The invention discloses a thermal insulation/protection integrated space debris protection structure and an application thereof. The protection structure is formed by stacking a front plate and a filled layer, wherein the filled layer is formed by alternately stacking SiC fibre fabrics and ceramic fibre-reinforced SiO2 nanometre aerogel plates in pairs, and one side of each SiC fibre fabric is close to the front plate. The protection structure is applied to thermal insulation and debris protection for a spacecraft, the protection performance is obviously superior to the protection performance of a Nextel/Kevlar filled protection structure under the same surface density, puncture damages are avoided, the thermal insulation performance is good, and the thermal conductivity is not greater than 0.023W/m.K; the mass of the filled layer of the protection structure is not greater than 1.08kg, and the thermal insulation/protection integrated effect can be acted at a higher temperature in case of an equivalent mass compared with the traditional filled Whipple protection structure; and the different requirements of thermal insulation, debris protection and weight reduction can be met by changing the thickness of the filled layer, and the designability is high.


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    Titel :

    Thermal insulation/protection integrated space debris protection structure and application thereof


    Beteiligte:
    WANG YINGDE (Autor:in) / HAN CHENG (Autor:in) / FENG JIAN (Autor:in) / JIANG YONGGANG (Autor:in)

    Erscheinungsdatum :

    02.12.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS





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