CN102887234A - 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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- CN102887234A CN102887234A CN2012104175769A CN201210417576A CN102887234A CN 102887234 A CN102887234 A CN 102887234A CN 2012104175769 A CN2012104175769 A CN 2012104175769A CN 201210417576 A CN201210417576 A CN 201210417576A CN 102887234 A CN102887234 A CN 102887234A
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- end cover
- sight vane
- thread gluing
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- 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 for space craft fast aeration expansion film support pipe.
Background technology
The inflating expanded film support pipe of space craft is mainly used on satellite and the lunar spacecraft, and its function overhangs capacity weight for passing through the inflating expanded of inflated tube, propping up, and overhangs a camera or magnetic detecting set as propping up.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 the expansion is restricted, duration of run is long.
Summary of the invention
The objective of the invention is for solving the existing inflating expanded film support pipe of space craft is mechanical deployed configuration, the weight of structure self is large, mechanical joint expansion reliability is lower, the problem that length after the expansion is restricted, duration of run is long is launched the film support pipe and provide a kind of for the space craft fast aeration.
Of the present invention being achieved through the following technical solutions:
The present invention includes the gather qi together cylinder, upper end cover, airflow duct, the folding film pipe, sight vane, clip, the sight vane conduit, interior glue ring, external adhesive ring, the 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 that communicates with the inner chamber of cylindrical shell, be provided with at least three bottom end cover tapped bore that communicate with the inner chamber of gather qi together cylinder along same circumference uniform distribution on the bottom end cover, be laid with three hangers on the circumference of bottom end cover, 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, the sight vane conduit is arranged in the airflow duct, the lateral wall of upper end cover is provided with circular groove, interior glue ring is arranged in the circular groove, one end of folding film pipe is enclosed within on the upper end cover, the other end of folding film pipe is closed top, external adhesive ring is enclosed within on the folding film pipe, and external adhesive ring and interior glue ring over against, clip is stuck on the external adhesive ring, sight vane is vertically set on the inwall at closed top, and sight vane is captiveed joint 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 flange, the adapter that is threaded of each lower tapped bore, the one end docking of thread gluing hook and thread gluing hair also is fixed on the closed top exterior walls, the joint of thread gluing hook and thread gluing hair is positioned at the center at closed top, and 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 the film support pipe, and expansion process is reliable and stable, and maximization that can implementation structure, namely forms long deployed configuration, and length of run is unrestricted; Because it is to launch by air-flow that the folding film pipe launches, therefore, duration of run is short.That the present invention also has is lightweight, volume after folding is little, the low characteristics of emission delivery cost.
Description of drawings
Fig. 1 is integral structure master cutaway view 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 integral structure master cutaway view of the present invention (folding film pipe 5 is deployed condition, and sight vane 6 breaks away 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 breaks away 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 that communicates with the inner chamber of cylindrical shell 1-1, bottom end cover 1-2 is upper to be 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, be laid with three hanger 1-2-2 on the circumference of bottom end cover 1-2, 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 the airflow duct 4, the lateral wall of upper end cover 3 is provided with circular groove 3-3, interior glue ring 11 is arranged among the circular groove 3-3, one end of folding film pipe 5 is enclosed within on the 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 the folding film pipe 5, and external adhesive ring 12 and interior glue ring 11 over against, clip 7 is stuck on the external adhesive ring 12, sight vane 6 is vertically set on the inwall of closed top 5-1, and sight vane 6 is captiveed joint 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 flange 2, each lower tapped bore 2-1 is threaded one and takes over 2, the one end docking of thread gluing hook 13 and thread gluing hair 14 also is fixed on the 5-1 outer wall of closed top, the joint of thread gluing hook 13 and thread gluing hair 14 is positioned at the center of closed top 5-1, and 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 the space flight phenol formaldehyde foam.Cross section after folding film pipe 5 folds is rectangle, and the cross section after folding film pipe 5 launches is circular.Height after folding film pipe 5 folds and the equal in length of airflow duct 4.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 is so that the film support pipe energy linear running after inflating expanded is avoided the 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, so that high pressure draft passes through fast, 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 the 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, longitudinally be provided with several oblique strap stiffeners 10 between every adjacent two stringers 9, article two, oblique strap stiffener 10 end to end being crisscross arranged of several between the stringer 9, every several oblique strap stiffener 10 is pasted together with folding film pipe 5.Design prevents the 5 local explosions of folding film pipe 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 all is connected with source of the gas by pipeline, when needs launch the film support pipe, start source of the gas, air-flow through take over 2, cylindrical shell 1-1 inner chamber, upper end cover air extractor vent 3-1 jack-up sight vane 6, after sight vane 6 breaks away from sight vane conduit 8, folding film pipe 5 launches rapidly, and whole expansion process is in 2 seconds.
Claims (6)
1. one kind is used for space craft fast aeration expansion 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) that communicates with the inner chamber of cylindrical shell (1-1), bottom end cover (1-2) is upper to be 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, be laid with three hangers (1-2-2) on the circumference of bottom end cover (1-2), 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 the 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 the circular groove (3-3), one end of folding film pipe (5) is enclosed within on the 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 the folding film pipe (5), and external adhesive ring (12) and interior glue ring (11) over against, clip (7) is stuck on the external adhesive ring (12), sight vane (6) is vertically set on the inwall of closed top (5-1), and sight vane (6) is captiveed joint 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 flange (2), each lower tapped bore (2-1) is threaded one and takes over (2), the one end docking of thread gluing hook (13) and thread gluing hair (14) also 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), and thread gluing hair (14) bonds together with the other end of thread gluing hook (13).
2. described for space craft fast aeration expansion film support pipe according to claim 1, it is characterized in that: the cross sectional shape of described sight vane (6) is " ten " font, and " ten " font of the intracavity section shape of sight vane conduit (8) and sight vane (6) matches.
3. described for space craft fast aeration expansion film support pipe according to claim 1 and 2, 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. described for space craft fast aeration expansion film support pipe according to claim 3, it is characterized in that: the quantity of described adapter (2) is four.
5. described for space craft fast aeration expansion 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. described for space craft fast aeration expansion film support pipe according to claim 5, it is characterized in that: described support tube also comprises several oblique strap stiffeners (10), longitudinally be provided with several oblique strap stiffeners (10) between every adjacent two stringers (9), article two, end to end being crisscross arranged of several oblique strap stiffeners (10) between the 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 |
|---|---|---|---|
| CN201210417576.9A CN102887234B (en) | 2012-10-26 | 2012-10-26 | Rapidly-inflatable-deployment thin-film support tube for space craft |
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| Publication Number | Publication Date |
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| CN102887234A true CN102887234A (en) | 2013-01-23 |
| CN102887234B 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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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103466197A (en) * | 2013-09-26 | 2013-12-25 | 中国空间技术研究院 | Supporting packaging structure oriented to solar sail adopting inflatable auxiliary self-rebounding supporting arm |
| CN104149991A (en) * | 2014-08-06 | 2014-11-19 | 哈尔滨工业大学 | Inner container for controllable inflation unfolding supporting arms of spacecraft |
| CN105292524A (en) * | 2015-11-20 | 2016-02-03 | 成都尔珏科技有限公司 | Externally-expanding gradual-change inflatable docking unit used for outer space |
| CN110450986A (en) * | 2019-08-14 | 2019-11-15 | 上海卫星工程研究所 | Foldable inflating device and its application method suitable for spacecraft |
| 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 |
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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 |
| US20090019784A1 (en) * | 2007-07-20 | 2009-01-22 | Tinker Michael L | Foam Rigidized Inflatable Structural Assemblies |
| US20090200427A1 (en) * | 2004-10-29 | 2009-08-13 | Eads Space Transportation Sas | Control device for deployment of inflatable structures |
| CN102243038A (en) * | 2010-09-21 | 2011-11-16 | 哈尔滨工业大学 | Rapidly-controlled aeration releasing mechanism |
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| US20040046085A1 (en) * | 2002-08-29 | 2004-03-11 | L'garde, Inc. | Deployable inflatable boom and methods for packaging and deploying a deployable inflatable boom |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103466197A (en) * | 2013-09-26 | 2013-12-25 | 中国空间技术研究院 | Supporting packaging structure oriented to solar sail adopting inflatable auxiliary self-rebounding supporting arm |
| CN104149991A (en) * | 2014-08-06 | 2014-11-19 | 哈尔滨工业大学 | Inner container for controllable inflation unfolding supporting arms of spacecraft |
| CN105292524A (en) * | 2015-11-20 | 2016-02-03 | 成都尔珏科技有限公司 | Externally-expanding gradual-change inflatable docking unit used for outer 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 |
| CN110450986A (en) * | 2019-08-14 | 2019-11-15 | 上海卫星工程研究所 | Foldable inflating device and its application method suitable for spacecraft |
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| CN102887234B (en) | 2014-08-13 |
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