CN1672914A - Composite thermosetting film for inflated spatial expanded structure and its making and rigidizing process - Google Patents
Composite thermosetting film for inflated spatial expanded structure and its making and rigidizing process Download PDFInfo
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- CN1672914A CN1672914A CN 200510009885 CN200510009885A CN1672914A CN 1672914 A CN1672914 A CN 1672914A CN 200510009885 CN200510009885 CN 200510009885 CN 200510009885 A CN200510009885 A CN 200510009885A CN 1672914 A CN1672914 A CN 1672914A
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Abstract
The present invention relates to composite film and its making and rigidizing process. The composite thermoset film for inflated spatial expanded structure includes inner gas blocking layer, rigidized layer, heating layer, and outer heat insulating layer successively from inside to outside. Fiber fabric woven in two or three directions is soaked in thermoset resin to form the pre-soaked fabric; and metal foil or metal filament is set between two layers of polyimide film with thermoset adhesive painted in the inner layer and formed via heating and pressurizing in a hot press. Perforated polyimide film or polyester film with aluminum plated to the one or two sides is adhered to dacron net and formed into shape the same as the required inner gas blocking layer. The composite thermoset film of the present invention has the advantages of light weight, small occupied emitting volume, lowered emitting cost and high reliability.
Description
Technical field:
The making, the thermosetting that the present invention relates to a kind of laminated film and this film have just been changed method.
Background technology:
In the modern national defense field, the competition of defense force has more and more developed into the competition of space technology, and following war will depend on contention of air supremacy to a great extent.And the competition of following space technology and control of the air, then more and more stronger large-scale (or ultra-large type) space structure constructing technology that depends on, these large space structures are large space antenna, solar array for example, and large-scale space-based weapon system optimal in structure, empty day aircraft etc., in fields such as China's space flight and national defence wilderness demand is arranged all.Development large space structure technology, significant to improving Future in China in competitiveness and empty day operation ability of international space technology.Owing to be subjected to the restriction of carrying capacity, how to make up spacecraft cheaply in the space simultaneously, be the focus of Space Science and Technology research always.Utilizing the space structure technology of inflatable form can relatively easily be built into large space structure, can alleviate throw-weight and emission volume simultaneously, is a kind of effective solution route that can make up large space structure and reduce emission (delivery) cost.This technology has become the focus of international space technical research at present, has released a lot of test products, and has carried out the verification experimental verification of part correlation.But, also there is not directly the relevant data in field therewith from the domestic document of publishing.And external data also mostly is conceptual narration, and key technology still is in the secret stage.
Summary of the invention:
The objective of the invention is for filling up the blank of the large space structure product that can alleviate throw-weight and emission volume at present, a kind of composite thermosetting film and making and rigidizing process that is used for inflated spatial expanded structure is provided, composite thermosetting film of the present invention has light weight, take the emission volume little, reduce launch cost, low, the high reliability features of expense; The making and rigidizing process of composite thermosetting film of the present invention has the characteristics of suitable space environment, good forming effect.Composite thermosetting film of the present invention is made up of internal gas barrier layer 1, firmization layer 2, zone of heating 3, outer insulative layer 4; Firmization layer 2 is arranged on the outside of internal gas barrier layer 1, and zone of heating 3 is arranged on the outside of firmization layer 2, and outer insulative layer 4 is arranged on the outside of zone of heating 3.The thickness of internal gas barrier layer 1 is 0.025mm～0.05mm; The thickness of firmization layer 2 is 0.1～0.8mm; The thickness of zone of heating 3 is 0.1～0.3mm; The thickness of outer insulative layer 4 is 0.5～1mm.The making and rigidizing process of composite thermosetting film of the present invention is: one, the making of internal gas barrier layer 1: Kapton or polyester film are made spherical, tubular or tubulose (shape after inflating expanded); Two, the making of firmization layer 2: with two to or the fiber cloth of three-dimensional braiding immerse thermosetting resin, make preimpregnation cloth, make the shape identical again with internal gas barrier layer 1, be set in the outside of internal gas barrier layer 1; Three, the making of zone of heating 3: metal forming or filament are placed in the middle of the two layers of polyimide film that the inboard scribbles the thermosetting adhesive, be placed on again and heat extrusion forming on the hot press, make the shape identical then, be set in the outside of firmization layer 2 with internal gas barrier layer 1; Four, the making of outer insulative layer 4: aluminize Kapton or polyester film and the terylene net of punching of single or double is bonded together, makes the shape identical, be set in the outside of zone of heating 3 with internal gas barrier layer 1; Make internal gas barrier layer 1, firmization layer 2, zone of heating 3, outer insulative layer 4 form a sealed whole; Five, firmization: after composite thermosetting film is sent into space, at first connect power supply zone of heating 3 is heated to 20 ℃, make its flexible increasing,, it is fully launched, improve temperature then firmization layer 2 is solidified again to the composite thermosetting film inner inflatable.Composite thermosetting film of the present invention generally is called inflatable outer space structure.Composite thermosetting film of the present invention is to make a kind of novel outer space structure that forms by the flexible thin-film material, not only in light weight and the emission before be flexible, can FOLD AND PACK, this structure is stored in the carrier rocket launching pod with folding form when emission, only take very little emission volume, after being transmitted on the track, then make structure inflating expanded by charge into gas to inside configuration, utilize material or structure just to change the technology moulding, generate the shape of design in advance, and realize its functional requirement.Compare with the outer space structure of traditional form, inflatable outer space structure has incomparable advantage in following several respects: light weight, take the emission volume little, expense is low, reliability is high.The making and rigidizing process of composite thermosetting film of the present invention has the advantage of suitable space environment, good forming effect.At present, the outer space structure of inflatable form receives increasing concern in the world, and it has important use to be worth on outer space structures such as the big antenna of space, solar energy sailboard, solar energy array and space residence.
Description of drawings:
Fig. 1 is an overall structure schematic diagram of the present invention.
The specific embodiment:
The specific embodiment one: the composite thermosetting film of (referring to Fig. 1) present embodiment is made up of internal gas barrier layer 1, firmization layer 2, zone of heating 3, outer insulative layer 4; Firmization layer 2 is arranged on the outside of internal gas barrier layer 1, and zone of heating 3 is arranged on the outside of firmization layer 2, and outer insulative layer 4 is arranged on the outside of zone of heating 3.The thickness of internal gas barrier layer 1 is 0.025mm～0.05mm; The thickness of firmization layer 2 is 0.1～0.8mm; The thickness of zone of heating 3 is 0.1～0.3mm; The thickness of outer insulative layer 4 is 0.5～1mm.The making and rigidizing process of present embodiment composite thermosetting film is: one, the making of internal gas barrier layer 1: Kapton or polyester film are made spherical, tubular or tubulose (shape after inflating expanded); Two, the making of firmization layer 2: with two to or the fiber cloth of three-dimensional braiding immerse thermosetting resin, make preimpregnation cloth, make the shape identical again with internal gas barrier layer 1, be set in the outside of internal gas barrier layer 1; Three, the making of zone of heating 3: metal forming or filament are placed in the middle of the two layers of polyimide film that the inboard scribbles the thermosetting adhesive, be placed on again and heat extrusion forming on the hot press, make the shape identical then, be set in the outside of firmization layer 2 with internal gas barrier layer 1; Four, the making of outer insulative layer 4: aluminize Kapton or polyester film and the terylene net of punching of single or double is bonded together, makes the shape identical, be set in the outside of zone of heating 3 with internal gas barrier layer 1; Make internal gas barrier layer 1, firmization layer 2, zone of heating 3, outer insulative layer 4 form a sealed whole; Five, firmization: after composite thermosetting film is sent into space, at first connect power supply zone of heating 3 is heated to 20 ℃, make its flexible increasing,, it is fully launched, improve temperature then firmization layer 2 is solidified again to the composite thermosetting film inner inflatable.Described Kapton or polyester film are Kapton film or the Mylar film that E.I.Du Pont Company produces.Described fiber cloth is the 3K of two-way braiding, the plain of T300 and Kevlar shuffling.Described resin is an epoxy resin.The solidification temperature of described firmization layer 2 is 100～140 ℃.Be 0.5～2 hour the hardening time of described firmization layer 2.The heating power of described zone of heating 3 is 300～520W/m
2Present embodiment internal gas barrier layer is the most inboard structure, and its effect is to prevent that internal gas from leaking, and has the effect that keeps gas and prevent structure bonding when packing.The material selection of internal gas barrier layer is suitable for the folded thin-film material of folding of steric requirements, and the material that can select for use has: Kapton, polyester film etc.Firmization layer by material prepreg (by two to or the uncured resin of fiber cloth preimpregnation of three-dimensional establishment make) constitute, crosslinking curing takes place and obtains hard material in the back resin chemistry that is heated, be used to support total, the appropriate design of this layer material is to realize material and the high performance key of structure.Cure cycle depends on selected matrix material, for dozens of minutes arrives several hrs.Reinforcing material can be selected pbo fiber, carbon fiber, aramid fiber, glass fibre etc. for use, when these fibers and thermosetting resin such as curable epoxide, can obtain extremely hard laminated material, made high-performance thermosetting composite has shown excellent high-strength high hardware features.But merely improve the intensity and the hardness of material and be unfavorable for integrally-built performance, material is really up to the mark, and breach appears in fiber easily when folding, and the ability of resisting space junk or particle hits simultaneously also can descend.In order to reduce the damage of fiber when folding, the modulus of fiber should not be too big.Composite is heating and curing and temperature distortion in order to reduce, and fiber should have and is bordering on zero thermal coefficient of expansion.The composite thermosetting film structure applications of inflatable deployable need the long time to make, assemble and test before emission, thereby material prepreg must have long storage life in outer space structure.So resin system is selected the resin system with long latency for use, has the incubation period more than 3 months at ambient temperature.Zone of heating provides suitable temperature for launching and solidifying, and can also be used to keeping the shape of expansion tube simultaneously.When structure was launched, the heating system of embedding heated the material to about 20 ℃ earlier, and when material was heated to 20 ℃, its flexibility will increase, and this moment is inflating expanded, and then heats this structure to solidification temperature.The heating of zone of heating is controlled, predictable, and the energy that zone of heating needs comes from the power supply of spacecraft.The effect of outer insulative layer (MLI layer) is in order to resist abominable space environment, also is simultaneously for isolated inner heat leakage, keeps inner solidification temperature.The MLI layer designs accordingly according to different space environments and task needs.
Claims (10)
1, a kind of composite thermosetting film that is used for inflated spatial expanded structure, it is made up of internal gas barrier layer (1), firmization layer (2), zone of heating (3), outer insulative layer (4); It is characterized in that firmization layer (2) is arranged on the outside of internal gas barrier layer (1), zone of heating (3) is arranged on the outside of firmization layer (2), and outer insulative layer (4) is arranged on the outside of zone of heating (3).
2, the composite thermosetting film that is used for inflated spatial expanded structure according to claim 1, the thickness that it is characterized in that internal gas barrier layer (1) is 0.025mm～0.05mm.
3, the composite thermosetting film that is used for inflated spatial expanded structure according to claim 1 is characterized in that the thickness of firmization layer (2) is 0.1～0.8mm.
4, the composite thermosetting film that is used for inflated spatial expanded structure according to claim 1, the thickness that it is characterized in that zone of heating (3) is 0.1～0.3mm.
5, the composite thermosetting film that is used for inflated spatial expanded structure according to claim 1, the thickness that it is characterized in that outer insulative layer (4) is 0.5～1mm.
6, the making and rigidizing process of composite thermosetting film is characterized in that one, the making of internal gas barrier layer (1): Kapton or polyester film are made spherical, tubular or tubulose; Two, the making of firmization layer (2): with two to or the fiber cloth of three-dimensional braiding immerse thermosetting resin, make preimpregnation cloth, make again and the identical shape of internal gas barrier layer (1), be set in the outside of internal gas barrier layer (1); Three, the making of zone of heating (3): metal forming or filament are placed in the middle of the two layers of polyimide film that the inboard scribbles the thermosetting adhesive, be placed on again and heat extrusion forming on the hot press, make then and the identical shape of internal gas barrier layer (1), be set in the outside of firmization layer (2); Four, the making of outer insulative layer (4): aluminize Kapton or polyester film and the terylene net of punching of single or double is bonded together, makes and the identical shape of internal gas barrier layer (1), be set in the outside of zone of heating (3); Make internal gas barrier layer (1), firmization layer (2), zone of heating (3), outer insulative layer (4) form a sealed whole that is set-located; Five, firmization: after composite thermosetting film is sent into space, at first connect power supply zone of heating (3) is heated to 20 ℃, make its flexible increasing,, it is fully launched, improve temperature then firmization layer (2) is solidified again to the composite thermosetting film inner inflatable.
7, the making and rigidizing process of composite thermosetting film according to claim 6 is characterized in that described resin is an epoxy resin.
8, the making and rigidizing process of composite thermosetting film according to claim 6 is characterized in that the solidification temperature of described firmization layer (2) is 100～140 ℃.
9, the making and rigidizing process of composite thermosetting film according to claim 6 is characterized in that be 0.5～2 hour the hardening time of described firmization layer (2).
10, the making and rigidizing process of composite thermosetting film according to claim 6, the heating power that it is characterized in that described zone of heating (3) is 300～520W/m
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN100345728C (en) * | 2005-10-21 | 2007-10-31 | 哈尔滨工业大学 | Truss type rigidifying solar energy cell array of inflatable expansion |
| CN101913270A (en) * | 2010-07-23 | 2010-12-15 | 哈尔滨工业大学 | Foldable-expandable shape memory supporting pipe and preparation method thereof |
| CN102417158A (en) * | 2011-09-30 | 2012-04-18 | 哈尔滨工业大学 | Shell membrane model for forecasting bending and folding characteristics of inflatable membrane beam |
| CN102495515A (en) * | 2011-12-12 | 2012-06-13 | 中国科学院长春光学精密机械与物理研究所 | Heat-insulation cushion applicable to heat control of space camera |
| CN103241393A (en) * | 2013-05-17 | 2013-08-14 | 哈尔滨工业大学 | Spacecraft space firm docking method |
| CN103616619A (en) * | 2013-11-19 | 2014-03-05 | 北京卫星环境工程研究所 | Polyimide film insulation inspection tool on SADA support |
| CN104743144A (en) * | 2015-03-28 | 2015-07-01 | 哈尔滨工业大学 | Variable-cross-section spiral winding type gas-filled capturing manipulator |
| CN113696172A (en) * | 2021-09-08 | 2021-11-26 | 哈尔滨工业大学 | Inflatable grasper capable of rigidizing |
| CN115157805A (en) * | 2022-02-22 | 2022-10-11 | 航天科工空间工程发展有限公司 | Reversible rigidized composite film for space inflation unfolding structure |
Families Citing this family (1)
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| CN103682668B (en) * | 2013-12-18 | 2015-06-17 | 哈尔滨工业大学 | Bending-forming-based parabolic cylinder antenna reflector and method for reflector to achieve parabolic cylinder |
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| JPS5749626A (en) * | 1980-09-09 | 1982-03-23 | Yoshino Kogyosho Co Ltd | Treatment of bottle made of saturated polyester |
| FR2776485B1 (en) * | 1998-03-30 | 2000-04-28 | Michel Raymond Jean Fouquerant | ISOTHERMAL FOOTWEAR |
| JPH11286048A (en) * | 1998-04-02 | 1999-10-19 | Fuji Pureamu Kk | Laminate apparatus |
| CN2464202Y (en) * | 2001-02-23 | 2001-12-12 | 夏红宪 | Rolling type film sunshading curtain |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100345728C (en) * | 2005-10-21 | 2007-10-31 | 哈尔滨工业大学 | Truss type rigidifying solar energy cell array of inflatable expansion |
| CN101913270B (en) * | 2010-07-23 | 2012-11-21 | 哈尔滨工业大学 | Foldable-expandable shape memory supporting pipe and preparation method thereof |
| CN101913270A (en) * | 2010-07-23 | 2010-12-15 | 哈尔滨工业大学 | Foldable-expandable shape memory supporting pipe and preparation method thereof |
| CN102417158A (en) * | 2011-09-30 | 2012-04-18 | 哈尔滨工业大学 | Shell membrane model for forecasting bending and folding characteristics of inflatable membrane beam |
| CN102495515B (en) * | 2011-12-12 | 2014-01-15 | 中国科学院长春光学精密机械与物理研究所 | Heat-insulation cushion applicable to heat control of space camera |
| CN102495515A (en) * | 2011-12-12 | 2012-06-13 | 中国科学院长春光学精密机械与物理研究所 | Heat-insulation cushion applicable to heat control of space camera |
| CN103241393A (en) * | 2013-05-17 | 2013-08-14 | 哈尔滨工业大学 | Spacecraft space firm docking method |
| CN103241393B (en) * | 2013-05-17 | 2015-06-03 | 哈尔滨工业大学 | Spacecraft space firm docking method |
| CN103616619A (en) * | 2013-11-19 | 2014-03-05 | 北京卫星环境工程研究所 | Polyimide film insulation inspection tool on SADA support |
| CN103616619B (en) * | 2013-11-19 | 2016-12-07 | 北京卫星环境工程研究所 | Spacecraft solar array driving means support polyimide (PI) film insulation inspection tool |
| CN104743144A (en) * | 2015-03-28 | 2015-07-01 | 哈尔滨工业大学 | Variable-cross-section spiral winding type gas-filled capturing manipulator |
| CN113696172A (en) * | 2021-09-08 | 2021-11-26 | 哈尔滨工业大学 | Inflatable grasper capable of rigidizing |
| CN115157805A (en) * | 2022-02-22 | 2022-10-11 | 航天科工空间工程发展有限公司 | Reversible rigidized composite film for space inflation unfolding structure |
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