CN101054008A - Rigidization method of thermo-setting composite film used in the space inflatable deployment structure - Google Patents
Rigidization method of thermo-setting composite film used in the space inflatable deployment structure Download PDFInfo
- Publication number
- CN101054008A CN101054008A CN 200710103666 CN200710103666A CN101054008A CN 101054008 A CN101054008 A CN 101054008A CN 200710103666 CN200710103666 CN 200710103666 CN 200710103666 A CN200710103666 A CN 200710103666A CN 101054008 A CN101054008 A CN 101054008A
- Authority
- CN
- China
- Prior art keywords
- firmization
- layer
- heating
- zone
- thermosetting film
- 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
Images
Landscapes
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
Abstract
The present invention relates to a stiffening method for thermosetting composite membrane used for the space gas-charging and outspreading structure, which relates to a stiffening method for composite membrane. The present invention is adapted for the large scale space structure to reduce the emitting weight and emitting volume. In the present invention, after the thermosetting composite membrane is sent to the outer space, the power source is switch on and the thermal blanket (3) is heated to 20 DEG C to increase the flexibility; and then the thermosetting composite membrane is gas-charged, so that the membrane is sufficiently outspreaded, and then the temperature is enhanced to cure the stiffening layer (2) with a curing temperature of 100~140 DEG C, a curing time of 0.5~2 hours and a heating power of 300~520 W/m<2>. The thermosetting composite membrane of the present invention is light in weight, is flexible before emitting, and can be folded package; after emitting to the outer space, the structure is gas-charged to outspread the structure sufficiently, and the predetermined shape is formed, and the functional requirement is realized. The stiffening method for thermosetting composite membrane is adapted to the outer space environment and the shaping effect is excellent.
Description
The application is dividing an application of former " composite thermosetting film and the making and rigidizing process that are used for inflated spatial expanded structure ", and the original bill application number is 200510009885.2, and the original bill applying date is on April 8th, 2005.
Technical field
The thermosetting that the present invention relates to a kind of laminated film and this film has 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 firmization method that is used for the composite thermosetting film of inflated spatial expanded structure is provided, and the firmization method of composite thermosetting film of the present invention has the characteristics of suitable space environment, good forming effect.Composite thermosetting film is made up of internal gas barrier layer 1, firmization layer 2, zone of heating 3, outer insulative layer 4 in the method for the present invention; 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.Described gas-barrier layer 1 is made by Kapton or polyester film; Described firmization layer 2 by two to or the uncured resin of fiber cloth preimpregnation of three-dimensional establishment make; Described zone of heating 3 is placed in the middle of the two layers of polyimide film that the inboard scribbles the thermosetting adhesive by metal forming or filament, is placed on the hot press heating extrusion forming again and makes; Described outer insulative layer 4 is bonded together and is made by the aluminize Kapton of punching or polyester film and terylene net of single or double.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 preparation method 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.The firmization method of composite thermosetting film of the present invention is: 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, again to the composite thermosetting film inner inflatable, it is fully launched, improve temperature then firmization layer 2 is solidified.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 firmization method 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 the overall structure schematic diagram of composite thermosetting film in the method for the present invention.
The specific embodiment
The specific embodiment one: composite thermosetting film is made up of internal gas barrier layer 1, firmization layer 2, zone of heating 3, outer insulative layer 4 in the method for (referring to Fig. 1) present embodiment; 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 (8)
1, a kind of firmization method that is used for the composite thermosetting film of inflated spatial expanded structure, the composite thermosetting film in the method 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); Described gas-barrier layer (1) is made by Kapton or polyester film; Described firmization layer (2) by two to or the uncured resin of fiber cloth preimpregnation of three-dimensional establishment make; Described zone of heating (3) is placed in the middle of the two layers of polyimide film that the inboard scribbles the thermosetting adhesive by metal forming or filament, is placed on the hot press heating extrusion forming again and makes; Described outer insulative layer (4) is bonded together and is made by the aluminize Kapton of punching or polyester film and terylene net of single or double, it is characterized in that, 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, to the composite thermosetting film inner inflatable, it is fully launched again, improve temperature then firmization layer (2) is solidified.
2, the firmization method that is used for the composite thermosetting film of inflated spatial expanded structure according to claim 1 is characterized in that, the thickness of internal gas barrier layer (1) is 0.025mm～0.05mm.
3, the firmization method that is used for the composite thermosetting film of 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 firmization method that is used for the composite thermosetting film of 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 firmization method that is used for the composite thermosetting film of 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 firmization method that is used for the composite thermosetting film of inflated spatial expanded structure according to claim 1 is characterized in that, the solidification temperature of described firmization layer (2) is 100～140 ℃.
7, the firmization method that is used for the composite thermosetting film of inflated spatial expanded structure according to claim 1 is characterized in that, be 0.5～2 hour the hardening time of described firmization layer (2).
8, the firmization method that is used for the composite thermosetting film of inflated spatial expanded structure according to claim 1 is characterized in that, the heating power of described zone of heating (3) is 300～520W/m
2
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB200710103666XA CN100560365C (en) | 2005-04-08 | 2005-04-08 | The firmization method that is used for the composite thermosetting film of inflated spatial expanded structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB200710103666XA CN100560365C (en) | 2005-04-08 | 2005-04-08 | The firmization method that is used for the composite thermosetting film of inflated spatial expanded structure |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2005100098852A Division CN100348408C (en) | 2005-04-08 | 2005-04-08 | Composite thermosetting film for inflated spatial expanded structure and its making and rigidizing process |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101054008A true CN101054008A (en) | 2007-10-17 |
| CN100560365C CN100560365C (en) | 2009-11-18 |
Family
ID=38794135
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB200710103666XA Expired - Fee Related CN100560365C (en) | 2005-04-08 | 2005-04-08 | The firmization method that is used for the composite thermosetting film of inflated spatial expanded structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN100560365C (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101905748A (en) * | 2010-07-09 | 2010-12-08 | 哈尔滨工业大学 | Gas-filled unfolded article storing cabin |
| CN101905749A (en) * | 2010-07-09 | 2010-12-08 | 哈尔滨工业大学 | Inflation expandable waste collection cabin |
| CN104691787A (en) * | 2014-12-31 | 2015-06-10 | 哈尔滨工业大学 | Inflatable spreading support framework for multi-layer sandwich air inflation cabin |
| CN105305006A (en) * | 2015-11-21 | 2016-02-03 | 哈尔滨工业大学 | Foldable-inflatable supporting ring applicable to radial rib antenna and manufacture method of same |
| CN109779029A (en) * | 2019-03-12 | 2019-05-21 | 马会环 | Aluminium alloy cable-membrane analysis and its method of construction for space base |
| CN110181730A (en) * | 2019-06-28 | 2019-08-30 | 中国科学院工程热物理研究所 | Consolidated structures, curing method and its application based on powder filling |
| CN114150814A (en) * | 2021-11-26 | 2022-03-08 | 哈尔滨工业大学 | Inflatable and expandable rigidizable lunar soil filling brick with foldable rigid shell |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103114384B (en) * | 2013-02-06 | 2014-07-09 | 哈尔滨工业大学 | Die and method for braiding curve limiting mesh of inflatable membrane |
-
2005
- 2005-04-08 CN CNB200710103666XA patent/CN100560365C/en not_active Expired - Fee Related
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101905748A (en) * | 2010-07-09 | 2010-12-08 | 哈尔滨工业大学 | Gas-filled unfolded article storing cabin |
| CN101905749A (en) * | 2010-07-09 | 2010-12-08 | 哈尔滨工业大学 | Inflation expandable waste collection cabin |
| CN101905748B (en) * | 2010-07-09 | 2013-03-06 | 哈尔滨工业大学 | Gas-filled unfolded article storing cabin |
| CN101905749B (en) * | 2010-07-09 | 2013-03-20 | 哈尔滨工业大学 | Inflation expandable waste collection cabin |
| CN104691787A (en) * | 2014-12-31 | 2015-06-10 | 哈尔滨工业大学 | Inflatable spreading support framework for multi-layer sandwich air inflation cabin |
| CN105305006A (en) * | 2015-11-21 | 2016-02-03 | 哈尔滨工业大学 | Foldable-inflatable supporting ring applicable to radial rib antenna and manufacture method of same |
| CN105305006B (en) * | 2015-11-21 | 2018-03-16 | 哈尔滨工业大学 | A kind of foldable inflating suitable for radial rib antenna deploys support ring and preparation method thereof |
| CN109779029A (en) * | 2019-03-12 | 2019-05-21 | 马会环 | Aluminium alloy cable-membrane analysis and its method of construction for space base |
| CN110181730A (en) * | 2019-06-28 | 2019-08-30 | 中国科学院工程热物理研究所 | Consolidated structures, curing method and its application based on powder filling |
| CN114150814A (en) * | 2021-11-26 | 2022-03-08 | 哈尔滨工业大学 | Inflatable and expandable rigidizable lunar soil filling brick with foldable rigid shell |
| CN114150814B (en) * | 2021-11-26 | 2023-02-07 | 哈尔滨工业大学 | Inflatable and expandable rigidizable lunar soil filling brick with foldable rigid shell |
Also Published As
| Publication number | Publication date |
|---|---|
| CN100560365C (en) | 2009-11-18 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN100348408C (en) | Composite thermosetting film for inflated spatial expanded structure and its making and rigidizing process | |
| CN100560365C (en) | The firmization method that is used for the composite thermosetting film of inflated spatial expanded structure | |
| Cadogan et al. | Rigidizable materials for use in gossamer space inflatable structures | |
| Li et al. | Progress of shape memory polymers and their composites in aerospace applications | |
| CN100362693C (en) | Plane framework supporting structure capable of steel charge expansion | |
| CN101853986B (en) | Manufacturing methods of inflatable deployable antenna reflecting surface based on shape memory polymer and reflecting surface film and skin thereof | |
| Bansemir et al. | Fibre composite structures for space applications—recent and future developments | |
| CN101913270B (en) | Foldable-expandable shape memory supporting pipe and preparation method thereof | |
| CN105474780B (en) | The gathering of space film facility launches support tube | |
| CN101847786B (en) | Reflecting surface of deployable antenna based on shape memory polymer and manufacturing method of skeleton structure thereof | |
| CN1772562A (en) | Inflating expanded truss for outer space use | |
| CN101734369B (en) | Shape memory polymer-based air filling extensible wing and methods for manufacturing same | |
| CN108058406B (en) | Preparation method of seepage-proof and leakage-proof carrier rocket all-composite material low-temperature liquid oxygen storage tank | |
| CN1751965A (en) | Ultraviolet light rigidization composite film capable of aeration expanding outer space structure | |
| CN105356029A (en) | Planar reflection array antenna based on shape memory polymer composite material hinge and expansion method thereof | |
| CN102501491A (en) | Polyethylene composite bulletproof plate and manufacturing method thereof | |
| Cadogan et al. | Inflatable and rigidizable wing components for unmanned aerial vehicles | |
| US20200307153A1 (en) | Fiber reinforced composite structure comprising stitch-member and the method for producing the same | |
| JPS6239399A (en) | Solar-panel | |
| WO2018173348A1 (en) | Low-temperature tank and method for manufacturing same | |
| CN104154822A (en) | Portable bulletproof module | |
| Zeng et al. | A shape-memory deployable subsystem with a large folding ratio in China’s tianwen-1 mars exploration mission | |
| CN105207577A (en) | Flexible solar cell array based on shape memory polymer composite material and expansion method of flexible solar cell array | |
| EP3333420B1 (en) | Reconfigurable structure using dual-matrix composite material | |
| CN107825957B (en) | Military bulletproof protection oil tank shell and preparation method thereof |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20091118 Termination date: 20100408 |