CN103101262B - High temperature-resistant and heat insulating sandwich structure composite material and preparation method thereof - Google Patents
High temperature-resistant and heat insulating sandwich structure composite material and preparation method thereof Download PDFInfo
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- CN103101262B CN103101262B CN201310053314.3A CN201310053314A CN103101262B CN 103101262 B CN103101262 B CN 103101262B CN 201310053314 A CN201310053314 A CN 201310053314A CN 103101262 B CN103101262 B CN 103101262B
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Abstract
The invention relates to a high temperature-resistant and heat insulating sandwich structure composite material and a preparation method thereof. The high temperature-resistant and heat insulating sandwich structure composite material is composed of an upper surface layer, a core layer, and a lower surface layer. The core layer is a high temperature-resistant fiber reinforced aerogel composite material, and the upper surface layer and the lower surface layer are both a high temperature-resistant fiber reinforced high temperature-resistant resin composite material. The thickness of the core layer is 3-200mm, and the thickness of the upper surface layer and the lower surface layer is 0.1-5.0mm respectively. The invention also includes a preparation method of the high temperature-resistant and heat insulating sandwich structure composite material. The high temperature-resistant and heat insulating sandwich structure composite material provided in the invention has the advantages of good high temperature resistance, low thermal conductivity, as well as good heat insulation effect. At the same time, with greatly improved strength and toughness and substantially reduced molding process difficulty, the high temperature-resistant and heat insulating sandwich structure composite material can be better suitable for aerospace and other fields.
Description
Technical field
The present invention relates to a kind of high temperature resistant heat insulation sandwich structure composite material and preparation method thereof.
Background technology
High-speed aircraft is high speed flying for long time in an atmosphere, and its external fuselage temperature is more than 200 DEG C, and part reaches 400 DEG C.For preventing high temperature to the infringement of internal unit, high efficiency heat insulation material manufacture must be adopted.
The heat-barrier materials such as traditional polyurethane foam have good effect of heat insulation at normal temperatures, but temperature tolerance is generally lower than 200 DEG C, are difficult to reach heatproof requirement.
U.s. space shuttle uses ceramic insulation watt to play important function, but the problems such as low toughness (being generally 1-5MPa × m1/2), low-intensity (being generally less than 5MPa), thermal conductivity higher (being generally greater than 0.06W/m × k) and single-piece area little (being generally 200 × 200mm) that tool is intrinsic, fail to adapt to the heat insulation highly reliable and high efficiency demand of high-speed aircraft large area very well, and price is very expensive.The low toughness of ceramic insulation watt makes, in production, transport, installation and flight course, easily to produce brittle break, there is larger potential safety hazard; Low-intensity is also that one of key factor destroyed occurs ceramic insulation watt; Fragility adds low-intensity, easily causes producing stress rupture between Rigid ceramic tile with bonding matrix, and this is the key factor that Rigid ceramic tile single-piece area is less; Little single-piece area makes again the difficulty of installation strengthen, and leaves numerous reluctant gap; The thermal conductivity of Rigid ceramic tile is comparatively large, certainly will increase ceramic tile thickness, reduce aircraft dischargeable capacity and payload.
The aerogel composite grown up in recent years has good effect of heat insulation, and heatproof is greater than 400 DEG C, but the intensity of this material is not high, not resistance to erosion, therefore, can not be directly used in outside anti-heat insulation.
Summary of the invention
Technical problem to be solved by this invention is, provides a kind of high temperature resistant, good heat-insulation effect, simultaneously high temperature resistant heat insulation sandwich structure composite material of being also greatly improved of intensity and toughness and preparation method thereof.
The technical scheme that the present invention solves the employing of its technical problem is:
The high temperature resistant heat insulation sandwich structure composite material of the present invention, be made up of upper surface layer, sandwich layer, undersurface layer, described sandwich layer is that high-temperature fibre strengthens aerogel composite, and described upper surface layer, undersurface layer are high-temperature fibre and strengthen fire resistant resin composite; The thickness of described sandwich layer is the preferred 5-100mm of 3-200mm(, more preferably 10-50mm), the thickness of described upper surface layer, undersurface layer is respectively the preferred 0.5-2.0mm of 0.1-5.0mm().
Further, described high-temperature fibre strengthens aerogel composite by the high-temperature fibres such as carbon fiber, quartz fibre, alumina fibre, short basalt fiber, mullite fiber or silicon carbide fibre and aerosil, alumina aerogels or silica and aluminium oxide binary aerogel, or the aeroge such as carbon aerogels forms.
Further, described high-temperature fibre strengthens the density of aerogel composite is 0.2-0.9g/cm
3, thermal conductivity≤0.2W/m × K.
Further, described high-temperature fibre enhancing fire resistant resin composite is made up of fire resistant resins such as the high-temperature fibres such as carbon fiber, quartz fibre, alumina fibre, mullite fiber or silicon carbide fibre and polyimides, polysiloxanes, polysilazane, polybenzimidazoles or polybenzoxazoles.
The preparation method of the high temperature resistant heat insulation sandwich structure composite material of the present invention, comprises the following steps:
(1) selecting high-temperature fibre to strengthen aerogel composite is core material, and the thickness of core material is 3-200mm;
(2) at sandwich layer upper and lower surface tiling high-temperature fibre cloth or thin layer stereo fabric, then carry out acupuncture, puncture or sew up process, to make high-temperature fibre cloth or thin layer stereo fabric combine with sandwich layer, the thickness 0.1-5.0mm of described high-temperature fibre cloth or thin layer stereo fabric;
(3) spray fire resistant resin respectively on the upper and lower surface of gained fabric, to 40% of volume fraction >=gap shared by institute's jetting liquid, at room temperature hang 1-3 hour, then use mold cramping, at being placed in 30-400 DEG C, make it solidify; Or adopt resin transfer molding (RTM) process forming surface flaggy;
(4) room temperature is cooled to, the demoulding.
Further, in step (1), high-temperature fibre used strengthens aerogel composite by the high-temperature fibres such as carbon fiber, quartz fibre, alumina fibre, short basalt fiber, mullite fiber or silicon carbide fibre and aerosil, alumina aerogels or silica and aluminium oxide binary aerogel, or the method for the aeroge employing supercritical drying such as carbon aerogels is made.
Further, in step (1), the density that described high-temperature fibre strengthens aerogel composite is 0.2-0.9g/cm
3, thermal conductivity≤0.2W/m × K.
Further, in step (2), described high-temperature fibre can be carbon fiber, quartz fibre, alumina fibre, mullite fiber or silicon carbide fibre etc.; Acupuncture, puncture or stitching process adopt quartz fibre or carbon fiber etc., and acupuncture, puncture or stitch pitch are 2-40mm.
Further, in step (3), described fire resistant resin can be polyimides, polysiloxanes, polysilazane, polybenzimidazoles or polybenzoxazoles etc.
The high temperature resistant heat insulation sandwich structure composite material of the present invention, sandwich layer is that high-temperature fibre strengthens aerogel composite, upper surface layer, undersurface layer are high-temperature fibre and strengthen fire resistant resin composite, its resistance to elevated temperatures is good, thermal conductivity is low, good heat-insulation effect, and intensity and toughness are also greatly improved simultaneously, moulding process difficulty significantly reduces, and can better be applicable to the fields such as Aero-Space.
Detailed description of the invention
Below in conjunction with embodiment, the invention will be further described.
Embodiment 1
The high temperature resistant heat insulation sandwich structure composite material of the present embodiment, be made up of upper surface layer, sandwich layer, undersurface layer, described sandwich layer is that Short Mullite Fibre strengthens silicon dioxide silica aerogel composite material, and described upper surface layer, undersurface layer are quartz fiber cloth and strengthen composite polyimide material; The thickness of described sandwich layer is 20mm, and the density of core material is 0.32g/cm
3, thermal conductivity is 0.028W/m × K, and the thickness of described upper surface layer is 0.8mm, and the thickness of undersurface layer is 0.6mm.
Preparation method, comprises the following steps:
(1) selecting Short Mullite Fibre to strengthen silicon dioxide silica aerogel composite material is core material, and the thickness of sandwich layer is 20mm;
Described Short Mullite Fibre strengthen silicon dioxide silica aerogel composite material adopt the preparation of the method for supercritical drying (can refer to Chinese patent 200510031952.0,200710034510.0,201110110844.8,201110110947.4, method disclosed in 201110110946.X, 201010300112.0 or 201010148105.3 carries out), density is 0.32g/cm
3, thermal conductivity is 0.028W/m × K;
(2) quartz fiber cloth that the 1 layer of 0.8mm that tile respectively on the upper and lower surface of sandwich layer is thick, then carries out stitching process; Sew up the quartz fibre that the fiber adopted is 380Tex, every two suture spacing are 15mm;
(3) in step (2) gained quartz fiber cloth " covering " surface spraying polyimide solution, be 40% of gap to volume fraction shared by institute's jetting liquid, at room temperature hang 1 hour, then use mold cramping, solidify at 370 DEG C;
(4) room temperature is cooled to, the demoulding.
The density of the present embodiment gained high temperature resistant heat insulation sandwich structure composite material is 0.45g/cm
3, its key property is in table 1.
The key property of table 1 embodiment 1 high temperature resistant heat insulation sandwich structure composite material
| Resistance to elevated temperatures | Be greater than 450 DEG C |
| Thermal conductivity (W/m × k) | 0.04 |
| Equivalent dielectric Changshu | 1.8 |
| Equivalent loss tangent | 0.004 |
| Panel normal temperature hot strength (MPa) | 280 |
| Panel normal temperature stretch modulus (Gpa) | 6 |
| Fracture elongation | 1.2% |
| Panel 450 DEG C of hot strengths (MPa) | 270 |
Embodiment 2
The high temperature resistant heat insulation sandwich structure composite material of the present embodiment, be made up of upper surface layer, sandwich layer, undersurface layer, described sandwich layer is that short basalt fiber strengthens silicon dioxide silica aerogel composite material, and described upper surface layer, undersurface layer are carbon cloth and strengthen polysilazane composite; The thickness of described sandwich layer is 25mm, and the density of core material is 0.30g/cm
3, thermal conductivity is 0.022W/m × K, and the thickness of described upper surface layer is 1.2mm, and the thickness of undersurface layer is 0.8mm.
Preparation method, comprises the following steps:
(1) selecting short basalt fiber to strengthen silicon dioxide silica aerogel composite material is core material, and the thickness of sandwich layer is 25mm;
Described short basalt fiber strengthen silicon dioxide silica aerogel composite material adopt the preparation of the method for supercritical drying (can refer to Chinese patent 200510031952.0,200710034510.0,201110110844.8,201110110947.4, method disclosed in 201110110946.X, 201010300112.0 or 201010148105.3 carries out), density is 0.30g/cm
3, thermal conductivity is 0.022W/m × K;
(2) carbon cloth that the 2 layers of 0.6mm that tile respectively on the upper and lower surface of sandwich layer is thick, then carries out stitching process; Sew up the carbon fiber that the fiber adopted is 400Tex, every two suture spacing are 15mm;
(3) in step (2) gained carbon cloth " covering " surface spraying polysilazane solution, be 40% of gap to volume fraction shared by institute's jetting liquid, at room temperature hang 2 hours, then use mold cramping, solidify at 300 DEG C;
(4) room temperature is cooled to, the demoulding.
The density of the present embodiment gained high temperature resistant heat insulation sandwich structure composite material is 0.48g/cm
3, its key property is in table 2.
The key property of table 2 embodiment 2 high temperature resistant heat insulation sandwich structure composite material
| Resistance to elevated temperatures | Be greater than 450 DEG C |
| Thermal conductivity (W/m × k) | 0.035 |
| Panel normal temperature hot strength (MPa) | 350 |
| Panel normal temperature stretch modulus (Gpa) | 7 |
| Fracture elongation | 1.3% |
| Panel 450 DEG C of hot strengths (MPa) | 320 |
Embodiment 3
The high temperature resistant heat insulation sandwich structure composite material of the present embodiment, be made up of upper surface layer, sandwich layer, undersurface layer, described sandwich layer is that Short Mullite Fibre strengthens alumina aerogels composite, and described upper surface layer, undersurface layer are carbon cloth and strengthen polysilazane composite; The thickness of described sandwich layer is 20mm, and the density of core material is 0.32g/cm
3, thermal conductivity is 0.029W/m × K, and the thickness of described upper surface layer is 1.2mm, and the thickness of undersurface layer is 0.8mm.
Preparation method, comprises the following steps:
(1) selecting profound Short Mullite Fibre to strengthen alumina aerogels composite is core material, and the thickness of sandwich layer is 20mm;
Described Short Mullite Fibre strengthen alumina aerogels composite adopt the preparation of the method for supercritical drying (can refer to Chinese patent 200510031952.0,200710034510.0,201110110844.8,201110110947.4, method disclosed in 201110110946.X, 201010300112.0 or 201010148105.3 carries out), density is 0.32g/cm
3, thermal conductivity is 0.029W/m × K;
(2) carbon cloth that the 1 layer of 1.0mm that tile respectively on the upper and lower surface of sandwich layer is thick, then carries out stitching process; Sew up the carbon fiber that the fiber adopted is 400Tex, every two suture spacing are 15mm;
(3) in step (2) gained carbon cloth " covering " surface spraying polysilazane solution, be 40% of gap to volume fraction shared by institute's jetting liquid, at room temperature hang 2 hours, then use mold cramping, solidify at 300 DEG C;
(4) room temperature is cooled to, the demoulding.
The density of the present embodiment gained high temperature resistant heat insulation sandwich structure composite material is 0.48g/cm
3, its key property is in table 3.
The key property of table 3 embodiment 3 high temperature resistant heat insulation sandwich structure composite material
| Resistance to elevated temperatures | Be greater than 470 DEG C |
| Thermal conductivity (W/m × k) | 0.042 |
| Panel normal temperature hot strength (MPa) | 390 |
| Panel normal temperature stretch modulus (Gpa) | 8 |
| Fracture elongation | 1.4% |
| Panel 450 DEG C of hot strengths (MPa) | 310 |
Claims (4)
1. a high temperature resistant heat insulation sandwich structure composite material, be made up of upper surface layer, sandwich layer, undersurface layer, it is characterized in that: described sandwich layer is that high-temperature fibre strengthens aerogel composite, and described upper surface layer, undersurface layer are high-temperature fibre and strengthen fire resistant resin composite; The thickness of described sandwich layer is 3-200mm, and the thickness of described upper surface layer, undersurface layer is respectively 0.1-5.0mm;
The preparation method of described high temperature resistant heat insulation sandwich structure composite material, comprises the following steps:
(1) selecting high-temperature fibre to strengthen aerogel composite is core material, and the thickness of sandwich layer is 3-200mm;
(2) at sandwich layer upper and lower surface tiling high-temperature fibre cloth or thin layer stereo fabric, then carry out acupuncture, puncture or sew up process, to make high-temperature fibre cloth or thin layer stereo fabric combine with sandwich layer, the thickness 0.1-5.0mm of described high-temperature fibre cloth or thin layer stereo fabric;
(3) spray fire resistant resin respectively on the upper and lower surface of gained fabric, to 40% of volume fraction >=gap shared by institute's jetting liquid, at room temperature hang 1-3 hour, then use mold cramping, at being placed in 30-400 DEG C, make it solidify;
(4) room temperature is cooled to, the demoulding.
2. high temperature resistant heat insulation sandwich structure composite material according to claim 1, it is characterized in that: described high-temperature fibre strengthens aerogel composite by carbon fiber, quartz fibre, alumina fibre, short basalt fiber, mullite fiber or silicon carbide fibre, with aerosil, alumina aerogels or silica and aluminium oxide binary aerogel, or carbon aerogels composition.
3. high temperature resistant heat insulation sandwich structure composite material according to claim 2, is characterized in that: the density that described high-temperature fibre strengthens aerogel composite is 0.2-0.9g/cm
3, thermal conductivity≤0.2W/mK.
4. high temperature resistant heat insulation sandwich structure composite material according to claim 1 and 2, it is characterized in that: described high-temperature fibre strengthens fire resistant resin composite by carbon fiber, quartz fibre, alumina fibre, mullite fiber or silicon carbide fibre, forms with polyimides, polysiloxanes, polysilazane, polybenzimidazoles or polybenzoxazoles.
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