CN108825600A - One kind being applied to spacecraft wire members without external force mounting device - Google Patents
One kind being applied to spacecraft wire members without external force mounting device Download PDFInfo
- Publication number
- CN108825600A CN108825600A CN201810623977.7A CN201810623977A CN108825600A CN 108825600 A CN108825600 A CN 108825600A CN 201810623977 A CN201810623977 A CN 201810623977A CN 108825600 A CN108825600 A CN 108825600A
- Authority
- CN
- China
- Prior art keywords
- wire members
- external force
- spacecraft
- flat base
- tabletting
- 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.)
- Granted
Links
- 238000009434 installation Methods 0.000 claims abstract description 16
- 238000000465 moulding Methods 0.000 claims description 3
- 230000015572 biosynthetic process Effects 0.000 claims 1
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 6
- 238000005452 bending Methods 0.000 abstract description 4
- 230000008569 process Effects 0.000 abstract description 3
- 229910000831 Steel Inorganic materials 0.000 description 3
- 239000010959 steel Substances 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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)
- Connection Of Plates (AREA)
- Clamps And Clips (AREA)
Abstract
The present invention discloses one kind and is applied to spacecraft wire members without external force mounting device, including wire members, flat base, tabletting；The tabletting is glued on the flat base and forms a U-shaped slot with the slot region on flat base, and the fixed installation face state of being in U-shape of the wire members is placed in U-shaped slot, and both ends are each passed through by two of the tablettingThe socket that shape side and the two sides of flat base are constituted.The present invention can realize installing without external force for wire members of bending process in spacecraft structure by simple structure, not by external force after wire members installation, its main structure will not be deformed because of installation, and whole device has the characteristics that simple and practical, high reliablity.
Description
Technical field
The present invention relates to spacecraft structure and mechanism, specially a kind of spacecraft wire members that are applied to are filled without external force installation
It sets, installing without external force for wire members made of bending suitable for the spacecrafts such as satellite guarantees the form accuracy of wire members.
Background technique
With the development of spacecraft technology, wire members are increasingly extensive in spaceborne application, to steel made of bending
The form accuracy of silk component requires increasingly to increase, but conventional wire members installation method is easy to cause the shape essence of wire members
The change of degree is not suitable for applying in spacecraft mechanism.
Above technical problem proposes demand without external force installation to spaceborne wire members.
Summary of the invention
In view of the above technical problems, from product simplicity and practicability, the present invention devises a kind of applied to space flight
Device wire members are without external force mounting device.
To achieve the above object, the invention is realized by the following technical scheme：
One kind being applied to spacecraft wire members without external force mounting device, including wire members, flat base, tabletting；Institute
State tabletting be glued on the flat base on flat base slot region formed a U-shaped slot, the wire members
The fixed installation face state of being in U-shape is placed in U-shaped slot, and both ends are each passed through by two of the tablettingShape side and plane bottom
The socket that the two sides of seat are constituted.
Further, the wire members and U-shaped slot clearance fit, the fixed installation face of wire members are in a ratio
In the slightly larger U-shaped slot of the outer dimension of itself.
Further, half circular frame, the semi-circular ends shape of the semicircle frame and tabletting are equipped in the flat base
At a matching relationship.
Further, the wire members bend molding, flat base and pressure by the rigid silk that diameter d is 1.0mm~2.0mm
The sectional dimension for the U-shaped slot that piece is formed is in the range of (d+0.2mm)~(d+0.4mm).
The present invention by simple structure can realize wire members of bending process in spacecraft structure without external force
Installation, not by external force after wire members installation, main structure will not be deformed because of installation, and whole device has letter
The characteristics of single practical, high reliablity.
Detailed description of the invention
Fig. 1, which is that the embodiment of the present invention is a kind of, to be illustrated applied to spacecraft wire members without the appearance configuration of external force mounting device
Figure；
Fig. 2 is a kind of wire members appearance applied to spacecraft wire members without external force mounting device of the embodiment of the present invention
Figure.
Fig. 3 is a kind of tabletting outside drawing applied to spacecraft wire members without external force mounting device of the embodiment of the present invention.
Fig. 4 is a kind of flat base appearance applied to spacecraft wire members without external force mounting device of the embodiment of the present invention
Figure.
Fig. 5 is a kind of working principle frame applied to spacecraft wire members without external force mounting device of the embodiment of the present invention
Figure.
In figure：1- wire members；2- flat base；3- tabletting.
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, various modifications and improvements can be made.These belong to the present invention
Protection scope.
As Figure 1-Figure 5, it is applied to spacecraft wire members the embodiment of the invention provides one kind and dress is installed without external force
It sets, including wire members 1, flat base 2, tabletting 3；The tabletting 3 be glued on the flat base 2 on flat base 2
Slot region form a U-shaped slot, the fixed installation face state of being in U-shape of the wire members is placed in U-shaped slot, both ends
It is each passed through by two of the tabletting 3The socket that shape side and the two sides of flat base 2 are constituted.The wire members 1 and U
Shape slot clearance fit, the fixed installation face of wire members are in a U-shaped slot more slightly larger than the outer dimension of itself, steel
Silk component has certain deflection yoke in outer force eliminating device, therefore in fixation procedure, wire members will not generate shape
Become, thus maintain the form accuracy of wire members, be equipped with half circular frame in the flat base 2, the semicircle frame and
The semi-circular ends of tabletting 3 form a matching relationship, and the relative positional relationship both in installation and Bonding Process is determining
, both guarantee to be formed by U-lag having a size of determining, also guarantees the unique shape for eventually forming steel wire mounting assembly shape
State.
Wire members can be bent molding, the U that flat base and tabletting are formed by the rigid silk that diameter d is 1.0mm~2.0mm
Shape slot cross-section size is in the range of (d+0.2mm)~(d+0.4mm).
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 (4)
1. one kind is applied to spacecraft wire members without external force mounting device, it is characterised in that：Including wire members (1), plane
Pedestal (2), tabletting (3)；The tabletting (3) is glued on the flat base (2) and the slot region shape on flat base (2)
At a U-shaped slot, the fixed installation face state of being in U-shape of the wire members is placed in U-shaped slot, and both ends are each passed through by institute
The socket that the two sides on the two ┐ shape sides and flat base (2) of stating tabletting (3) are constituted.
2. a kind of spacecraft wire members that are applied to as described in claim 1 are without external force mounting device, it is characterised in that：It is described
Wire members (1) and U-shaped slot clearance fit, the fixed installation face of wire members be in one it is more slightly larger than the outer dimension of itself
U-shaped slot in.
3. a kind of spacecraft wire members that are applied to as described in claim 1 are without external force mounting device, it is characterised in that：It is described
Half circular frame, semi-circular ends one matching relationship of formation of the semicircle frame and tabletting (3) are equipped in flat base (2).
4. a kind of spacecraft wire members that are applied to as described in claim 1 are without external force mounting device, it is characterised in that：It is described
Wire members bend molding, the section for the U-shaped slot that flat base and tabletting are formed by the rigid silk that diameter d is 1.0mm~2.0mm
Size is in the range of (d+0.2mm)~(d+0.4mm).
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 true CN108825600A (en) | 2018-11-16 |
| CN108825600B 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) |
Citations (4)
| 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 |
| 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 |
-
2018
- 2018-06-15 CN CN201810623977.7A patent/CN108825600B/en active Active
Patent Citations (4)
| 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 |
| 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 |
|---|---|
| CN108825600B (en) | 2021-02-19 |
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| GR01 | Patent grant | ||
| GR01 | Patent grant |