A high-temperature resistant lightweight
composite material, its preparation method, and its applications are disclosed, relating to the field of
composite material technology. This invention solves the problems of existing materials where it is difficult to simultaneously achieve high
temperature resistance and lightweight, low structural efficiency due to the separation of heat protection and load-
bearing design, insufficient
temperature resistance and
toughness of the sandwich layer, and difficulties and high costs associated with large-size molding. The material comprises an integrated co-cured outer heat-resistant layer, an intermediate
transition layer, and an inner load-bearing layer. The outer heat-resistant layer uses a modified
epoxy /
cyanate copolymer resin as the matrix and a high-
silica glass fiber and carbon
fiber blended fabric as reinforcement, with
fumed silica and
carbon nanotube fillers incorporated into the matrix resin. The intermediate
transition layer is polymethacrylamide foam. The inner load-bearing layer uses an
epoxy-modified
cyanate ester resin as the matrix and a carbon
fiber biaxial
plain weave fabric as reinforcement. This invention can be used in
rocket fairings, hypersonic vehicle skins,
spacecraft reentry
capsule thermal protection structures, hypersonic
missile shells, aircraft engine nacelles, or high-speed
train front fairings.