Abstract: The hybrid rocket system of this invention is characterized by use of an oxidizer tank having a cylindrical midsection surrounded by a skirt and bonded thereto by a layer of elastomeric adhesive. The skirt outer surface is in turn adhesively secured to a spacecraft inner surface. An elongated solid-fuel motor case is mechanically rigidly secured to a central rear surface of the tank, and the case terminates in a throat and nozzle. The elastomeric-adhesive bonding of tank to skirt, and rigid adhesion of skirt to spacecraft forms the sole support for the rocket system, and separate support for the motor case is not required.

Abstract: A rocket-powered spacecraft having a wing which has hinged aft portions which can be elevated about a hinge line. Tail booms extend rearwardly from the outer ends of the aft wing portions, and rudders are mounted at the aft ends of the booms. Each tail boom supports a horizontal tail with an elevon at its trailing edge. In normal flight, the wing aft portions are not elevated, and the wing has a normal airfoil shape. During atmosphere reentry, the wing aft portions are steeply elevated to provide a stable high-drag altitude for the spaceship for speed reduction at low thermal and structural loading. After reentry, the aft wing is returned to an unelevated position which enables gliding flight to a horizontal-runway landing.