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Continuous fiber reinforced thermal protection material and preparation method thereof

A heat protection material and continuous fiber technology, applied in chemical instruments and methods, layered products, synthetic resin layered products, etc., can solve the separation of heat protection and heat insulation functions, low heat protection efficiency, large redundant mass, etc. problems, to achieve excellent heat insulation performance and ablation resistance, which is conducive to precise attitude control and low volume density

Pending Publication Date: 2022-02-01
BEIJING INSTITUTE OF TECHNOLOGYGY +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The problem solved by the technology of the present invention is: to overcome the technical problems such as the separation of heat protection and heat insulation functions of traditional thermal protection materials, low thermal protection efficiency, large redundant quality, and poor reliability caused by mechanical connection / bonding combination

Method used

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  • Continuous fiber reinforced thermal protection material and preparation method thereof
  • Continuous fiber reinforced thermal protection material and preparation method thereof
  • Continuous fiber reinforced thermal protection material and preparation method thereof

Examples

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Effect test

Embodiment 1

[0059] The preparation process of the continuous fiber reinforced thermal protection material in this embodiment is shown in figure 1 , including the following steps:

[0060] 1. Weave continuous carbon fiber through orthogonal three-way weaving as a continuous fiber fabric in the ablation-resistant zone, with a thickness of 6mm. The partial weaving structure is shown in Figure 5 As shown; then the continuous carbon fiber is woven through the 2.5D shallow cross-bending layer angle interlocking weaving method as a continuous fiber fabric in the transition zone, with a thickness of 8mm, and its local weaving structure diagram is as follows Figure 4 As shown; then use continuous carbon fiber to weave the continuous fiber fabric as the heat insulation area through the 2.5D shallow cross-direction layer angle interlocking weaving method, the thickness is 26mm, and its partial weaving structure diagram is as follows image 3 Shown; continuous fiber fabric in ablation-resistant zo...

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Abstract

The invention discloses a continuous fiber reinforced thermal protection material and a preparation method thereof. The continuous fiber reinforced thermal protection material comprises an ablation-resistant area, a transition area and a thermal insulation area from surface to inside; the transition area and the thermal insulation area are formed by compounding and curing continuous fiber fabric and thermosetting resin; the ablation-resistant area is formed by compounding and curing a continuous fiber fabric and thermosetting resin and then impregnating with modified phenolic resin, the fiber volume fraction of the ablation-resistant area is greater than that of the transition area, and the fiber volume fraction of the transition area is greater than that of the thermal insulation area. The continuous fiber reinforced integrally-formed multifunctional thermal protection material provided by the invention has the excellent characteristics of light weight, surface ablation resistance, low internal heat conductivity coefficient, strong pyrolysis heat absorption, good surface heat protection effect and the like, and has a reusable application value in a thermal protection system of a hypersonic aircraft.

Description

technical field [0001] The invention relates to the technical field of heat protection materials, in particular to a continuous fiber reinforced heat protection material and a preparation method thereof. Background technique [0002] As humans explore outer space, the thermal protection systems of new aircraft such as next-generation deep space exploration, interstellar voyages, and return and reentry face more severe aerodynamic and thermal environments, such as ballistic and semi-ballistic reentry or when entering, acceleration Large, heat flow, enthalpy and pressure rise sharply, causing the surface temperature to reach above 3000°C; when the lift type reentries or enters, although the heat flow and pressure are relatively low, the re / entry time is long (1000s or even longer), resulting in The total aerodynamic thermal load is exacerbated. Such a harsh aerodynamic thermal environment poses a severe challenge to the effectiveness of thermal protection materials: the harsh...

Claims

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Application Information

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IPC IPC(8): B32B9/00B32B9/04B32B27/02B32B27/34B32B27/12B32B27/04B32B27/42B32B33/00B29C70/48B29C70/54
CPCB32B5/02B32B5/26B32B33/00B29C70/48B29C70/54B32B2260/02B32B2260/046B32B2307/304B32B2307/3065B32B2262/106B32B2262/10B32B2262/101B32B2262/0269
Inventor 张中伟李玮洁蒋祖航王同凯宋欣梁皓然
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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