CN104356605A - Light prepreg for unmanned aerial vehicle shell and preparation method of prepreg - Google Patents
Light prepreg for unmanned aerial vehicle shell and preparation method of prepreg Download PDFInfo
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- CN104356605A CN104356605A CN201410755847.0A CN201410755847A CN104356605A CN 104356605 A CN104356605 A CN 104356605A CN 201410755847 A CN201410755847 A CN 201410755847A CN 104356605 A CN104356605 A CN 104356605A
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Abstract
The invention discloses a light prepreg for an unmanned aerial vehicle shell and a preparation method of the prepreg, relating to a prepreg and a preparation method thereof. The prepreg disclosed by the invention is made of epoxy resin system penetrated reinforcing material, wherein the epoxy resin system consists of the following components in percentage by mass: 30-80 percent of epoxy resin mixture, 1-20 percent of nano particles, 1-10 percent of hollow microspheres and 5-40 percent of curing agent system mixture; the epoxy resin mixture is prepared by mixing the components in percentage by mass: 20-60 percent of solid state or semi-solid state epoxy resin and 40-80 percent of liquid epoxy resin; and the curing agent system mixture is formed by mixing the components in percentage by mass: 40-90 percent of curing agent and 10-60 percent of curing agent. The prepreg can be cured at 60 DEG C and is suitable for low-pressure molding processes such as a vacuum bag molding process. The cured prepreg has small density, high strength and excellent dielectric properties and is suitable for preparing light and high-strength unmanned aerial vehicle shells, particularly unmanned aerial vehicle shells with wave-transparent requirements.
Description
Technical field
The present invention relates to a kind of prepreg and preparation method thereof, be specifically related to a kind of unmanned plane housing prepreg and preparation method thereof.
Background technology
Unmanned plane housing will have following characteristics as body platform: the features such as lightweight construction, cost are low, long storage time.Unmanned plane requires higher to loss of weight, only has and airframe-to-fuel weight ratio is controlled below 30%, just can vacate weight-space gives fuel oil, useful load, the stealthy weightening finish brought of compensation, when meeting light structure, long boat, high stealthy, the high technical requirements such as motor-driven.At present the consumption of the unmanned plane matrix material of various advanced person generally accounts for the 60-80% of housing construction gross weight in the world according to statistics, some and be full composite material aircraft.The application of matrix material has following meaning for unmanned plane housing: (1) utilizes advanced composite material high specific strength, the characteristic of high specific stiffness realizes loss of weight, (2) matrix material is convenient to big area monolithic molding in design and fabrication technology, can realize the flying wing type total arrangement of height blended wing-body.
At present for the preparation of method mainly wet method hand paste technique and the prepreg placement process of matrix material unmanned plane housing, wherein prepreg laying forming technique has the features such as uniform quality, resin content is controlled, quality is light, is therefore the main method preparing high performance composite unmanned plane housing.Be not specifically designed to the prepreg of lightweight unmanned plane housing at present, and common prepreg solidification value high (generally at about 120 DEG C), and need the high-pressure molding techniques such as autoclave, manufacturing cost is high, and after solidification, composite density is comparatively large, if the density of carbon fiber/epoxy resin based composites is at 1.6g/cm
3, fail fully to reach the object reducing unmanned plane housing manufacturing cost and abundant loss of weight.
Summary of the invention
In order to solve the existing prepreg solidification value for unmanned plane housing high, need high-pressure molding, density large problem, the invention provides a kind of lightweight unmanned plane housing prepreg and preparation method thereof.
The object of the invention is to be achieved through the following technical solutions:
A kind of lightweight unmanned plane housing prepreg, take epoxy resin as body material, soak into strongthener by epoxy-resin systems to form, described epoxy-resin systems according to mass percent by 30 ~ 80% epoxy resin composition, the nanoparticle of 1 ~ 20%, the tiny balloon of 1 ~ 10% and the curative systems mixture composition of 5 ~ 40%, wherein: epoxy resin composition by mass percentage by 20 ~ 60% solid-state or semi-solid state epoxy resin and 40 ~ 80% liquid-state epoxy resins mix, curative systems mixture is mixed by the solidifying agent of 40 ~ 90% and the promotor of 10 ~ 60% by mass percentage.
A preparation method for above-mentioned lightweight unmanned plane housing prepreg, its concrete steps are as follows:
One, epoxy resin composition is heated to 50 ~ 130 DEG C in the container of drying, constant temperature 0.5 ~ 2 hour, obtain the epoxy resin of melting, add nanoparticle and tiny balloon wherein, stir with the rotating speed of 2000 ~ 5000 turns/min in container, and constant temperature obtains epoxy prepolymer in 0.1 ~ 3 hour at 50 ~ 140 DEG C;
Two, solidifying agent is heated to 50 ~ 100 DEG C in the container of drying, constant temperature 5 ~ 20 hours, adds promotor wherein, in container, carry out stirring 0.5 ~ 2h with the rotating speed of 1700 ~ 3000 turns/min, obtains curative systems mixture;
Three, the epoxy prepolymer in step one and the curative systems mixture in step 2 are joined in dry container, mix and obtain prepreg resin matrix;
Four, the prepreg resin matrix obtained in step 3 constant temperature under the condition of 40 ~ 100 DEG C is polymerized 10 ~ 200 minutes;
Five, with the epoxy-resin systems be polymerized for body material and strongthener hot melt process prepare prepreg.
Advantage of the present invention is as follows:
1, this prepreg can 60 DEG C of solidifications, be applicable to low pressure molding process, as vacuum-bag process technique etc., prepreg after solidification has that density is little, intensity is high, dielectric properties are excellent, is applicable to preparation lightweight, high-strength, especially has the unmanned plane housing that wave transparent requires.
2, this method has that technique is simple, throughput high, has important actual application value.
Embodiment
Below technical scheme of the present invention is further described, but is not limited thereto, everyly technical solution of the present invention is modified or equivalent to replace, and do not depart from the spirit and scope of technical solution of the present invention, all should be encompassed in protection scope of the present invention.
Embodiment one: a kind of lightweight, can 60 DEG C of cured epoxy resin prepregs by lightweight, 60 DEG C of cured epoxy resin systems can soak into strongthener and form, wherein: lightweight, can 60 DEG C of cured epoxy resins according to mass percent by 30 ~ 80% epoxy resin composition, the nanoparticle of 1 ~ 20%, the tiny balloon of 1 ~ 10% and the curative systems mixture composition of 5 ~ 40%, wherein: epoxy resin composition by mass percentage by 20 ~ 60% solid-state or semi-solid state epoxy resin and 40 ~ 80% liquid-state epoxy resins mix, curative systems mixture is mixed by the solidifying agent of 40 ~ 90% and the promotor of 10 ~ 60% by mass percentage.
The minimum solidification value of the prepreg of present embodiment design is 60 DEG C, and lower solidification value can reduce the manufacturing cost of composite products, improves product size stability; This prepreg is applicable to the low pressure molding process such as vacuum forming; Composite density prepared by this type of prepreg is lower than 1.3g/cm
3.
Embodiment two: present embodiment and embodiment one unlike: described solid-state or semi-solid state epoxy resin is the combination of one or more in bisphenol A type epoxy resin, bisphenol-s epoxy resin and novolac epoxy; Liquid-state epoxy resin is the combination of one or more in bisphenol A type epoxy resin, bisphenol f type epoxy resin, bisphenol-s epoxy resin, trifunctional epoxy resin, four-functional group epoxy resin, phenolic resin varnish type epoxy resin and formaldehyde novolac type epoxy resin.
Embodiment three: present embodiment and embodiment one or two are the one in the Nano particles of silicon dioxide of the titanium nanoparticle of rubber-like nano core-shell particle, amino or hydroxyl modified, amino or hydroxyl modified unlike: described nanoparticle.
Embodiment four: present embodiment and embodiment one, two or three unlike: described tiny balloon is the glass hollow microballoon of phenolic aldehyde tiny balloon or surface modification, and wherein the diameter of tiny balloon is less than 0.01mm.
Embodiment five: present embodiment and embodiment one to four unlike: described strongthener is the combination of one or more in high molecular weight polyethylene fiber, sisal fibers, carbon fiber, aramid fiber, aromatic polyamide fibre.Fibers form is unidirectional fibre or fabric, and the mass area ratio of fortifying fibre cloth and the ratio of thickness are 300 ~ 1700; The unit of mass area ratio is g/m
2, the unit of thickness is mm; The Tex number of reinforcing fiber bundles is 100 ~ 10000.
Embodiment six: present embodiments provide for a kind of lightweight, can the preparation method of 60 DEG C of cured epoxy resin prepregs, specifically complete according to the following steps:
One, epoxy resin composition is heated to 50 ~ 130 DEG C in the container of drying, constant temperature 0.5 ~ 2 hour, obtain the epoxy resin of melting, add nanoparticle and tiny balloon wherein, stir with the rotating speed of 2000 ~ 5000 turns/min in container, and constant temperature obtains epoxy prepolymer in 0.1 ~ 3 hour at 50 ~ 140 DEG C;
Two, solidifying agent is heated to 50 ~ 100 DEG C in the container of drying, constant temperature 5 ~ 20 hours, adds promotor wherein, in container, carry out stirring 0.5 ~ 2h with the rotating speed of 1700 ~ 3000 turns/min, obtains curative systems mixture;
Three, the epoxy prepolymer in step one and the curative systems mixture in step 2 are joined in dry container, mix and obtain prepreg resin matrix;
Four, the prepreg resin matrix obtained in step 3 constant temperature under the condition of 40 ~ 100 DEG C is polymerized 10 ~ 200 minutes;
Five, with the epoxy-resin systems of polymerization for body material and strongthener hot melt process prepare prepreg, described epoxy-resin systems is according to the epoxy resin composition of mass percent by 30 ~ 80wt.%, the nanoparticle of 1 ~ 20wt.%, the tiny balloon of 1 ~ 10wt.% and the curative systems mixture composition of 5 ~ 40wt.%, wherein: epoxy resin composition is mixed by the solid-state of 20 ~ 60wt.% or semi-solid state epoxy resin and 40 ~ 80% liquid-state epoxy resins by mass percentage, in curative systems mixture, the consumption of solidifying agent is 40 ~ 90wt.%, the consumption of promotor is 10 ~ 60wt.%.
Embodiment seven: present embodiment and embodiment six unlike: the hot melt process in described step 4 is prepared prepreg method and is: first under film temperature is the condition of 50 ~ 140 DEG C, the intermediate temperature setting epoxy resin be polymerized is prepared into glued membrane, then the glued membrane prepared and strongthener are carried out sweat connecting under preimpregnation temperature is the condition of 50 ~ 140 DEG C.
Embodiment eight: present embodiment and embodiment six to seven unlike: the strongthener in described step 4 is the combination of one or more in carbon fiber, glass fibre, aramid fiber, aromatic polyamide fibre, high molecular weight polyethylene fiber and basalt fibre.
Embodiment nine: present embodiment and embodiment six to eight difference are: described fiber is through pyrrole monomer and FeCl
3saturated solution soak 10 ~ 30 min, soaking temperature is 10 ~ 90 DEG C.
Embodiment ten: a kind of preparation method of lightweight unmanned plane housing prepreg, specifically completes according to the following steps:
One, bisphenol A-type solid epoxy CYD012, trifunctional liquid-state epoxy resin TDE85 are heated to 120 DEG C in the container of drying, constant temperature 1 hour, obtain the epoxy resin of melting, add amido modified titanium nanoparticle and hollow glass micro-ball wherein, stir with the rotating speed of 2000 turns/min in container, and at 120 DEG C constant temperature 1 hour, obtain epoxy prepolymer;
Two, curing agent dicyandiamide is heated to 70 DEG C in the container of drying, constant temperature 8 hours, adds promotor passivation imidazoles wherein, carry out carrying out stirring 1h with the rotating speed of 2000 turns/min in container, obtain curative systems mixture; The curing agent dicyandiamide added by mass percentage in this curative systems mixture is 72.7%; The promotor passivation imidazoles added is 27.3%;
Three, the epoxy prepolymer in step one and the curative systems mixture in step 2 are joined in dry container, mix, namely obtain lightweight, can 60 DEG C of cured epoxy resin systems, in said composition, the mass percent of each composition is: bisphenol A type epoxy resin YD012 is 40%, trifunctional epoxy resin TDE85 is 35%, amido modified titanium nanoparticle is 5%, and hollow glass micro-ball is 10%, and curative systems mixture is 10%.
Four, by the epoxy-resin systems that obtains in step 3 at 80 DEG C, constant temperature polyase 13 0 minute; With the epoxy resin of polymerization for body material and strongthener (the two weight ratio is for 6:5), prepare prepreg by hot melt process; Described strongthener be molecular weight 1,300,000 polyethylene fibre, through pyrrole monomer and FeCl
3saturated solution soak 15min, soaking temperature is 50 DEG C.
The processing performance of the prepreg of present embodiment gained is as shown in table 1.
Table 1 prepeg process performance
| Performance | Feature |
| Viscous at room temperature | Band toughness, can be bonding between prepreg |
| 60 DEG C of gel times | Be less than 120 minutes |
| -18 DEG C of shelf liveves | 90 days |
Prepreg vacuum-bag process technique is prepared matrix material, and its processing parameter is pressure-0.09MPa, and solidification value is first 40 DEG C of constant temperature 1 hour, then 60 DEG C of constant temperature 4 hours, measured composite property was as shown in table 2.
Table 2 composite property
| Performance | Test value |
| Fiber volume fraction | 50% |
| Voidage | 0.8% |
| Density | 1.08g/cm 3 |
Embodiment 11: a kind of intermediate temperature setting epoxy resin is the preparation method of the prepreg of body material, specifically completes according to the following steps:
One, phenol aldehyde type epoxy resin F54, bisphenol A type epoxy resin E51 are heated to 100 DEG C in the container of drying, constant temperature 2 hours, add core shell rubbers nanoparticle and phenolic aldehyde tiny balloon wherein, stir with the rotating speed of 2000 turns/min in container, and at 110 DEG C constant temperature 2 hours, obtain epoxy prepolymer;
Two, curing agent dicyandiamide is heated to 80 DEG C in the container of drying, constant temperature 3 hours, add polyether monoamine solidifying agent D2000 and polyureas vulkacit D yhrad UR500 wherein, in container, carry out stirring 1h with the rotating speed of 2000 turns/min, obtain curative systems mixture; The curing agent dicyandiamide added by mass percentage in this curative systems mixture is 46.7%, and the polyether monoamine solidifying agent D2000 added is 33.3%, and the polyureas vulkacit D yhrad UR500 added is 20%;
Three, the epoxy prepolymer in step one and the curative systems mixture in step 2 are joined in dry container, mix, namely obtain lightweight, can 60 DEG C of cured epoxy resin systems, in said composition, the mass percent of each composition is: phenol aldehyde type epoxy resin F54 is 30%, and the bisphenol A type epoxy resin E51 added is 48%; Core shell rubbers nanoparticle is 5%, and phenolic aldehyde tiny balloon is 10%; Curative systems mixture is 7%.
Four, by the epoxy-resin systems that obtains in step 3 60 DEG C of constant temperature polyase 13s 0 minute; With the intermediate temperature setting epoxy resin of polymerization for body material and strongthener (the two weight ratio is for 7:10) prepare prepreg by hot melt process.Described strongthener is aramid fiber, and tex number is 120, and film temperature is 80 DEG C, preimpregnation temperature 100 DEG C.Through pyrrole monomer and FeCl
3saturated solution soak 10min, soaking temperature is 40 DEG C.
The processing performance testing the prepreg of two gained is as shown in table 3.
Table 3 prepeg process performance
| Performance | Feature |
| Viscous at room temperature | Band toughness, can be bonding between prepreg |
| 60 DEG C of gel times | Be less than 50 minutes |
| -18 DEG C of shelf liveves | 102 days |
This prepreg vacuum bag molding prepares matrix material, and its processing parameter is pressure 0.08MPa, and solidification value is first 40 DEG C of constant temperature 1 hour, then 90 DEG C of constant temperature 1 hour, measured composite property was as shown in table 4.
Table 4 composite property
| Performance | Test value |
| Fiber volume fraction | 55% |
| Voidage | 0.8% |
| Density | 1.28g/cm 3 |
Embodiment 12: a kind of intermediate temperature setting epoxy resin is the preparation method of the prepreg of body material, specifically completes according to the following steps:
One, condensed ring naphthalene type epoxy resin NPTE4000, bisphenol A type epoxy resin E-54 are heated to 120 DEG C in the container of drying, constant temperature 1 hour, obtain the epoxy resin of melting, add amido modified titanium nanoparticle and hollow glass micro-ball wherein, stir with the rotating speed of 2000 turns/min in container, and at 120 DEG C constant temperature 1 hour, obtain epoxy prepolymer;
Two, curing agent dicyandiamide is heated to 70 DEG C in the container of drying, constant temperature 8 hours, adds promotor passivation imidazoles wherein, carry out carrying out stirring 1h with the rotating speed of 2000 turns/min in container, obtain curative systems mixture; The curing agent dicyandiamide added by mass percentage in this curative systems mixture is 60%; The promotor passivation imidazoles added is 30%, and the polyureas vulkacit D yhrad UR300 added is 10%;
Three, the epoxy prepolymer in step one and the curative systems mixture in step 2 are joined in dry container, mix, namely obtain lightweight, can 60 DEG C of cured epoxy resin systems, in said composition, the mass percent of each composition is: condensed ring naphthalene type epoxy resin NPTE4000 is 30%, bisphenol A type epoxy resin E-54 is 45%, amido modified titanium nanoparticle is 5%, and hollow glass micro-ball is 10%, and curative systems mixture is 10%.
Four, by the epoxy-resin systems that obtains in step 3 at 65 DEG C, constant temperature is polymerized 20 minutes; With the epoxy resin of polymerization for body material and strongthener (the two weight ratio is for 6:5), prepare prepreg by hot melt process; Described strongthener be molecular weight 1,500,000 polyethylene fiber peacekeeping carbon fiber T700, the two volume ratio be 7:3. wherein polyethylene fibre through pyrrole monomer and FeCl
3saturated solution soak 15min, soaking temperature is 50 DEG C.
The processing performance of the prepreg of present embodiment gained is as shown in table 5.
Table 5 prepeg process performance
| Performance | Feature |
| Viscous at room temperature | Band toughness, can be bonding between prepreg |
| 60 DEG C of gel times | Be less than 120 minutes |
| -18 DEG C of shelf liveves | 60 days |
Prepreg vacuum-bag process technique is prepared matrix material, and its processing parameter is pressure-0.09MPa, and solidification value is first 50 DEG C of constant temperature 1 hour, then 80 DEG C of constant temperature 2 hours, measured composite property was as shown in table 6.
Table 6 composite property
| Performance | Test value |
| Fiber volume fraction | 50% |
| Voidage | 0.8% |
| Density | 1.22g/cm 3 |
Claims (10)
1. a lightweight unmanned plane housing prepreg, soak into strongthener by epoxy-resin systems to form, it is characterized in that described epoxy-resin systems according to mass percent by 30 ~ 80% epoxy resin composition, the nanoparticle of 1 ~ 20%, the tiny balloon of 1 ~ 10% and the curative systems mixture composition of 5 ~ 40%, wherein: epoxy resin composition by mass percentage by 20 ~ 60% solid-state or semi-solid state epoxy resin and 40 ~ 80% liquid-state epoxy resins mix, curative systems mixture is mixed by the solidifying agent of 40 ~ 90% and the promotor of 10 ~ 60% by mass percentage.
2. lightweight unmanned plane housing prepreg according to claim 1, is characterized in that described solid-state or semi-solid state epoxy resin is the combination of one or more in bisphenol A type epoxy resin, bisphenol-s epoxy resin and novolac epoxy; Liquid-state epoxy resin is the combination of one or more in bisphenol A type epoxy resin, bisphenol f type epoxy resin, bisphenol-s epoxy resin, trifunctional epoxy resin, four-functional group epoxy resin, phenolic resin varnish type epoxy resin and formaldehyde novolac type epoxy resin.
3. lightweight unmanned plane housing prepreg according to claim 1, is characterized in that described nanoparticle is the one in the Nano particles of silicon dioxide of the titanium nanoparticle of rubber-like nano core-shell particle, amino or hydroxyl modified, amino or hydroxyl modified.
4. lightweight unmanned plane housing prepreg according to claim 1, it is characterized in that described tiny balloon is the glass hollow microballoon of phenolic aldehyde tiny balloon or surface modification, the diameter of its tiny balloon is less than 0.01mm.
5. lightweight unmanned plane housing prepreg according to claim 1, is characterized in that described strongthener is the combination of one or more in high molecular weight polyethylene fiber, sisal fibers, carbon fiber, aramid fiber, aromatic polyamide fibre.
6. lightweight unmanned plane housing prepreg according to claim 5, is characterized in that described fibers form is unidirectional fibre or fabric.
7. lightweight unmanned plane housing prepreg according to claim 5, is characterized in that the mass area ratio of described strongthener and the ratio of thickness are 300 ~ 1700; The unit of mass area ratio is g/m
2, the unit of thickness is mm; The Tex number of reinforcing fiber bundles is 100 ~ 10000.
8. a preparation method for lightweight unmanned plane housing prepreg described in the arbitrary claim of claim 1-7, is characterized in that described method concrete steps are as follows:
One, epoxy resin composition is heated to 50 ~ 130 DEG C in the container of drying, constant temperature 0.5 ~ 2 hour, obtain the epoxy resin of melting, add nanoparticle and tiny balloon wherein, stir with the rotating speed of 2000 ~ 5000 turns/min in container, and constant temperature obtains epoxy prepolymer in 0.1 ~ 3 hour at 50 ~ 140 DEG C;
Two, solidifying agent is heated to 50 ~ 100 DEG C in the container of drying, constant temperature 5 ~ 20 hours, adds promotor wherein, in container, carry out stirring 0.5 ~ 2h with the rotating speed of 1700 ~ 3000 turns/min, obtains curative systems mixture;
Three, the epoxy prepolymer in step one and the curative systems mixture in step 2 are joined in dry container, mix and obtain prepreg resin matrix;
Four, the prepreg resin matrix obtained in step 3 constant temperature under the condition of 40 ~ 100 DEG C is polymerized 10 ~ 200 minutes;
Five, with the epoxy-resin systems be polymerized for body material and strongthener hot melt process prepare prepreg.
9. the preparation method of lightweight unmanned plane housing prepreg according to claim 8, it is characterized in that described hot melt process is prepared prepreg method and is: first under film temperature is the condition of 50 ~ 140 DEG C, the epoxy-resin systems of polymerization is prepared into glued membrane, then the glued membrane prepared and strongthener are carried out sweat connecting under preimpregnation temperature is the condition of 50 ~ 140 DEG C.
10. the preparation method of lightweight unmanned plane housing prepreg according to claim 8, is characterized in that described strongthener is through pyrrole monomer and FeCl
3saturated solution soak 10 ~ 30 min, soaking temperature is 10 ~ 90 DEG C.
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Cited By (14)
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|---|---|---|---|---|
| CN105885357A (en) * | 2016-06-28 | 2016-08-24 | 周易 | Heterogeneous toughened resin, carbon fiber prepreg and carbon fiber composite material |
| CN106113738A (en) * | 2016-07-15 | 2016-11-16 | 广东新秀新材料股份有限公司 | Sandwich structure composite material and preparation method thereof |
| CN106317771A (en) * | 2015-07-08 | 2017-01-11 | 深圳光启创新技术有限公司 | Prepreg, preparation method of prepreg and composite material |
| CN107312293A (en) * | 2017-06-14 | 2017-11-03 | 安徽华昊机械制造有限公司 | A kind of preparation method of electric machine casing |
| CN108485205A (en) * | 2018-05-23 | 2018-09-04 | 吕军 | A kind of unmanned plane case material formula of lightweight |
| CN108707311A (en) * | 2018-05-23 | 2018-10-26 | 吕军 | A kind of lightweight unmanned plane organism material of low-density |
| CN108707312A (en) * | 2018-05-23 | 2018-10-26 | 吕军 | Unmanned plane shell made of a kind of composite material |
| CN109467726A (en) * | 2018-10-16 | 2019-03-15 | 厦门大学 | Using glass microballoon reinforcing fiber/polymer matrix composites laminate interlaminar strength Enhancement Method |
| CN109608826A (en) * | 2018-12-04 | 2019-04-12 | 长春安旨科技有限公司 | A kind of fibre reinforced composites |
| CN110776719A (en) * | 2019-10-18 | 2020-02-11 | 合肥工业大学 | Method for dispersing nano inorganic particle filler in solid epoxy resin |
| CN112029457A (en) * | 2020-08-03 | 2020-12-04 | 河北天启通宇航空器材科技发展有限公司 | Light bonding material and preparation method thereof |
| CN112409756A (en) * | 2020-10-20 | 2021-02-26 | 中电科芜湖钻石飞机制造有限公司 | Low-dielectric epoxy resin composition, preparation method thereof and composite material |
| CN113698732A (en) * | 2021-08-31 | 2021-11-26 | 厦门天源欧瑞科技有限公司 | Novel glue, preparation method thereof and preparation process of casing |
| CN114538882A (en) * | 2022-03-08 | 2022-05-27 | 宁波华芯新材料有限公司 | Non-combustible silicate composite material and preparation method thereof |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101287794A (en) * | 2005-08-24 | 2008-10-15 | 亨克尔两合股份公司 | Epoxy compositions having improved impact resistance |
-
2014
- 2014-12-11 CN CN201410755847.0A patent/CN104356605A/en active Pending
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101287794A (en) * | 2005-08-24 | 2008-10-15 | 亨克尔两合股份公司 | Epoxy compositions having improved impact resistance |
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| CN106317771A (en) * | 2015-07-08 | 2017-01-11 | 深圳光启创新技术有限公司 | Prepreg, preparation method of prepreg and composite material |
| CN105885357A (en) * | 2016-06-28 | 2016-08-24 | 周易 | Heterogeneous toughened resin, carbon fiber prepreg and carbon fiber composite material |
| CN106113738A (en) * | 2016-07-15 | 2016-11-16 | 广东新秀新材料股份有限公司 | Sandwich structure composite material and preparation method thereof |
| CN107312293A (en) * | 2017-06-14 | 2017-11-03 | 安徽华昊机械制造有限公司 | A kind of preparation method of electric machine casing |
| CN108707312A (en) * | 2018-05-23 | 2018-10-26 | 吕军 | Unmanned plane shell made of a kind of composite material |
| CN108707311A (en) * | 2018-05-23 | 2018-10-26 | 吕军 | A kind of lightweight unmanned plane organism material of low-density |
| CN108485205A (en) * | 2018-05-23 | 2018-09-04 | 吕军 | A kind of unmanned plane case material formula of lightweight |
| CN109467726A (en) * | 2018-10-16 | 2019-03-15 | 厦门大学 | Using glass microballoon reinforcing fiber/polymer matrix composites laminate interlaminar strength Enhancement Method |
| CN109608826A (en) * | 2018-12-04 | 2019-04-12 | 长春安旨科技有限公司 | A kind of fibre reinforced composites |
| CN110776719A (en) * | 2019-10-18 | 2020-02-11 | 合肥工业大学 | Method for dispersing nano inorganic particle filler in solid epoxy resin |
| CN112029457A (en) * | 2020-08-03 | 2020-12-04 | 河北天启通宇航空器材科技发展有限公司 | Light bonding material and preparation method thereof |
| CN112409756A (en) * | 2020-10-20 | 2021-02-26 | 中电科芜湖钻石飞机制造有限公司 | Low-dielectric epoxy resin composition, preparation method thereof and composite material |
| CN113698732A (en) * | 2021-08-31 | 2021-11-26 | 厦门天源欧瑞科技有限公司 | Novel glue, preparation method thereof and preparation process of casing |
| CN114538882A (en) * | 2022-03-08 | 2022-05-27 | 宁波华芯新材料有限公司 | Non-combustible silicate composite material and preparation method thereof |
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Application publication date: 20150218 |