抄録
One of the key technologies of Reusable Launch Vehicle (RLV) is thermal structures. This paper describes on advanced thermal structures studied by Mitsubishi Heavy Industries, Ltd. (MHI) for future application. Carbon fiber reinforced Silicone Carbide (C/SiC) hot structure is a candidate for control surfaces of RLV. MHI has developed C/SiC samples by combining Japanese 3-D woven fiber technology with French Chemical Vapor Infiltration (CVI) matrix technology.
