The invention belongs to the field of aerospace heat insulation materials, and discloses a composite heat insulation cover which comprises a heat insulation layer and a heat insulation disc. A heat insulation layer is arranged in the maximum heat flow direction of the heat insulation disc; wherein the heat insulation layer is of a SiO2 aerogel/fiber sandwich structure, and the heat insulation disc is of a multi-layer composite structure which is integrally formed at a time by adopting a co-injection RTM (Resin Transfer Molding) process. The present invention realizes a heat-insulating member having low density, high specific strength, high toughness, and excellent heat-insulating performance. The invention is suitable for a hot-end heat insulation component of a spacecraft, has the characteristics of low density, high specific surface area, high porosity, low thermal conductivity and the like, overcomes the defects of process processing difficulty of injection temperature and curing system of two different resins, low reliability and the like, solves the difficulty of integrated design of the heat insulation component, and meets the requirements of component structural strength, high heat conductivity and the like. The requirements on heat conductivity coefficient and weight are effectively reduced.
本发明属于航空航天隔热材料领域,公开了一种复合材料隔热罩,包括隔热层和隔热盘;在隔热盘的热流最大方向设置隔热层;其中,隔热层为SiO2气凝胶/纤维夹芯结构,隔热盘为采用共注射RTM工艺一次整体成型的多层复合结构。本发明实现了一种低密度、高比强度、高韧性,具有优异的隔热性能的隔热部件。本发明适用于空间飞行器的热端隔热部件,具有低密度,高比表面积,高孔隙率、低导热率等特点,克服了两种不同树脂的注射温度、固化制度的工艺加工难题、可靠性低等缺点,本发明解决了隔热部件一体化设计的难点,满足了部件结构强度,有效降低导热系数和重量的要求。
Composite material heat shield
一种复合材料隔热罩
2022-04-12
Patent
Electronic Resource
Chinese