CN1254508C - Method for improving antigen oxygen peeling of aircraft by adding nanometer partical material - Google Patents
Method for improving antigen oxygen peeling of aircraft by adding nanometer partical material Download PDFInfo
- Publication number
- CN1254508C CN1254508C CNB2004100091539A CN200410009153A CN1254508C CN 1254508 C CN1254508 C CN 1254508C CN B2004100091539 A CNB2004100091539 A CN B2004100091539A CN 200410009153 A CN200410009153 A CN 200410009153A CN 1254508 C CN1254508 C CN 1254508C
- Authority
- CN
- China
- Prior art keywords
- atomic oxygen
- polymer
- resin
- composite material
- ablation
- 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.)
- Expired - Fee Related
Links
Images
Landscapes
- Compositions Of Macromolecular Compounds (AREA)
Abstract
本发明公开了一种通过添加纳米颗粒材料来提高航天器用聚合物和聚合物基复合材料抗原子氧剥蚀性能的方法，其按照比例，在反应釜中将聚合物或聚合物基复合材料的树脂基体、稀释剂和/或固化剂搅拌混合均匀，制得树脂溶液；再将经表面改性处理后的不与原子氧反应的纳米颗粒材料，在搅拌状态下加入到树脂溶液中，制得抗原子氧剥蚀复合材料溶液；将抗原子氧剥蚀复合材料溶液经成型工艺可制备出抗原子氧剥蚀的颗粒复合材料或者制备出抗原子氧剥蚀的纤维颗粒复合材料。本发明的复合材料通过原子氧效应试验表明，具有较好的抗原子氧剥蚀性能，从而较好地解决了航天器用高分子材料受原子氧剥蚀严重的问题，能够满足航天工程的使用要求。材料的整个制备过程采用常规的制备方法，具有很好的工程适用性，同时，使用这种材料也不会给航天器结构带来复杂化。The invention discloses a method for improving the anti-atomic oxygen ablation performance of polymers and polymer-based composite materials for spacecraft by adding nanoparticle materials. According to the proportion, the polymer or the resin of the polymer-based composite materials The matrix, diluent and/or curing agent are stirred and mixed evenly to obtain a resin solution; then the surface-modified nanoparticle material that does not react with atomic oxygen is added to the resin solution under stirring to obtain an antigen Anti-atomic oxygen ablation composite material solution; the anti-atomic oxygen ablation composite material solution can be prepared through a molding process to prepare an anti-atomic oxygen ablation particle composite material or to prepare an anti-atomic oxygen ablation fiber particle composite material. The atomic oxygen effect test shows that the composite material of the present invention has better anti-atomic oxygen erosion performance, thereby better solving the problem that the polymer materials used in spacecraft are severely eroded by atomic oxygen, and can meet the use requirements of aerospace engineering. The entire preparation process of the material adopts a conventional preparation method, which has good engineering applicability, and at the same time, the use of this material will not bring complexity to the structure of the spacecraft.
Description
Technical field
The present invention relates to a kind of method that improves spacecraft with polymkeric substance and polymer matrix composite antigen oxygen peeling performance, specifically, be meant in the resin matrix of polymkeric substance and polymer matrix composite and add the antigen oxygen peeling performance that does not improve the spacecraft material with the nano-particle material of atomic oxygen reaction.
Background technology
Polymkeric substance and polymer matrix composite have a wide range of applications on spacecraft.When spacecraft moves in the Low Earth Orbit environment of space, most of polymkeric substance and polymer matrix composite can be subjected to seriously degrading of atomic oxygen in the environment, the thickness of material and quality can be lost, and performance also can degenerate, thereby have influenced the works better and the work-ing life of spacecraft.In order to ensure moving reliably and with long-term at rail of spacecraft, and prolong its work-ing life, improving spacecraft is very important and necessary with the antigen oxygen peeling performance of polymkeric substance and polymer matrix composite.
At present; antigen oxygen peeling method commonly used on the spacecraft mainly contains: (one) anti-atomic oxygen protective coating: it is to plate one deck supercoat at the material surface that is subject to degrade; atomic oxygen can't be contacted with the protected material of bottom, thereby play the effect of antigen oxygen peeling.This method of anti-atomic oxygen protective coating occurs the earliest, also is at present the most frequently used, as just having used protective coating to guarantee that it moves and work-ing life reliably and with long-term in a large number on the international space station.It is complicated that but this method brings for the structure of spacecraft, also can increase the difficulty of forming materials and processing.In addition, defective appears in coating easily, as: 1. when spacecraft moves in track, (this is called as thermal cycling to its surface temperature changing between ± 80 ℃ approximately, about 90 minutes of cycle), because the thermal expansivity of coating and primer is different, under the effect of long term thermal round-robin, thermal stresses between the two may make coatingsurface crackle occur; 2. the bump of space micrometeorite and rubbish fragment also can make coatingsurface defectives such as hole occur; 3. in the deposition process of coating and during the component processing moulding, coatingsurface also might produce defective.These defectives are in case form, and atomic oxygen will pass these defectives and primer reacts, the formation sapping, and finally cause coating to lose provide protection even come off.(2) change the elementary composition of material surface: mainly be the surface-element composition that changes material by surface silicon alkanisation or ion implantation (aluminium, silicon, yttrium plasma) these two kinds of approach, make its surface contain abundant aluminium, silicon plasma, thereby make material under the effect of factors such as space atomic oxygen or atomic oxygen and uv-radiation, form oxide skin (silicon oxide, aluminum oxide etc.).Because these oxide compounds are not react with atomic oxygen, thereby also just reduce the atomic oxygen erodes degree of material, improved the antigen oxygen peeling performance of material.This method is actually and has changed the elementary composition of material surface certain depth, and then under given conditions, material surface just can generate the new texture or the protective layer of anti-atomic oxygen.Spacecraft material after this method is handled, protective layer only are to exist at material surface, if suffer the bump of micrometeorite and rubbish fragment, equally also can lose efficacy; In addition, the bump of high energy particle also can change the molecular structure and the physics-chem characteristic of material surface, and for example the surface carbonization takes place and presents burgundy or the like.(3) development of new polymer materials: the molecular composition and the structure of redesign material, construct can antigen oxygen peeling novel material.This method mainly is to add the element that some can anti-atomic oxygen on the main chain of polymkeric substance at present, as fluorine, phosphorus etc., to improve the antigen oxygen peeling performance of material.But it can relate to the change of polymer production technology, bigger difficulty is arranged, and resulting material is except having preferably the antigen oxygen peeling performance, can satisfy the service requirements (as hot optical property, mechanical property, insulating property etc.) of spacecraft others, it be not immediately clear.
Summary of the invention
The objective of the invention is the deficiency that the polymkeric substance used at spacecraft and polymer matrix composite are subjected to serious problem of Low Earth Orbit environment atomic oxygen erodes and existing antigen oxygen peeling technology, according to the reaction characteristics and the rule of atomic oxygen and polymkeric substance and polymer matrix composite, a kind of novel method and matrix material thereof that can significantly improve spacecraft material antigen oxygen peeling performance disclosed.
The present invention is a kind of method that improves spacecraft usefulness polymkeric substance and polymer matrix composite antigen oxygen peeling performance by the interpolation nano-particle material, it proportionally, resin matrix, thinner and/or solidifying agent with polymkeric substance or polymer matrix composite in reactor mix, and make resin solution; Nano-particle material that again will be after surface modification treatment joins in the resin solution under whipped state, makes antigen oxygen peeling matrix material solution; The sub-oxygen of above-mentioned antigens is degraded matrix material solution can be prepared the particulate composite of antigen oxygen peeling or prepare the fiber grain matrix material of antigen oxygen peeling through moulding process.
The composition of the particulate composite of described antigen oxygen peeling is by weight:
(A) polymkeric substance, consumption are 100 parts, and this polymkeric substance is Resins, epoxy or polyimide resin or resol or polyamide resin or vibrin or polysulfones or polyether-ether-ketone or polymethylmethacrylate; With
(B) nano-particle material, consumption are 2～35 parts, this nano-particle material be not with silicon-dioxide or aluminium sesquioxide or zirconium white or the stannic oxide or the material of titanium oxide after surface modification treatment of atomic oxygen reaction, its particle diameter 5～100 nanometers.
The composition of the fiber grain matrix material of described antigen oxygen peeling is by weight:
(A) resin matrix of polymer matrix composite, consumption are 100 parts, and this resin matrix is Resins, epoxy or polyimide resin or resol or polyamide resin or vibrin or polysulfones or polyether-ether-ketone or polymethylmethacrylate; With
(B) nano-particle material, consumption are 2～35 parts, this nano-particle material be not with silicon-dioxide or aluminium sesquioxide or zirconium white or the stannic oxide or the material of titanium oxide after surface modification treatment of atomic oxygen reaction, its particle diameter 5～100 nanometers; With
(C) filamentary material: carbon fiber or glass fibre.
Describedly improve spacecraft with polymkeric substance and polymer matrix composite antigen oxygen peeling performance methodology, comprise the following steps: by adding nano-particle material
(a) preparation nano-particle material
Choose not nano-particle material with the atomic oxygen reaction;
Choose not the required surface-modifying agent of nano-particle material with the atomic oxygen reaction, its surface-modifying agent can be vinyltriethoxysilane (Al51) or γ-An Jibingjisanyiyangjiguiwan (KH550) or tetra isopropyl (dioctyl phosphorous acid ester acyl group) titanic acid ester (NDZ-401);
Admit the rice particulate material: surface-modifying agent=100: 0.5～5 take by weighing above-mentioned materials, make nano-particle material;
(b) take by weighing the resin matrix and the nano-particle material of polymkeric substance or polymer matrix composite
Resin matrix by polymkeric substance or polymer matrix composite: nano-particle material=100: 2～35 take by weighing;
(c) resin solution of system polymkeric substance or polymer matrix composite
Choose the resin matrix of polymkeric substance or polymer matrix composite;
Choosing thinner is acetone;
Choosing solidifying agent is polymeric amide or triethylamine or hexanediamine or 4,4 '-two amido ditanes or glyoxal ethyline or MALEIC ANHYDRIDE;
Resin matrix by polymkeric substance or polymer matrix composite: solidifying agent: thinner=100: 0～70: 40～80 take by weighing above-mentioned materials, and put it in the reactor and mix, and make the resin solution of polymkeric substance or polymer matrix composite;
(d) system antigen oxygen peeling matrix material solution
After preparing above-mentioned (c) solution, in stirring, be added into the nano-particle material in above-mentioned (a), make antigen oxygen peeling matrix material solution;
(e) system antigen oxygen peeling particulate composite or antigen oxygen peeling fiber grain matrix material
Make antigen oxygen peeling particulate composite or antigen oxygen peeling fiber grain matrix material through moulding process.
Matrix material of the present invention has the following advantages: (1) with the modification of aerosol surface modification equipment handle not with the nano-particle material of atomic oxygen reaction, properties-correcting agent and particulate material surface can fully act on, and reach the purpose of complete modification; Make not the nano-particle material coated with uniform one deck properties-correcting agent with the atomic oxygen reaction, guaranteed dispersion and the combination of nano-particle material in resin matrix; (2) in the process of high-speed stirring, nano-particle material is joined in the resin matrix, make nano-particle material can be in resin matrix uniform distribution; With the antigen oxygen peeling matrix material that this kind method is prepared, the atomic oxygen erodes rate is reduced to and does not add 50%～5% of nanometer particulate material, and its antigen oxygen peeling performance significantly improves; (3) this method technology is simple, is easy to realize, and can not increases the complicacy of spacecraft, has good versatility, can be widely used in various polymkeric substance and polymer matrix composite commonly used on the spacecraft.
Description of drawings
Fig. 1 does not adopt aerosol surface modification technology schema with the material of atomic oxygen reaction.
Fig. 2 is preparation technology's schema of embodiment 1.
Fig. 3 is preparation technology's schema of embodiment 2.
Fig. 4 (a) does not add 15 parts of SiO
2The field emission SEM photo of Resins, epoxy E51.
Fig. 4 (b) adds 15 parts of SiO
2The field emission SEM photo of Resins, epoxy E51.
Fig. 5 (a) does not add 15 parts of SiO
2The field emission SEM photo of/polyimide resin BMP316.
Fig. 5 (b) adds 15 parts of SiO
2The field emission SEM photo of/polyimide resin BMP316.
Embodiment
The present invention is described in further detail below in conjunction with embodiment.
In the present invention, nano-particle material be meant after surface modification treatment not with atomic oxygen reaction receive particulate material.Its processing technology for surface modification and equipment are the inventor's disclosed devices in the patent application that proposed on December 26th, 2002, publication number CN1424136A, application number 02158690X, denomination of invention " adopts aerosol processing that nanometer and micron particle material are disperseed technology and device thereof with surface modification treatment ".The aerosol processing nanometer of this technology or micron particle dispersion of materials and processing technology for surface modification mainly comprise: nanometer or micron particle material are broken up in the strong turbulence field with high velocity air, spray in the nanometer or micron particle material system of having been broken up with the properties-correcting agent atomizing or after gasifying by spraying gun, by the fully mixed aerosol that gets, properties-correcting agent is fully contacted with nanometer or micron particle material surface; The temperature and the pressure of control aerosol system behind the certain hour, come out this aerosol spray by nozzle; Adopt the method for injecting atmospheric air then, the aerosol that gushes out is cooled off rapidly, make properties-correcting agent can be coated on nanometer or micron particle material surface preferably, reach the purpose that makes nanometer or micron particle dispersion of materials and surface modification; Finish collection by collector at last to nanometer or micron particle material.Technical process is clearly referring to shown in Figure 1, particulate material surface after this art breading can fully act on properties-correcting agent, and reach the purpose of complete modification, make not the nano-particle material coated with uniform one deck properties-correcting agent with the atomic oxygen reaction, guaranteed dispersion and the combination of nano-particle material in resin matrix solution.
A kind of method that improves spacecraft usefulness polymkeric substance and polymer matrix composite antigen oxygen peeling performance by the interpolation nano-particle material of the present invention, it proportionally, resin matrix, thinner and/or solidifying agent with polymkeric substance or polymer matrix composite in reactor mix, and make resin solution; Again will be after surface modification treatment not with the nano-particle material of atomic oxygen reaction, under whipped state, join in the resin solution, make antigen oxygen peeling matrix material solution; Antigen oxygen peeling matrix material solution can be prepared the particulate composite of antigen oxygen peeling or prepared the fiber grain matrix material of antigen oxygen peeling through moulding process.
In the present invention, the composition of the particulate composite of antigen oxygen peeling is by weight:
(A) polymkeric substance, consumption are 100 parts, and this polymkeric substance is Resins, epoxy or polyimide resin or resol or polyamide resin or vibrin or polysulfones or polyether-ether-ketone or polymethylmethacrylate; With
(B) nano-particle material, consumption are 2～35 parts, this nano-particle material be not with silicon-dioxide or aluminium sesquioxide or zirconium white or the stannic oxide or the material of titanium oxide after surface modification treatment of atomic oxygen reaction, its particle diameter 5～100 nanometers.
In the present invention, the another composition of the particulate composite of antigen oxygen peeling is by weight:
(A) polymkeric substance, consumption are 100 parts, and this polymkeric substance is Resins, epoxy or polyimide resin; With
(B) nano-particle material, consumption are 2～20 parts, this nano-particle material be not with the material of silicon-dioxide after surface modification treatment of atomic oxygen reaction, its particle diameter 20～30 nanometers.
In the present invention, the composition of the fiber grain matrix material of antigen oxygen peeling is by weight:
(A) resin matrix of polymer matrix composite, consumption are 100 parts, and this resin matrix is Resins, epoxy or polyimide resin or resol or polyamide resin or vibrin or polysulfones or polyether-ether-ketone or polymethylmethacrylate; With
(B) nano-particle material, consumption are 2～35 parts, this nano-particle material be not with silicon-dioxide or aluminium sesquioxide or zirconium white or the stannic oxide or the material of titanium oxide after surface modification treatment of atomic oxygen reaction, its particle diameter 5～100 nanometers; With
(C) filamentary material: carbon fiber or glass fibre.
In the present invention, the another composition of the fiber grain matrix material of antigen oxygen peeling is by weight:
(A) resin matrix of polymer matrix composite, consumption are 100 parts, and this resin matrix is Resins, epoxy or polyimide resin; With
(B) nano-particle material, consumption are 2～20 parts, this nano-particle material be not with the material of silicon-dioxide after surface modification treatment of atomic oxygen reaction, its particle diameter 20～30 nanometers; With
(C) filamentary material: glass fibre.
In the present invention, the fiber grain matrix material of preparing the particulate composite of antigen oxygen peeling or preparing antigen oxygen peeling comprises the following steps:
(a) preparation nano-particle material
Choose not nano-particle material with the atomic oxygen reaction;
Choose not the required surface-modifying agent of nano-particle material with the atomic oxygen reaction, its surface-modifying agent can be vinyltriethoxysilane (A151) or γ-An Jibingjisanyiyangjiguiwan (KH550) or tetra isopropyl (dioctyl phosphorous acid ester acyl group) titanic acid ester (NDZ-401);
By nano-particle material: surface-modifying agent=100: 0.5～5 take by weighing above-mentioned materials, make nano-particle material;
(b) take by weighing the resin matrix and the nano-particle material of polymkeric substance or polymer matrix composite
Resin matrix by polymkeric substance or polymer matrix composite: nano-particle material=100: 2～35 take by weighing;
(c) resin solution of system polymkeric substance or polymer matrix composite
Choose the resin matrix of polymkeric substance or polymer matrix composite;
Choosing thinner is acetone;
Choosing solidifying agent is polymeric amide or triethylamine or hexanediamine or 4,4 '-two amido ditanes or glyoxal ethyline or MALEIC ANHYDRIDE;
Resin matrix by polymkeric substance or polymer matrix composite: solidifying agent: thinner=100: 0～70: 40～80 take by weighing above-mentioned materials, and put it in the reactor and mix, and make the resin solution of polymkeric substance or polymer matrix composite;
(d) system antigen oxygen peeling matrix material solution
After preparing above-mentioned (c) solution, in stirring, be added into the nano-particle material in above-mentioned (a), make antigen oxygen peeling matrix material solution;
(e) system antigen oxygen peeling particulate composite or antigen oxygen peeling fiber grain matrix material
Make antigen oxygen peeling particulate composite or antigen oxygen peeling fiber grain matrix material through moulding process.
In the method for preparing the antigen oxygen peeling matrix material in the present invention, solution in (d) step is made membranaceous antigen oxygen peeling particulate composite by solution-cast technology; Perhaps solution in (d) step is made lamination template antigen oxygen peeling fiber grain matrix material by technology laminated into type.
Hybrid technique of the present invention is the technology of conventional preparation mixture material, just when the resin matrix solution of preparation polymkeric substance or polymer matrix composite to thinner and/or solidify neat consumption and adjust to some extent.Carrying out surface modification treatment for nano-particle material carries out in " adopting aerosol processing nanometer and micron particle material to be disperseed technology and device thereof with surface modification treatment ".
Embodiment 1
100 parts of Resins, epoxy E51 consumptions (by weight), the particulate composite of 15 parts of preparations of earth silicon material antigen oxygen peeling.
The preparation method is as described below:
(a) preparation nanometer titanium dioxide silicon materials
Take by weighing not with the particle diameter of atomic oxygen reaction is 100 parts of the earth silicon materials and the required surface-modifying agent vinyltriethoxysilane A151 of 25 nanometers, consumption is 3 parts, through " aerosol surface modification device " silicon-dioxide is carried out surface modification treatment, make the nanometer silicon dioxide particle material;
(b) take by weighing 15 parts of 100 parts of Resins, epoxy E51 and nanometer titanium dioxide silicon materials;
(c) preparation Resins, epoxy E51 solution
With 100 parts of Resins, epoxy E51,50 parts in thinner acetone, solidifying agent polymeric amide PA651 puts into reactor for 60 parts, stirs (about 500 rev/mins) with homogenizer, and system is mixed, and makes Resins, epoxy E51 solution;
(d) preparation antigen oxygen peeling matrix material solution
Under whipped state, the earth silicon material of step (a) is added in the Resins, epoxy E51 solution of step (c), stir (about 500 rev/mins) with homogenizer, system is mixed, make antigen oxygen peeling matrix material solution.
The above-mentioned mixing solutions that makes is put into vacuum chamber carry out the vacuum stripping processing, about the about 400Pa of gas pressure in vacuum; After taking out mixing solutions in the vacuum chamber, on sheet glass, adopt solution-cast technology made membrane; And film put into 40 ℃ in loft drier insulation 7 hours, and then 80 ℃ of insulations 7 hours, nano silicon/Resins, epoxy E51 composite material film can be obtained after the curing; Film is cut into the square sample of 2cm * 2cm, in Low Earth Orbit environment atomic oxygen effect ground-based simulation equipment, carry out the atomic oxygen effect test of sample, the antigen oxygen peeling performance of sample is estimated and analyzed from aspects such as outward appearance, mass loss and atomic oxygen erodes rate, surface topography, surface compositions.Test-results shows: this kind SiO
2/ Resins, epoxy E51 epoxy composite material can significantly improve the antigen oxygen peeling performance of Resins, epoxy E51.Its antigen oxygen peeling results of property sees the following form:
| Polymkeric substance | Atomic oxygen erodes rate (cm 3/atom) | Test shows | ||
| Before the interpolation | After the interpolation | (being reduced to) | ||
| Resins, epoxy E51 | 4.64×10 -24 | 5 parts | 1.78×10 -24 | 38.36％ |
| 10 parts | 0.82×10 -24 | 17.67％ | ||
| 15 parts | 0.44×10 -24 | 9.48％ | ||
Last atom oxygen denudation rate is more little, and the antigen oxygen peeling performance of material is good more.
Be added with the Resins, epoxy E51 matrix material sample of 15 parts of nanometer titanium dioxide silicon materials, its denudation rate is about 9.48% of Resins, epoxy E51 virgin resin, shows that this method can significantly improve the antigen oxygen peeling performance of Resins, epoxy E51 really.See also the forward and backward SEM photo of interpolation shown in Figure 4.
Add the Resins, epoxy E51 matrix material sample of 5 parts or 10 parts nanometer titanium dioxide silicon materials after the same method, test-results shows that its denudation rate is about 38.36% or 17.67% of Resins, epoxy E51 virgin resin respectively.
Embodiment 2
100 parts of polyimide resin BMP316 consumptions (by weight), the fiber grain matrix material of 15 parts of preparations of earth silicon material antigen oxygen peeling.
The preparation method is as described below:
(a) preparation nanometer titanium dioxide silicon materials
Take by weighing not with the particle diameter of atomic oxygen reaction is 100 parts of the earth silicon materials and the required surface-modifying agent vinyltriethoxysilane A151 of 25 nanometers, consumption is 3 parts, through " aerosol surface modification device " silicon-dioxide is carried out surface modification treatment, make the nanometer silicon dioxide particle material;
(b) take by weighing 15 parts of 100 parts of polyimide resin BMP316 and nanometer titanium dioxide silicon materials;
(c) resin solution of prepared polymer based composites
With 100 parts of polyimide resin BMP316,60 parts in thinner acetone is put into reactor, stirs (about 500 rev/mins) with homogenizer, and system is mixed, and makes the resin solution of polymer matrix composite;
(d) preparation antigen oxygen peeling matrix material solution
Under whipped state, the earth silicon material of step (a) is added in the resin solution of step (c), stir (about 500 rev/mins) with homogenizer, system is mixed, make the fiber grain matrix material solution of antigen oxygen peeling.
Under room temperature state, the fiber grain matrix material solution of the above-mentioned antigen oxygen peeling that makes is soaked on glasscloth, and it was left standstill 48 hours in airiness place; Cutting at room temperature and lay-up carry out hot-forming (hot pressing condition is pressurize 1h under 80 ℃ of temperature, the pressure 7MPa) in the forming mould that scribbles releasing agent; In air, cool off the back demoulding, can obtain the glass fiber compound material thin plate of antigen oxygen peeling; Thin plate is cut into the square sample of 2cm * 2cm; In Low Earth Orbit environment atomic oxygen effect ground-based simulation equipment, carry out the atomic oxygen effect test of sample then, the antigen oxygen peeling performance of sample is estimated and analyzed from aspects such as outward appearance, mass loss and atomic oxygen erodes rate, surface topography, surface compositions.Test-results shows: this kind adds nanometer SiO
2The glass fibre thin plate of antigen oxygen peeling can significantly improve the antigen oxygen peeling performance of glass fibre/polyimide resin BMP316.Its antigen oxygen peeling results of property sees the following form:
| Fiber/resin matrix | Atomic oxygen erodes rate (cm 3/atom) | Test shows | ||
| Before the interpolation | After the interpolation | (being reduced to) | ||
| Glass fibre/polyimide resin BMP316 | 1.40×10 -24 | 5 parts | 0.77×10 -24 | 55.00％ |
| 10 parts | 0.35×10 -24 | 25.00％ | ||
| 15 parts | 0.20×10 -24 | 14.29％ | ||
Last atom oxygen denudation rate is more little, and the antigen oxygen peeling performance of material is good more.
Be added with the polyimide resin BMP316 complex fiber material sample of 15 parts of nanometer titanium dioxide silicon materials, its denudation rate is about 14.29% of polyimide resin BMP316 virgin resin, shows that this method can significantly improve the antigen oxygen peeling performance of polyimide resin BMP316 really.See also the forward and backward SEM photo of interpolation shown in Figure 5.
Add the polyimide resin BMP316 fibre composite sample of 5 parts or 10 parts nanometer titanium dioxide silicon materials after the same method, test-results shows that its denudation rate is about 55.00% or 25.00% of fiber/polyimide resin BMP316 respectively.
Embodiment 3
Choosing filamentary material is glasscloth,
Nano-particle material is SiO
2, properties-correcting agent is vinyltriethoxysilane A151
Polymer matrix composite is resol PF401, and the preparation method of employing embodiment 2 prepares the fiber grain matrix material of antigen oxygen peeling.
| Fiber/resin matrix | Atomic oxygen erodes rate (cm 3/atom) | Test shows (being reduced to) | ||
| Before the interpolation | After the interpolation | |||
| Glass fibre/resol PF401 | 2.50×10 -24 | 5 parts | 1.05×l0-24 | 42.00％ |
| 15 parts | 0.67×10 -24 | 26.80％ | ||
Embodiment 4
Nano-particle material is Al
2O
3, properties-correcting agent is γ-An Jibingjisanyiyangjiguiwan KH550,
Polymkeric substance is Resins, epoxy E51, and the preparation method of employing embodiment 1 prepares the particulate composite of antigen oxygen peeling.
| Polymkeric substance | Atomic oxygen erodes rate (cm 3/atom) | Test shows (being reduced to) | ||
| Before the interpolation | After the interpolation | |||
| Resins, epoxy E51 | 4.64×10 -24 | 5 parts | 1.93×10 -24 | 41.59％ |
| 10 parts | 1.02×l0 -24 | 21.98％ | ||
| 15 parts | 0.53×10 -24 | 11.42％ | ||
Claims (7)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2004100091539A CN1254508C (en) | 2004-05-31 | 2004-05-31 | Method for improving antigen oxygen peeling of aircraft by adding nanometer partical material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2004100091539A CN1254508C (en) | 2004-05-31 | 2004-05-31 | Method for improving antigen oxygen peeling of aircraft by adding nanometer partical material |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1583874A CN1583874A (en) | 2005-02-23 |
| CN1254508C true CN1254508C (en) | 2006-05-03 |
Family
ID=34600215
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2004100091539A Expired - Fee Related CN1254508C (en) | 2004-05-31 | 2004-05-31 | Method for improving antigen oxygen peeling of aircraft by adding nanometer partical material |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1254508C (en) |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103214846B (en) * | 2013-03-21 | 2016-06-08 | 北京航空航天大学 | Hybrid material that a kind of elemental oxygen of resistance to spatial environments degrades and preparation method |
| CN103817951B (en) * | 2013-11-19 | 2016-08-17 | 上海复合材料科技有限公司 | The manufacture method of the deployable component of Large-scale satellite composite |
| CN104099785B (en) * | 2014-07-10 | 2016-01-20 | 哈尔滨工业大学 | The preparation method of a kind of carbon fiber interface phosphorus-containing coatings of resistance to elemental oxygen |
| CN105368047A (en) * | 2015-10-15 | 2016-03-02 | 丽水市高升科技有限公司 | Material of high strength harmonic reducer cam |
| CN107201034B (en) * | 2017-04-24 | 2019-10-18 | 中国科学院宁波材料技术与工程研究所 | A kind of anti-reflection and anti-atomic oxygen ablation polymer composite film and preparation method thereof |
| CN113061337B (en) | 2017-12-05 | 2023-05-16 | 财团法人工业技术研究院 | Resin composition |
| CN108250671A (en) * | 2018-01-09 | 2018-07-06 | 南京航空航天大学 | A kind of cenosphere reinforced polyether ether ketone wearing composite material and preparation method thereof |
| CN108410125B (en) * | 2018-04-24 | 2020-09-01 | 航天特种材料及工艺技术研究所 | Heat-insulation-preventing integrated resin composition, heat-insulation-preventing integrated resin-based ablation material and preparation method thereof |
| CN109808201B (en) * | 2019-01-22 | 2020-08-18 | 西安交通大学 | Preparation and molding method of wear-resistant composite material with nano-gradient fiber reinforcement |
| CN110105712B (en) * | 2019-05-24 | 2022-02-18 | 哈尔滨工业大学 | Preparation method of electrical insulating material for inhibiting flashover voltage reduction |
| CN114106512A (en) * | 2021-09-09 | 2022-03-01 | 周琬彤 | Preparation method of epoxy resin-based composite material for curved surface and flow channel of hydraulic element |
| CN114149700B (en) * | 2021-11-30 | 2022-07-05 | 北京卫星制造厂有限公司 | Atomic oxygen resistant coating prepared by sol-gel method and method |
-
2004
- 2004-05-31 CN CNB2004100091539A patent/CN1254508C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN1583874A (en) | 2005-02-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN1254508C (en) | Method for improving antigen oxygen peeling of aircraft by adding nanometer partical material | |
| CN100587007C (en) | A method of inorganic nanoparticles reinforced nylon selective laser sintering formed parts | |
| CN110054864B (en) | High-thermal-conductivity composite filler and preparation method of polymer-based composite material thereof | |
| CN1606481A (en) | Metal oxide dispersion | |
| JP5390351B2 (en) | Composite material | |
| CN103289325A (en) | High-thermal-conductivity thermosetting resin and preparation method thereof | |
| CN1802761A (en) | Carbon material for battery electrode and production method and use thereof | |
| CN1709973A (en) | A kind of inorganic nanocomposite fiber reinforced polyimide composite material and preparation method thereof | |
| CN114016286B (en) | Method for modifying carbon fiber by functionalized graphene oxide electrophoretic deposition and carbon fiber composite material thereof | |
| CN1354198A (en) | Epoxy resin/montmorillonoid nano-compoiste-material and its preparation method | |
| CN103214846A (en) | Hybrid material resistant to space environment atomic oxygen denudation and preparation method | |
| CN107955200B (en) | Graphene/organic matter composite particle and preparation method thereof | |
| CN112537921A (en) | Phenolic resin coated chopped carbon fiber composite powder for laser 3D printing and preparation method thereof | |
| CN107033375A (en) | A kind of graphene microchip for rubber and plastic strengthens masterbatch and preparation method | |
| CN116063064A (en) | Photocuring additive manufacturing method of ceramic | |
| Jiang et al. | Preparation of functionalized boron nitride sheets/epoxy resin composites by using a green and efficient approach for elevated thermal conductivity | |
| JP2015189638A (en) | surface-modified silica powder and slurry composition | |
| CN113526970A (en) | A kind of preparation method of DLP printing Cf/SiC ceramic body | |
| TW201518442A (en) | Surface modified silica nanowires composite and method of preparing the same | |
| KR101830949B1 (en) | Preparing method for producing an organic-inorganic particle, organic-inorganic coating solution and organic-inorganic film having water repellency | |
| CN1280237C (en) | Coating material of antenna housing and its preparation | |
| CN1709989A (en) | Composite electromagnetic wave shielded coating and its preparing method | |
| JP5037760B2 (en) | Epoxy resin varnish for resin substrates | |
| CN120157138A (en) | Hollow silica particles and preparation method and application thereof | |
| CN119931102A (en) | A glass fiber reinforced epoxy resin composite material 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: 20060503 Termination date: 20110531 |