Abstract: Arrangement for the thermal protection of an object, particularly a space vehicle, such as a space missile, including a frame structure covered with thermal insulating material, wherein the material is made of an aggregate of carbon or silica short fibers, the fibers being linked together by means of a binder made of the same constituent and possibly of an appropriate resin. The aggregate is in the form of at least one monobloc element, which is accordingly shaped and dimensioned, and adhered onto the frame structure.

Abstract: A device for retaining an object to a support and then separating it therefrom in a controlled sequence embodying a receptacle to be fixed to the support, a chimney fixed to the receptacle and a retaining sleeve adapted to couple a bearing surface of the object to a bearing surface of the receptacle or to release it. A piston slides along the chimney and has a locking configuration in which it holds the retaining sleeve in place and a release configuration. An ejector piston slides in the chimney to eject the object. Drive pressure operates first on the piston until it can operate on the ejector piston at the end of the movement of the piston.