CN101797805A - Method for manufacturing inflatable expansion wing skin based on shape memory polymer - Google Patents
Method for manufacturing inflatable expansion wing skin based on shape memory polymer Download PDFInfo
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- CN101797805A CN101797805A CN201010301021A CN201010301021A CN101797805A CN 101797805 A CN101797805 A CN 101797805A CN 201010301021 A CN201010301021 A CN 201010301021A CN 201010301021 A CN201010301021 A CN 201010301021A CN 101797805 A CN101797805 A CN 101797805A
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Abstract
The invention relates to a method for manufacturing an inflatable expansion wing skin based on shape memory polymer, relating to a method for manufacturing the expandable wing skin. The invention aims at solving the problems that the inflatable expansion wing skin is made of flexible materials before and after expansion, the stamping inside the wing is small and fails to meet the intensity and rigidity required by an airplane, and damage and gas leakage of the stamping wing are likely to occur. The method comprises the following steps of: firstly, designing a mould; secondly, preparing a shape memory polymer material; thirdly, coating the shape memory polymer material on the upper and the lower surfaces of a fibre reinforcing material; fourthly, placing the fibre reinforcing material coated with the shape memory polymer material in the mould; fifthly, placing and heating the mould in a heating cabinet for 16-24 hours at a temperature of 70-80 DEG C; and sixthly, demoulding, taking the mould out of the heating cabinet to obtain the upper skin or lower skin of the fibre reinforcing shape memory polymer. The invention is used for manufacturing the inflatable expansion wing skin.
Description
Technical field
The present invention relates to a kind of manufacture method of deployable wing cover.
Background technology
The U.S. is in the fifties inflatable aircraft that begins one's study at first in last century.At present, the aircraft that new-type structures such as inflation aerodone, inflation scounting aeroplane, trailing edge inflation lift-rising machine occurred.The inflation aircraft can be used as individual soldier's reconnaissance system, as the scounting aeroplane of howitzer emission, also can be used for a large amount of reconnaissance planes of throwing in of military transportation airplane.The inflation aircraft is a kind of course of new aircraft, compares with conventional airplane, and inflatable aircraft has following four big advantages: volume is little, weight is little, emission is convenient, stealthy performance is good, ballistic performance is good.Covering on the deployable wing of existing inflation is launching the distortion front and back, covering is flexible material, rigidity is constant, under the condition that guarantees enough strength and stiffness, wish that the lowland reduces the blowing pressure as far as possible, to reduce the risk of wing breakage, reduce gas charging system and the weight of structure and the leak rate of gas.Yet undue reduction air pressure can reduce the rigidity of wing again, and the wind that increases in the flight course carries distortion, reduces flight stability.In recent years, the fast development of intellectual material for the stiffness variable wing provide can be wide development space.Wherein, the shape-memory polymer unique properties, when it was heated to the material phase transformation temperature, the shape-memory polymer modulus descended significantly, and began to represent SME.Based on the stiffness variable wing that this kind material is made, can before and after operation, control the modulus of self.Before the wing inflation distortion, the wing modulus reduces, and is beneficial to the deployable distortion of inflation of wing.After the distortion, wing self modulus rises, and the intensity of wing and rigidity increase, and auxiliary wing bears the aerodynamic loading that produces in-flight, improves the stability and the reliability of flight.
Summary of the invention
The objective of the invention is launching to be flexible material before and after the distortion for the covering that solves on the deployable wing of existing inflation, the inner qi of chong channel ascending adversely pressure of wing is too little, it is too big to satisfy inflation needed intensity of aircraft flight and rigidity or qi of chong channel ascending adversely pressure, wing is easy to problem damaged and gas leakage, and a kind of manufacture method of the inflatable expansion wing skin based on shape-memory polymer is provided.
Method of the present invention realizes by following steps: one, designing mould: by the shaped design mould of last covering or following covering; Two, preparation shape memory polymer material: with high molecular polymer and curing agent by 28: the mass ratio of (1～5) is made into shape memory polymer material; Three, coated fiber reinforcing material: shape memory polymer material and fibre reinforced materials are pressed (0.67～99): 1 mass ratio takes by weighing, and shape memory polymer material is coated on the above and below of fibre reinforced materials; Four, irritate mould: the fibre reinforced materials that the above and below is coated with shape memory polymer material places in the mould, with the remaining shape memory polymer material of step 3 the space in the mould is filled again; Five, solidify: mould is placed in the heating cabinet heats, heating-up temperature is 70～80 ℃, and be 16～24 hours heat time heating time; Six, the demoulding: from heating cabinet, take out mould, promptly obtain the last covering or the following covering of fiber-reinforced shape memory polymer after the demoulding.
Advantage of the present invention: one, the covering made by shape memory polymer material of the present invention, be used on the deployable wing of inflation, making wing be software state (promptly crispaturaing) before use, is hardware state (shape invariance after promptly launching) in use, uses the back to be software state (promptly crispaturaing); Because wing is the hardware state in use, therefore, wing can satisfy needed intensity of aircraft flight and rigidity, and is not subjected to the restriction of inner punching press size, has avoided the damaged and gas leakage of wing.Two, the present invention have intensity height, modulus height, in light weight, expansion process mild, aircraft is not had impacts, launches characteristics such as control ability is strong, simple in structure, expansion reliability height, thereby reduced the quality burden of aircraft flight, improved the stability and the reliability of aircraft flight.Three, the preparation method of wing of the present invention is simple.
The specific embodiment
The specific embodiment one: present embodiment realizes by following steps: one, designing mould: by the shaped design mould of last covering or following covering; Two, preparation shape memory polymer material: with high molecular polymer and curing agent by 28: the mass ratio of (1～5) is made into shape memory polymer material; Three, coated fiber reinforcing material: shape memory polymer material and fibre reinforced materials are pressed (0.67～99): 1 mass ratio takes by weighing, and shape memory polymer material is coated on the above and below of fibre reinforced materials; Four, irritate mould: the fibre reinforced materials that the above and below is coated with shape memory polymer material places in the mould, with the remaining shape memory polymer material of step 3 the space in the mould is filled again; Five, solidify: mould is placed in the heating cabinet heats, heating-up temperature is 70～80 ℃, and be 16～24 hours heat time heating time; Six, the demoulding: from heating cabinet, take out mould, promptly obtain the last covering or the following covering of fiber-reinforced shape memory polymer after the demoulding.Last covering is identical with the shape of following covering.The outline of last covering and following covering should meet the standard of international air-foil NACA0020.Assembling is during wing, will go up covering or down the covering symmetry fasten, and several closed airbags that will be linked into promptly become after placing covering and following covering interior and inflate deployable wing; Each closed airbag is connected with charger by wireway, in order to inflate in closed airbag.Heat and to adopt the heating of resistance wire electrical heating or vapours inflating deployable wing:, can go up the inner surface adhering resistance heating film of covering and following covering if adopt the resistance wire electrical heating; If adopt the vapours heating, can when being out of shape, fill with vapours air bag inside on wing, improve the temperature of shape-memory polymer by the temperature of vapours.The covering that adopts shape-memory polymer to make can make wing can crispatura before use, and promptly covering is the software state; In use, the shape invariance after wing cover can keep launching, promptly covering is the hardware state; Use back wing cover still can recover the software state and crispatura for using preceding state.When the covering temperature that adopts shape-memory polymer to make was higher than its phase transition temperature, material modulus descended significantly, the rapid expansion distortion that its SME that demonstrates can auxiliary wing.When temperature was lower than phase transition temperature, the modulus of material rose significantly.Compare with traditional inflatable structure, shape memory polymer material high-modulus state at normal temperatures can increase the rigidity of wing, reduces the distortion that wind carries the effect lower wing, improves the stability and the reliability of flight.
The specific embodiment two: the high molecular polymer in the step 2 of present embodiment is styrene, polyurethane resin, isocyanates or epoxy resin.The particle diameter of above-mentioned material is less than 100nm, and particle diameter is even, contains suitable hydrophilic radical in the particle of above-mentioned material, in film forming procedure, volatilization along with moisture, merged by small number of curing agents, form high-quality and film, the molecular structure of filming is very tight, has soft chain segment in the structure, the toughness that can keep material, simultaneously, smaller particle size can be under lower temperature conditions film forming.Above-mentioned material also has very high mechanical strength and good resistance to water.Other step is identical with the specific embodiment one.
The specific embodiment three: the fibre reinforced materials in the step 3 of present embodiment is graphite fibre, carbon fiber, glass fibre, boron fibre, carbon black, graphite powder or CNT.Above-mentioned material has characteristics such as proportion is little, intensity is high, modulus is high, corrosion-resistant.Other step is identical with the specific embodiment one.
The expansion process of inflatable wing: before the use, to the last covering and the heating of following covering of wing, last covering and following covering begin deliquescing, wing can be compressed bending, and twist in the surface of airframe, and after stopping to heat, the wing hardening keeps shape; During use, last covering and following covering to wing heat once more, when the shape-memory polymer temperature surpasses phase transition temperature, air bag to last covering and following covering inside is inflated, increase along with the covering air pressure inside, wing begins distortion, wing by the thickness direction of curl shape wing to the straight deformation shape time also in distortion (distending); When stopping heating, temperature is reduced to the shape-memory polymer phase transition temperature when following, the covering hardening, and wing keeps the shape invariance after the expansion; Only need to heat to wing again if will recover the original shape of wing, the temperature of wing is increased to more than the shape-memory polymer transition temperature, emit the air bag gas inside simultaneously, outer power is planar compressed wing and it is twisted on the surface of airframe; Stop heating, temperature is reduced to the shape-memory polymer transition temperature when following, wing maintenance original state.
Claims (3)
1. manufacture method based on the inflatable expansion wing skin of shape-memory polymer, it is characterized in that: described method realizes by following steps: one, designing mould: by the last covering or the shaped design mould of covering down; Two, preparation shape memory polymer material: with high molecular polymer and curing agent by 28: the mass ratio of (1～5) is made into shape memory polymer material; Three, coated fiber reinforcing material: shape memory polymer material and fibre reinforced materials are pressed (0.67～99): 1 mass ratio takes by weighing, and shape memory polymer material is coated on the above and below of fibre reinforced materials; Four, irritate mould: the fibre reinforced materials that the above and below is coated with shape memory polymer material places in the mould, with the remaining shape memory polymer material of step 3 the space in the mould is filled again; Five, solidify: mould is placed in the heating cabinet heats, heating-up temperature is 70～80 ℃, and be 16～24 hours heat time heating time; Six, the demoulding: from heating cabinet, take out mould, promptly obtain the last covering or the following covering of fiber-reinforced shape memory polymer after the demoulding.
2. the manufacture method of the inflatable expansion wing skin based on shape-memory polymer according to claim 1, it is characterized in that: the high molecular polymer in the described step 2 is styrene, polyurethane resin, isocyanates or epoxy resin.
3. the manufacture method of the inflatable expansion wing skin based on shape-memory polymer according to claim 1, it is characterized in that: the fibre reinforced materials in the described step 3 is graphite fibre, carbon fiber, glass fibre, boron fibre, carbon black, graphite powder or CNT.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010301021A CN101797805A (en) | 2010-02-01 | 2010-02-01 | Method for manufacturing inflatable expansion wing skin based on shape memory polymer |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201010301021A CN101797805A (en) | 2010-02-01 | 2010-02-01 | Method for manufacturing inflatable expansion wing skin based on shape memory polymer |
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| CN201010301021A Pending CN101797805A (en) | 2010-02-01 | 2010-02-01 | Method for manufacturing inflatable expansion wing skin based on shape memory polymer |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102319989A (en) * | 2011-09-06 | 2012-01-18 | 上海交通大学 | Manufacturing method of airplane horizontal tail beam edge strip |
| CN103332289A (en) * | 2013-06-09 | 2013-10-02 | 哈尔滨工业大学 | Shape memory polymer variable stiffness skin |
| CN108482643A (en) * | 2018-03-14 | 2018-09-04 | 中国人民解放军国防科技大学 | Flexible inflatable wing structure capable of being inflated at high pressure and rapidly unfolded |
| CN116141651A (en) * | 2023-03-14 | 2023-05-23 | 哈尔滨工业大学 | Shape memory material-based aircraft emergency slide and manufacturing method thereof |
-
2010
- 2010-02-01 CN CN201010301021A patent/CN101797805A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102319989A (en) * | 2011-09-06 | 2012-01-18 | 上海交通大学 | Manufacturing method of airplane horizontal tail beam edge strip |
| CN102319989B (en) * | 2011-09-06 | 2013-11-20 | 上海交通大学 | Manufacturing method of airplane horizontal tail beam edge strip |
| CN103332289A (en) * | 2013-06-09 | 2013-10-02 | 哈尔滨工业大学 | Shape memory polymer variable stiffness skin |
| CN108482643A (en) * | 2018-03-14 | 2018-09-04 | 中国人民解放军国防科技大学 | Flexible inflatable wing structure capable of being inflated at high pressure and rapidly unfolded |
| CN116141651A (en) * | 2023-03-14 | 2023-05-23 | 哈尔滨工业大学 | Shape memory material-based aircraft emergency slide and manufacturing method thereof |
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Application publication date: 20100811 |