Abstract: A device for storing a missile 8 includes at least one adjustable and spring-loaded support point 11, 31 and at least two fixed support points 12 and 32 each are present in a launcher tube in the front and in the rear. The front support points 11, 12 act on support pins 10 arranged on the jacket of the missile 8, and the rear support points 12, 32 act on sliding ribs 35 arranged on supports 33 for wings 34 that can be folded out, wherein all support points are supported on frames 3 and 4 of a launching container 1.

Abstract: For the manufacturing of an oxidation-stable component that can withstand temperature changes for space travel, a solid CFC-body with a density of from 0.1 to 0.8 g/cm.sup.3, which has nondirectional short fibers, is made from short carbon fibers and a hardenable resin binder. From the solid CFC-body, a CFC-blank having the dimensions of the component to be manufactured is prepared by means of turning or other material cutting. The CFC-blank is infiltrated with pyrolytic carbon to a density of no more than 1.0 g/cm.sup.3 and then with metallic silicon so that its density amounts to more than 2.0 g/cm.sup.3. A portion of the metallic silicon is reacted with the pyrolytic carbon to form silicon carbide. The proportion of the unreacted metallic silicon which remains in the component after this reaction amounts to at least 15 percent by weight.