CN105864360A - Tensional cable assembly applied to flexible pressing and releasing device of spacecraft - Google Patents
Tensional cable assembly applied to flexible pressing and releasing device of spacecraft Download PDFInfo
- Publication number
- CN105864360A CN105864360A CN201610194295.XA CN201610194295A CN105864360A CN 105864360 A CN105864360 A CN 105864360A CN 201610194295 A CN201610194295 A CN 201610194295A CN 105864360 A CN105864360 A CN 105864360A
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- CN
- China
- Prior art keywords
- spacecraft
- rope
- release device
- pressure release
- tension cord
- 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.)
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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
- F16G—BELTS, CABLES, OR ROPES, PREDOMINANTLY USED FOR DRIVING PURPOSES; CHAINS; FITTINGS PREDOMINANTLY USED THEREFOR
- F16G11/00—Means for fastening cables or ropes to one another or to other objects; Caps or sleeves for fixing on cables or ropes
- F16G11/02—Means for fastening cables or ropes to one another or to other objects; Caps or sleeves for fixing on cables or ropes with parts deformable to grip the cable or cables; Fastening means which engage a sleeve or the like fixed on the cable
- F16G11/025—Fastening means which engage a sleeve or the like fixed on the cable, e.g. caps
-
- 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)
- Ropes Or Cables (AREA)
Abstract
The invention provides a tensional cable assembly applied to a flexible pressing and releasing device of a spacecraft. The tensional cable assembly comprises a rope, block pins clamped to the two ends of the rope, a movable end, a fixed end and fasteners, wherein the movable end and the fixed end are arranged at the two ends of the rope correspondingly, and the two block pins at the two ends of the rope are arranged in the movable end and the fixed end correspondingly; the fasteners are arranged in the movable end and the fixed end correspondingly. Compared with the prior art, the tensional cable assembly has the beneficial effects that 1, the high-strength fiber rope can be effectively fixed to the movable end and the fixed end; 2, under the condition of long-time stress, the rope cannot be dragged out from the fixed end and the movable end; 3, external connectors are simple, and assembling is convenient.
Description
Technical field
The present invention relates to a kind of tension cord assembly compressed in release device, the parts that this assembly launches after being entered the orbit by needs in spacecraft are pressed in spacecraft surface at launching phase, spacecraft is made to meet the envelope requirement of rocket trousers, a kind of tension cord assembly being applied in spacecraft in Compliant pressure release device at launching phase.
Background technology
The compression relieving mechanism of current domestic commonly used compressor arm/firer's sickle formula, its operation principle is to directly utilize the cutting knife in the thrust promotion sickle that Fire load blast produces so that it is at high speeds compressor arm is cut off.This type of compresses relieving mechanism and has following limitation: the attitude of satellite and sensitive unit can be impacted by the instantaneous big magnitude shock loading of generation, Fire load can produce corrosivity and pollution gas during getting angry, there is certain potential safety hazard in the energy having directly utilized explosive charge generation, Fire load belongs to dangerous materials makes troubles to ground storage and use, owing to disposably the work feature of not reproducible utilization of Fire load and compressor arm makes the cost of ground experiment increase.
And Compliant pressure release device is designed with Compliant pressure element (tension cord) and the configuration mode of Fuse Type sickle (being called for short hot cutter), releasing compression constraint by hot cutter fusing tension cord, release process has pollution-free, without impact and the feature such as reusable.
Traditional tension cord assembly have employed the mode that rope knotting is fixing, but this kind of fixed form is not easy to assembling, and creep easily occurs in position time length of simultaneously tiing a knot in the case of stress, makes tension cord elongated, and thrust reduces.
In order to realize the substrate hold-down function of Compliant pressure release device, it is necessary to design a set of tension cord assembly rope effectively can fixed and schedule two ends.
Summary of the invention
For defect of the prior art, it is an object of the invention to provide the tension cord assembly being applied in spacecraft in Compliant pressure release device of a kind of substrate hold-down function that can realize Compliant pressure release device.
For solving above-mentioned technical problem, a kind of tension cord assembly being applied in spacecraft in Compliant pressure release device that the present invention provides, including: rope；Bayonet lock, described bayonet lock is connected to the two ends of described rope；Mobile terminal and fixing end, described mobile terminal and described fixing end be separately positioned on the two ends of described rope, and two described bayonet locks of described rope ends are separately positioned in described mobile terminal and described fixing end；Securing member, described securing member is separately positioned in described mobile terminal and described fixing end.
Preferably, in the cone section in two described bayonet locks of described rope ends are separately positioned on described mobile terminal and described fixing end.
Preferably, described cone section is the cone section of 16 °.
Preferably, in described cone section, it is provided with female thread.
Preferably, described female thread is M8 female thread.
Preferably, described securing member is screw, is provided with the external screw thread matched with described female thread on described screw.
Preferably, described bayonet lock is provided with groove and hole.
Preferably, the material of described rope is dyneema fiber.
Compared with prior art, beneficial effects of the present invention is as follows:
1, high strength fibre rope can effectively be fixed on mobile terminal and fixing end.
2, under long stressing conditions, rope does not haves hauls out situation from fixing end and mobile terminal.
3, external interface is simple, easy to assembly.
Accompanying drawing explanation
The detailed description made non-limiting example with reference to the following drawings by reading, the further feature purpose of the present invention and advantage will become more apparent upon.
Fig. 1 is the tension cord modular construction schematic diagram that the present invention is applied in spacecraft in Compliant pressure release device；
Fig. 2 is the tension cord assembly profile that the present invention is applied in spacecraft in Compliant pressure release device；
Fig. 3 is the tension cord assembly clamping pin structure schematic diagram that the present invention is applied in spacecraft in Compliant pressure release device；
Fig. 4 is the tension cord assembly bolt structure schematic diagram that the present invention is applied in spacecraft in Compliant pressure release device.
In figure:
1-mobile terminal 2-screw 3-bayonet lock
4-rope 5-fixing end 6-groove
7-hole 8-bores section 9-through hole
Detailed description of the invention
Below in conjunction with specific embodiment, the present invention is described in detail.Following example will assist in those skilled in the art and are further appreciated by the present invention, but limit the present invention the most in any form.It should be pointed out that, to those skilled in the art, without departing from the inventive concept of the premise, it is also possible to make some changes and improvements.These broadly fall into protection scope of the present invention.
As shown in Figure 1 to 4, a kind of tension cord assembly being applied in spacecraft in Compliant pressure release device that the present invention provides uses the fibrecord 4 of dyneema high intensity, rope 4 two ends are by the through hole 9 in the middle of bayonet lock 3, bayonet lock 3 is put into the inner chamber cone section 8 of mobile terminal 1 or fixing end 5, it is screwed into and tightens screw 2, tighten screw 2 and be pressed down against bayonet lock 3 assembly, make bayonet lock 3 move downward, under the effect of mobile terminal 1 or fixing end 5 inner chamber cone section 8, bayonet lock 3 component strain also clamps middle rope 4.That tightens that screw 2 twists is the tightest, then bayonet lock 3 is the biggest to the clamping force of tension cord, shape deforming clip guy tightening 4, it is ensured that in the case of the stress of tension cord two ends, rope 4 will not be deviate from from mobile terminal 1 and fixing end 5.
Mobile terminal 1 is outside is M14 external screw thread, and inner chamber is M8 female thread and cone section 8 that cone angle is 16 °.Fixing end 5 is outside adds flange for the face of cylinder, and inner chamber is M8 female thread and cone section 8 that cone angle is 16 °.
The cone angle that the design of bayonet lock 3 matches with fixing end 5 and mobile terminal 1, adds simultaneously and has supplied groove 6 and hole 7 to reduce its rigidity, make bayonet lock 3 be easier to deformation clamping.
Above the specific embodiment of the present invention is described.It is to be appreciated that the invention is not limited in above-mentioned particular implementation, those skilled in the art can make a variety of changes within the scope of the claims or revise, and this has no effect on the flesh and blood of the present invention.In the case of not conflicting, the feature in embodiments herein and embodiment can arbitrarily be mutually combined.
Claims (8)
1. the tension cord assembly being applied in spacecraft in Compliant pressure release device, it is characterised in that including:
Rope；
Bayonet lock, described bayonet lock is connected to the two ends of described rope；
Mobile terminal and fixing end, described mobile terminal and described fixing end are separately positioned on the two ends of described rope, described rope
Two described bayonet locks at two ends are separately positioned in described mobile terminal and described fixing end；
Securing member, described securing member is separately positioned in described mobile terminal and described fixing end.
The tension cord assembly being applied in spacecraft in Compliant pressure release device the most according to claim 1,
It is characterized in that, two described bayonet locks of described rope ends are separately positioned in described mobile terminal and described fixing end
In cone section.
The tension cord assembly being applied in spacecraft in Compliant pressure release device the most according to claim 2,
It is characterized in that, described cone section is the cone section of 16 °.
4. according to the tension cord group being applied in spacecraft in Compliant pressure release device described in Claims 2 or 3
Part, it is characterised in that be provided with female thread in described cone section.
The tension cord assembly being applied in spacecraft in Compliant pressure release device the most according to claim 4,
It is characterized in that, described female thread is M8 female thread.
The tension cord assembly being applied in spacecraft in Compliant pressure release device the most according to claim 5,
It is characterized in that, described securing member is screw, is provided with the external screw thread matched with described female thread on described screw.
The tension cord assembly being applied in spacecraft in Compliant pressure release device the most according to claim 1,
It is characterized in that, described bayonet lock is provided with groove and hole.
The tension cord assembly being applied in spacecraft in Compliant pressure release device the most according to claim 1,
It is characterized in that, the material of described rope is dyneema fiber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610194295.XA CN105864360A (en) | 2016-03-30 | 2016-03-30 | Tensional cable assembly applied to flexible pressing and releasing device of spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610194295.XA CN105864360A (en) | 2016-03-30 | 2016-03-30 | Tensional cable assembly applied to flexible pressing and releasing device of spacecraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105864360A true CN105864360A (en) | 2016-08-17 |
Family
ID=56626531
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610194295.XA Pending CN105864360A (en) | 2016-03-30 | 2016-03-30 | Tensional cable assembly applied to flexible pressing and releasing device of spacecraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105864360A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828979A (en) * | 2017-01-20 | 2017-06-13 | 北京空间飞行器总体设计部 | A kind of hot blade of big carrying compresses release device |
| CN108945529A (en) * | 2018-06-15 | 2018-12-07 | 上海卫星工程研究所 | A kind of compression release device of spaceborne deployment rod |
| CN109625328A (en) * | 2018-12-12 | 2019-04-16 | 上海卫星装备研究所 | Fuse Type compresses release device |
| CN109733646A (en) * | 2018-12-29 | 2019-05-10 | 深圳航天东方红海特卫星有限公司 | A kind of elastic compensation drawstring retaining mechanism |
| CN113334309A (en) * | 2021-05-08 | 2021-09-03 | 上海卫星工程研究所 | Thermal release pin puller structure for spacecraft |
| CN113844680A (en) * | 2021-10-15 | 2021-12-28 | 中国科学院空间应用工程与技术中心 | Push rod closing device, locating component and positioner |
| CN114985997A (en) * | 2022-02-18 | 2022-09-02 | 上海电机学院 | Hot cutting device and flexible pressing and releasing device |
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| US3524228A (en) * | 1968-07-09 | 1970-08-18 | William F Kelly | Anchor for post-tensioning prestressed concrete |
| US3732526A (en) * | 1971-06-25 | 1973-05-08 | Bendix Corp | Electrical connector with improved cable support |
| AU1225295A (en) * | 1994-02-15 | 1995-08-24 | J.J.P. Geotechnical Engineering Pty Ltd | Cone for a bolt |
| CN1305568A (en) * | 1998-07-28 | 2001-07-25 | 国际弗里希尼特斯特普公司 | Single-piece part for making cable anchoring jaw and method for making such jaw |
| US8286309B2 (en) * | 2008-06-10 | 2012-10-16 | Actuant Corporation | Median barrier cable termination |
| CN103251447A (en) * | 2007-11-13 | 2013-08-21 | 新特斯有限责任公司 | Minimally invasive cerclage system |
| CN103264775A (en) * | 2013-04-23 | 2013-08-28 | 上海卫星工程研究所 | Flexible rope pressing device and using method |
| CN203979278U (en) * | 2014-08-18 | 2014-12-03 | 山东科瑞机械制造有限公司 | Screwing type card rope seat |
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2016
- 2016-03-30 CN CN201610194295.XA patent/CN105864360A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| US3524228A (en) * | 1968-07-09 | 1970-08-18 | William F Kelly | Anchor for post-tensioning prestressed concrete |
| US3732526A (en) * | 1971-06-25 | 1973-05-08 | Bendix Corp | Electrical connector with improved cable support |
| AU1225295A (en) * | 1994-02-15 | 1995-08-24 | J.J.P. Geotechnical Engineering Pty Ltd | Cone for a bolt |
| CN1305568A (en) * | 1998-07-28 | 2001-07-25 | 国际弗里希尼特斯特普公司 | Single-piece part for making cable anchoring jaw and method for making such jaw |
| CN103251447A (en) * | 2007-11-13 | 2013-08-21 | 新特斯有限责任公司 | Minimally invasive cerclage system |
| US8286309B2 (en) * | 2008-06-10 | 2012-10-16 | Actuant Corporation | Median barrier cable termination |
| CN103264775A (en) * | 2013-04-23 | 2013-08-28 | 上海卫星工程研究所 | Flexible rope pressing device and using method |
| CN203979278U (en) * | 2014-08-18 | 2014-12-03 | 山东科瑞机械制造有限公司 | Screwing type card rope seat |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828979A (en) * | 2017-01-20 | 2017-06-13 | 北京空间飞行器总体设计部 | A kind of hot blade of big carrying compresses release device |
| CN106828979B (en) * | 2017-01-20 | 2019-06-18 | 北京空间飞行器总体设计部 | A kind of hot blade compression release device of big carrying |
| CN108945529A (en) * | 2018-06-15 | 2018-12-07 | 上海卫星工程研究所 | A kind of compression release device of spaceborne deployment rod |
| CN108945529B (en) * | 2018-06-15 | 2020-05-29 | 上海卫星工程研究所 | Compression and release device of satellite-borne unfolding rod |
| CN109625328A (en) * | 2018-12-12 | 2019-04-16 | 上海卫星装备研究所 | Fuse Type compresses release device |
| CN109733646A (en) * | 2018-12-29 | 2019-05-10 | 深圳航天东方红海特卫星有限公司 | A kind of elastic compensation drawstring retaining mechanism |
| CN109733646B (en) * | 2018-12-29 | 2022-03-18 | 深圳航天东方红海特卫星有限公司 | Elastic compensation type stay cord locking mechanism |
| CN113334309A (en) * | 2021-05-08 | 2021-09-03 | 上海卫星工程研究所 | Thermal release pin puller structure for spacecraft |
| CN113334309B (en) * | 2021-05-08 | 2022-11-11 | 上海卫星工程研究所 | Thermal release pin puller structure for spacecraft |
| CN113844680A (en) * | 2021-10-15 | 2021-12-28 | 中国科学院空间应用工程与技术中心 | Push rod closing device, locating component and positioner |
| CN113844680B (en) * | 2021-10-15 | 2022-03-25 | 中国科学院空间应用工程与技术中心 | Push rod closing device, locating component and positioner |
| CN114985997A (en) * | 2022-02-18 | 2022-09-02 | 上海电机学院 | Hot cutting device and flexible pressing and releasing device |
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| 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 |
Application publication date: 20160817 |
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| RJ01 | Rejection of invention patent application after publication |