CN102887234B - Rapidly-inflatable-deployment thin-film support tube for space craft - Google Patents
Rapidly-inflatable-deployment thin-film support tube for space craft Download PDFInfo
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- CN102887234B CN102887234B CN201210417576.9A CN201210417576A CN102887234B CN 102887234 B CN102887234 B CN 102887234B CN 201210417576 A CN201210417576 A CN 201210417576A CN 102887234 B CN102887234 B CN 102887234B
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- end cover
- sight vane
- thread gluing
- deployment
- space craft
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Abstract
The invention discloses a rapidly-inflatable-deployment thin-film support tube for a space craft, and relates to an inflatable-deployment thin-film support tube for a space craft, for solving the problems of high self-weight, limit on the length after deployment, and long deployment time of the present inflatable-deployment thin-film support tube for a space craft due to a mechanical deployment structure. According to the invention, an upper end cover is arranged at the upper end of a barrel body and in threaded connection with the barrel body; an airflow guide tube is vertically arranged at the centre of the upper end surface of the upper end cover; the inner cavity of the airflow guide tube is connected with an air vent; one end of a folding thin-film tube is sleeved on the upper end cover; one end of the folding thin-film tube is fastened with the upper end cover via a hoop, and the other end of the folding thin-film tube is a closed-type top; a direction indicator is vertically arranged on the inner wall of the closed-type top; the section shape of the direction indicator is fitted with the section shape of the inner cavity of a direction indicator guide tube; at least three connection tubes are arranged on the outer end surface of a flange; and each lower thread hole is in threaded connection with one connection tube. The rapidly-inflatable-deployment thin-film support tube disclosed by the invention is used for supporting various micro cameras and various magnetometers on satellite detectors and lunar detectors.
Description
Technical field
The present invention relates to the inflating expanded film support pipe of a kind of space craft, be specifically related to a kind of space craft fast aeration and launch film support pipe.
Background technology
The inflating expanded film support pipe of space craft is mainly used on satellite and lunar spacecraft, and its function, for passing through the inflating expanded of inflated tube, is propped up and overhanged capacity weight, as propped up, overhangs a camera or magnetic detecting set.Existing technology mainly adopts mechanical deployed configuration, and the weight of structure self is larger, and mechanical joint expansion reliability is lower, and the length after expansion is restricted, duration of run is long.
Summary of the invention
The object of the invention is for solving the inflating expanded film support pipe of existing space craft is mechanical deployed configuration, the weight of structure self is large, mechanical joint expansion reliability is lower, the problem that length after expansion is restricted, duration of run is long, and provide a kind of space craft fast aeration to launch film support pipe.
Of the present invention being achieved through the following technical solutions:
The present invention includes gather qi together cylinder, upper end cover, airflow duct, folding film pipe, sight vane, clip, sight vane conduit, interior glue ring, external adhesive ring, thread gluing hook, thread gluing hair and at least three adapters, described gather qi together cylinder comprises cylindrical shell and bottom end cover, bottom end cover is arranged on the lower end of cylindrical shell, and cylindrical shell and bottom end cover are made one, described upper end cover is arranged on the upper end of cylindrical shell, and upper end cover is connected with cylinder screw, upper end cover is provided with the upper end cover air extractor vent communicating with the inner chamber of cylindrical shell, on bottom end cover, along same circumference uniform distribution, be provided with at least three bottom end cover tapped bore that communicate with the inner chamber of gather qi together cylinder, on the circumference of bottom end cover, be laid with three hangers, airflow duct is vertically set on the center, upper surface of upper end cover, the inner chamber of airflow duct communicates with air extractor vent, sight vane conduit is arranged in airflow duct, the lateral wall of upper end cover is provided with circular groove, interior glue ring is arranged in circular groove, one end of folding film pipe is enclosed within on upper end cover, the other end of folding film pipe is closed top, external adhesive ring is enclosed within on folding film pipe, and external adhesive ring and interior glue ring over against, clip is stuck on external adhesive ring, sight vane is vertically set on the inwall at closed top, and sight vane is fixedly connected with the inwall at closed top, the intracavity section shape of the cross sectional shape of sight vane and sight vane conduit matches, at least three adapters are arranged on the outer face of bottom end cover, the adapter that is threaded of each bottom end cover tapped bore, one end of thread gluing hook and thread gluing hair is docked and is fixed in closed top exterior walls, the joint of thread gluing hook and thread gluing hair is positioned at the center at closed top, the other end of thread gluing hair and thread gluing hook bonds together.
The present invention has following effect:
The present invention adopts the mode of inflation will launch film support pipe, and expansion process is reliable and stable, and maximization that can implementation structure, forms longer deployed configuration, and length of run is unrestricted; Due to folding film pipe, launching is to launch by air-flow, and therefore, duration of run is short.That the present invention also has is lightweight, volume after folding is little, the low feature of transmitting delivery cost.
Accompanying drawing explanation
Fig. 1 is the main cutaway view of integral structure of the present invention (folding film pipe 5 is folded state, and sight vane 6 is arranged in airflow duct 4); Fig. 2 is external structure front view of the present invention (folding film pipe 5 is folded state, and sight vane 6 is arranged in airflow duct 4); Fig. 3 is the main cutaway view of integral structure of the present invention (folding film pipe 5 is deployed condition, and sight vane 6 departs from airflow duct 4, removes thread gluing hook 13 and thread gluing hair 14); Fig. 4 is external structure front view of the present invention (folding film pipe 5 is deployed condition, and sight vane 6 departs from airflow duct 4, removes thread gluing hook 13 and thread gluing hair 14); Fig. 5 is the section drawing of sight vane 6 and airflow duct 4 in the specific embodiment two; Fig. 6 is the birds-eye view of bottom end cover 1-2.
The specific embodiment
The specific embodiment one: in conjunction with Fig. 1, Fig. 3 and Fig. 6 illustrate present embodiment, present embodiment comprises gather qi together cylinder 1, upper end cover 3, airflow duct 4, folding film pipe 5, sight vane 6, clip 7, sight vane conduit 8, interior glue ring 11, external adhesive ring 12, thread gluing hook 13, thread gluing hair 14 and at least three adapters 2, gather qi together cylinder 1 comprises cylindrical shell 1-1 and bottom end cover 1-2, bottom end cover 1-2 is arranged on the lower end of cylindrical shell 1-1, and cylindrical shell 1-1 and bottom end cover 1-2 make one, described upper end cover 3 is arranged on the upper end of cylindrical shell 1-1, and upper end cover 3 is threaded with cylindrical shell 1-1, upper end cover 3 is provided with the upper end cover air extractor vent 3-1 communicating with the inner chamber of cylindrical shell 1-1, bottom end cover 1-2 is upper is provided with at least three bottom end cover tapped bore 1-2-1 that communicate with the inner chamber of gather qi together cylinder 1 along same circumference uniform distribution, on the circumference of bottom end cover 1-2, be laid with three hanger 1-2-2, three hanger 1-2-2 are used for connecting satelloid, airflow duct 4 is vertically set on the center, upper surface of upper end cover 3, the inner chamber of airflow duct 4 communicates with air extractor vent 3-1, sight vane conduit 8 is arranged in airflow duct 4, the lateral wall of upper end cover 3 is provided with circular groove 3-3, interior glue ring 11 is arranged in circular groove 3-3, one end of folding film pipe 5 is enclosed within on upper end cover 3, the other end of folding film pipe 5 is closed top 5-1, external adhesive ring 12 is enclosed within on folding film pipe 5, and external adhesive ring 12 and interior glue ring 11 over against, clip 7 is stuck on external adhesive ring 12, sight vane 6 is vertically set on the inwall of closed top 5-1, and sight vane 6 is fixedly connected with the inwall of closed top 5-1, the intracavity section shape of the cross sectional shape of sight vane 6 and sight vane conduit 8 matches, taking over 2 at least three is arranged on the outer face of bottom end cover 1-2, each bottom end cover tapped bore 1-2-1 is threaded one and takes over 2, one end of thread gluing hook 13 and thread gluing hair 14 is docked and is fixed on the 5-1 outer wall of closed top, thread gluing hook 13 is positioned at 5-1 center, closed top with the joint of thread gluing hair 14, thread gluing hair 14 bonds together with the other end of thread gluing hook 13.Thread gluing hair 14 and thread gluing hook 13 are used for fixing lifts thing.The material of sight vane 6 adopts space flight phenol formaldehyde foam.Cross section after folding film pipe 5 is folding is rectangle, and the cross section after folding film pipe 5 launches is circular.Height after folding film pipe 5 is folding and airflow duct 4 equal in length.The material of folding film pipe 5 is polyimide, polyimide high temperature-resistant, low temperature resistant, withstand voltage.During folding film pipe 5 folded state, sight vane 6 is positioned at sight vane conduit 8.
The specific embodiment two: in conjunction with Fig. 5, present embodiment is described, the cross sectional shape of the sight vane 6 of present embodiment is " ten " font, and " ten " font of the intracavity section shape of sight vane conduit 8 and sight vane 6 matches." ten " word shape makes the film support pipe energy linear running after inflating expanded, avoids film support tubotorsion.Other composition and annexation are identical with the specific embodiment one.
The specific embodiment three: in conjunction with Fig. 6, present embodiment is described, the inner chamber bottom face of the upper end cover 3 of present embodiment and corresponding position, cylindrical shell 1-1 upper surface are provided with annular groove 3-2.Other composition and annexation are identical with the specific embodiment one or two.
The specific embodiment four: in conjunction with Fig. 1～Fig. 4, present embodiment is described, the quantity of the adapter 2 of present embodiment is four.The quantity of adapter 2 increases, and high pressure draft is passed through fast, and folding film pipe 5 is launched rapidly.Other composition and annexation are identical with the specific embodiment one.Other composition and annexation are identical with the specific embodiment three.
The specific embodiment five: present embodiment is described in conjunction with Fig. 4, the support tube of present embodiment also comprises four stringers 9, article four, stringer 9 is along the uniform setting of circumferential outer surface of folding film pipe 5, and every stringer 9 is pasted together with folding film pipe 5.Be designed to like this increase the rigidity of folding film pipe 5, can prevent that the high pressure of moment generation from making folding film pipe 5 explosion in the process of launching simultaneously.Other composition and annexation are identical with the specific embodiment four.
The specific embodiment six: present embodiment is described in conjunction with Fig. 4, the support tube of present embodiment also comprises several oblique strap stiffeners 10, between every adjacent two stringers 9, be longitudinally provided with several oblique strap stiffeners 10, article two, end to end being crisscross arranged of the oblique strap stiffener 10 of several between stringer 9, every several oblique strap stiffener 10 is pasted together with folding film pipe 5.Design prevents the local explosion of folding film pipe 5 like this.Other composition and annexation are identical with the specific embodiment five.
Principle of work of the present invention: each is taken over 2 and is all connected with source of the gas by pipeline, when needs launch film support pipe, start source of the gas, air-flow through taking over 2, cylindrical shell 1-1 inner chamber, upper end cover air extractor vent 3-1 jack-up sight vane 6, sight vane 6 departs from after sight vane conduit 8, folding film pipe 5 launches rapidly, and whole expansion process is in 2 seconds.
Claims (6)
1. a space craft fast aeration is launched film support pipe, described support tube comprises gather qi together cylinder (1), upper end cover (3), airflow duct (4), folding film pipe (5), sight vane (6), clip (7), sight vane conduit (8), interior glue ring (11), external adhesive ring (12), thread gluing hook (13), thread gluing hair (14) and at least three adapters (2), it is characterized in that: described gather qi together cylinder (1) comprises cylindrical shell (1-1) and bottom end cover (1-2), bottom end cover (1-2) is arranged on the lower end of cylindrical shell (1-1), and cylindrical shell (1-1) is made one with bottom end cover (1-2), described upper end cover (3) is arranged on the upper end of cylindrical shell (1-1), and upper end cover (3) is threaded with cylindrical shell (1-1), upper end cover (3) is provided with the upper end cover air extractor vent (3-1) communicating with the inner chamber of cylindrical shell (1-1), bottom end cover (1-2) is upper is provided with at least three bottom end cover tapped bore (1-2-1) that communicate with the inner chamber of gather qi together cylinder (1) along same circumference uniform distribution, on the circumference of bottom end cover (1-2), be laid with three hangers (1-2-2), airflow duct (4) is vertically set on the center, upper surface of upper end cover (3), the inner chamber of airflow duct (4) communicates with air extractor vent (3-1), sight vane conduit (8) is arranged in airflow duct (4), the lateral wall of upper end cover (3) is provided with circular groove (3-3), interior glue ring (11) is arranged in circular groove (3-3), one end of folding film pipe (5) is enclosed within on upper end cover (3), the other end of folding film pipe (5) is closed top (5-1), external adhesive ring (12) is enclosed within on folding film pipe (5), and external adhesive ring (12) and interior glue ring (11) over against, clip (7) is stuck on external adhesive ring (12), sight vane (6) is vertically set on the inwall of closed top (5-1), and sight vane (6) is fixedly connected with the inwall of closed top (5-1), the intracavity section shape of the cross sectional shape of sight vane (6) and sight vane conduit (8) matches, at least three adapters (2) are arranged on the outer face of bottom end cover (1-2), each bottom end cover tapped bore (1-2-1) is threaded one and takes over (2), one end of thread gluing hook (13) and thread gluing hair (14) is docked and is fixed on the outer wall of closed top (5-1), the joint of thread gluing hook (13) and thread gluing hair (14) is positioned at the center of closed top (5-1), thread gluing hair (14) bonds together with the other end of thread gluing hook (13).
2. space craft fast aeration is launched film support pipe according to claim 1, it is characterized in that: the cross sectional shape of described sight vane (6) is " ten " font, " ten " font of the intracavity section shape of sight vane conduit (8) and sight vane (6) matches.
3. according to space craft fast aeration described in claim 1 or 2, launch film support pipe, it is characterized in that: the inner chamber bottom face of described upper end cover (3) and cylindrical shell (1-1) corresponding position, upper surface are provided with annular groove (3-2).
4. space craft fast aeration is launched film support pipe according to claim 3, it is characterized in that: the quantity of described adapter (2) is four.
5. space craft fast aeration is launched film support pipe according to claim 4, it is characterized in that: described support tube also comprises four stringers (9), article four, stringer (9) is along the uniform setting of circumferential outer surface of folding film pipe (5), and every stringer (9) is pasted together with folding film pipe (5).
6. space craft fast aeration is launched film support pipe according to claim 5, it is characterized in that: described support tube also comprises several oblique strap stiffeners (10), between every adjacent two stringers (9), be longitudinally provided with several oblique strap stiffeners (10), article two, end to end being crisscross arranged of several oblique strap stiffeners (10) between stringer (9), every oblique strap stiffener (10) is pasted together with folding film pipe (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210417576.9A CN102887234B (en) | 2012-10-26 | 2012-10-26 | Rapidly-inflatable-deployment thin-film support tube for space craft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210417576.9A CN102887234B (en) | 2012-10-26 | 2012-10-26 | Rapidly-inflatable-deployment thin-film support tube for space craft |
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| CN102887234A CN102887234A (en) | 2013-01-23 |
| CN102887234B true CN102887234B (en) | 2014-08-13 |
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| CN201210417576.9A Active CN102887234B (en) | 2012-10-26 | 2012-10-26 | Rapidly-inflatable-deployment thin-film support tube for space craft |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103466197B (en) * | 2013-09-26 | 2015-05-27 | 中国空间技术研究院 | Supporting packaging structure oriented to solar sail adopting inflatable auxiliary self-rebounding supporting arm |
| CN104149991B (en) * | 2014-08-06 | 2016-02-24 | 哈尔滨工业大学 | A kind of space vehicle controllable inflation launches hold-down arm inner bag |
| CN105292524B (en) * | 2015-11-20 | 2018-04-27 | 朱正直 | Gradual change inflatable docking facilities are extended out for space |
| RU2714986C2 (en) * | 2018-08-13 | 2020-02-21 | Публичное акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева | Device for extending payload from spacecraft by supercharging expandable tubular structure |
| CN110450986B (en) * | 2019-08-14 | 2021-02-19 | 上海卫星工程研究所 | Folding inflation device suitable for spacecraft and use method thereof |
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| CN1751965A (en) * | 2005-10-31 | 2006-03-29 | 哈尔滨工业大学 | Ultraviolet light rigidization composite film capable of aeration expanding outer space structure |
| CN102243038A (en) * | 2010-09-21 | 2011-11-16 | 哈尔滨工业大学 | Rapidly-controlled aeration releasing mechanism |
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| US6786456B2 (en) * | 2002-08-29 | 2004-09-07 | L'garde, Inc. | Deployable inflatable boom and methods for packaging and deploying a deployable inflatable boom |
| FR2877315B1 (en) * | 2004-10-29 | 2007-02-02 | Eads Space Transp Sas Soc Par | DEVICE FOR CONTROLLING THE DEPLOYMENT OF INFLATABLE STRUCTURES |
| US7735265B2 (en) * | 2007-07-20 | 2010-06-15 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Foam rigidized inflatable structural assemblies |
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| CN1751965A (en) * | 2005-10-31 | 2006-03-29 | 哈尔滨工业大学 | Ultraviolet light rigidization composite film capable of aeration expanding outer space structure |
| CN102243038A (en) * | 2010-09-21 | 2011-11-16 | 哈尔滨工业大学 | Rapidly-controlled aeration releasing mechanism |
Non-Patent Citations (2)
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| 王长国.空间充气薄膜的褶皱分析.《力学学报》.2008,第40卷(第3期),第331-338页. |
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| CN102887234A (en) | 2013-01-23 |
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