The invention relates to a high-temperature heat shield based on phase change heat storage and an aircraft spray pipe assembly, and relates to the technical field of aerospace craft design, the high-temperature heat shield comprises an aerogel layer and a phase change heat storage packaging layer which are sequentially distributed from a spray pipe to a cabin section and connected, and the phase change heat storage packaging layer comprises a packaging shell and a phase change energy storage material; an accommodating cavity is formed in the packaging shell; the accommodating cavity is filled with the phase change energy storage material; and the thickness of the aerogel layer is adapted as follows: after a heat source of the spray pipe is subjected to heat insulation through the aerogel layer, heat transferred to the phase change heat storage packaging layer reaches the phase transition temperature of the phase change energy storage material. The aircraft spray pipe assembly comprises a spray pipe and a cabin section, and a heat insulation space is formed between the cabin section and the spray pipe; and the high-temperature heat insulation cover is arranged in the heat insulation space. The aerogel layer isolates and blocks a large amount of heat generated by the spray pipe, the phase change energy storage material absorbs heat and stores energy, the heat entering the cabin section is greatly reduced, the important single-machine working environment in the cabin section is improved, and long-time stable work of the aircraft is achieved.

    本申请涉及一种基于相变储热的高温隔热罩和飞行器喷管组件,涉及航天飞行器设计技术领域,高温隔热罩包括沿喷管至舱段依次分布且相连的气凝胶层和相变储热封装层,相变储热封装层包括封装壳和相变储能材料,封装壳内具有容置腔;相变储能材料填充于容置腔内;以及,气凝胶层的厚度被适配成:喷管的热源经过气凝胶层隔热后,传递至相变储热封装层的热量达到相变储能材料的相转变温度。飞行器喷管组件包括喷管和舱段,舱段与喷管之间形成有隔热空间;高温隔热罩设于隔热空间内。气凝胶层将喷管产生的大量热量隔离阻挡,相变储能材料吸热储能,大幅度降低进入舱段内部的热量,改善舱段内部重要单机工作环境,实现飞行器长时间稳定工作。


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    Titel :

    High-temperature heat shield based on phase change heat storage and aircraft nozzle assembly


    Weitere Titelangaben:

    基于相变储热的高温隔热罩和飞行器喷管组件


    Beteiligte:
    MAO JING (Autor:in) / LIU LIHONG (Autor:in) / TU ZHENGGUANG (Autor:in) / WANG HUI (Autor:in) / XU WENBO (Autor:in) / MAO JINDI (Autor:in) / GAO XU (Autor:in) / WANG YUANJIE (Autor:in) / SHAN HUAWEI (Autor:in) / WU JIHUA (Autor:in)

    Erscheinungsdatum :

    2022-07-15


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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