Abstract: A composite structure containing a weave and a rigidifying resin matrix is formed in a hollow configuration with inwardly directed ring stiffeners. This is achieved by arranging longitudinal strands in radial rows or groups around a base mandrel and weaving a circumferential strand through the longitudinal strands. When a wall section of normal width is desired, a submandrel is placed around the base mandrel and those longitudinal strands located innermost in their respective groups are passed behind the submandrel so that the circumferential strand is woven only through the longitudinal strands located outwardly from the submandrel. Where a ring stiffener is desired, the thickness of the weave is increased by weaving the circumferential strand through all of the longitudinal strands located beyond the base mandrel, and this of course takes place beyond the end of the submandrel. Longitudinal stiffeners may be provided along with the ring stiffeners by forming depressions in the submandrels.

Abstract: A multidimensional woven, resinous impregnated, rocket nozzle structure composed of fibers running along the longitudinal axis of the nozzle and positioned radially in conformance with the general shape of the nozzle with a weaving fiber under tension and running circumferentially and radially normal to the said longitudinal axis to interlock with said longitudinal fibers in at least three directions.

Abstract: A loom includes a take-up assembly to which the forward ends of longitudinal strands are attached and a tensioning assembly to which the rear ends of the strands are connected. The tensioning assembly maintains the strands taut and further arranges the strands in a predetermined array in which a plurality of strands exist in both crosswise directions. A shedding assembly is located between the take-up assembly and tensioning assembly and includes a plurality of vertical wires which pass crosswise through the array and a plurality of horizontal wires which also pass crosswise through the array. The vertical and horizontal wires are arranged in pairs with the two wires of each pair being on opposite sides of the longitudinal centerline for the array and spaced equally therefrom. Each pair of wires is supported on a single cable system having an actuator. The actuator when energized moves the cable system such that the wires either move together or spread apart.

Abstract: The combustion chambers of ramjet-powered missiles must be thermally insulated to protect adjacent equipment from combustion gas temperatures of 3000.degree. F. or greater. Thermal protection is accomplished in the present disclosure by the hot wall carbon/carbon combustor, and an intermediate-temperature insulation layer composed of "MIN-K 2000" a proprietary product of the Manville Corporation. A portion of the "MIN-K 2000" insulation is allowed to experience temperatures greater than its maximum rated value of 2,000.degree. F. and thermally degrade in the one-time use to which the disclosure is put. However, virgin layers of the "MIN-K" insulation still protect the structure, fuel and electrical components adjacent to the combustion chamber from heat shorts. The present disclosure minimizes the weight and volume of the thermal protection system, resulting in increased missile performance.