 (en) | Electronic device and suspension mount thereof | |
| CN108825600B (en) | Be applied to no external force installation device of spacecraft steel wire component | |
| US20170100922A1 (en) | Laminating device and laminating method using the same | |
| CN101957643B (en) | Electronic device housing | |
| GB2583854A (en) | Shape memory alloy actuation apparatus | |
| CN103240755A (en) | Adjusting mechanism | |
| CN103576531B (en) | Dial plate and timepiece bottom plate fastening | |
| US9878510B2 (en) | Pressing apparatus and stamp press apparatus | |
| JPS5814323Y2 (en) | Adjustment device for adjusting the position of optical or electro-optical components in two mutually orthogonal directions | |
| US9411094B2 (en) | Backlight module and liquid crystal display device | |
| US10663784B2 (en) | Liquid crystal display device and display | |
| CN102207604B (en) | Holding device for reflector | |
| US6611999B1 (en) | Detent means for a heat sink | |
| CN210361136U (en) | Ear folding and returning mechanism | |
| CN108789220B (en) | Jig tool | |
| TW200505768A (en) | Cassette for substrate | |
| JPH0744051Y2 (en) | Fixing structure of board to housing and fixing jig | |
| JP2016052184A (en) | Fitting structure for solar cell panel, and fitting method for solar cell panel | |
| CN102595825B (en) | Elastic module, slip cover structure employing elastic module and electronic device | |
| JP2010014189A (en) | Floating nut | |
| CN205554072U (en) | Bracket with fixed double hinge | |
| EP1193518A3 (en) | Compensation mechanism for component and assembly deviation in a component precision positioning stage | |
| PL1933997T3 (en) | Method for producing a fold on a sheet metal element, sheet metal element and device for pre-folding a metal sheet element |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |