Abstract: A two-stage space vehicle is provided for achieving low earth orbit that includes a carrier and an orbiter. The carrier has a large airfoil area relative to its dry weight, and the thrust of the rocket engine is controlled such that the carrier achieves a launch altitude and speed for the orbiter without exceeding a wingloading pressure beyond 3,500 Pa., which allows the carrier to be inexpensively constructed. Liquid propellant for the rocket engine is advantageously stored within the relatively large airfoil of the carrier, which is preferably a delta wing. The ratio of airfoil area to dry weight is about 33 m2 per ton, which allows the carrier to descend and land after launching the orbiter with low wingloading on the order of 300 Pa.

Abstract: A heat-resistive wall assembly for a space vehicle is disclosed herein comprising an inner wall formed from either wrought beryllium or aluminum for providing both structural support for the vehicle, as well as a heat sink which equilibrates the heat gradient around the vehicle during reentry, an outer wall preferably formed from interlocking panels of a honeycomb laminate of a heat resistive metal such as Inconel.RTM. 617, and an evacuated jacket formed from an envelope of nickel foil which is disposed between the inner and outer walls. The evacuated jacket contains an insulating material formed from alternating layers of a sheet material made from nonwoven quartz fibers, and sheets of nickel foil. Even though the interior of the wall assembly is exposed to ambient atmospheric pressure, such atmospheric pressure is insufficient to compress the evacuated jacket during the maximum heat experienced by the vehicle during reentry into the atmosphere.