Abstract: A thermal protection system suitable as a heat shield for a space vehicle includes a flexible insulation mat that is adhesively bonded onto the outer skin of the space vehicle, a cover layer made of at least one ply of a ceramic fiber composite material secured onto the insulation mat, and a coating of an inorganic material applied onto an outer surface of the ceramic cover layer. The cover layer is secured to the insulation mat by adhesive bonding, stitching with ceramic threads or the like, or by a snap fastener button connection. The ceramic fiber composite materials of the cover layer include inorganic fibers which are preferably oxides, carbides or mixtures thereof embedded in a matrix of the same compositional components, whereby the components can be selected appropriately depending on the requirements of the particular application.