Abstract: A circular loom which holds multiple longitudinal threads is able to weave them into a three-dimensional fabric using a filament insertion device which supplies it with multiple circumferential threads and a supply of weaver thread. One version of the filament insertion device uses two spools of circumferential thread which each have feed tubes and tensionmeters which supply two lines of circumferential thread to a filament insertion device tip so that it may dispense two circumferential threads with adjustable tensions simultaneously to said circular loom. A weaver spool and weaver feed tube supply the filament insertion device tip with a tensionless supply of weaver thread so that it may dispense weaver thread when required.

Abstract: An improved nozzle structure for an engine, such as a ramjet, rocket or turbojet, which generates thrust by expulsion of gaseous fuel combustion products along a thrust axis is described which comprises an annular wall structure defining an inlet and an outlet for the nozzle and having a contoured inner surface defining near the inlet a radially inwardly convergent annular ramp of predetermined length and convergence angle, near the outlet a radially outwardly divergent annular ramp of predetermined length and divergence angle, and a nozzle throat of predetermined diameter at the juncture of the annular ramps; a transverse web member disposed at the nozzle throat and extending diametrically of the annular wall, defining two substantially symmetrical passageways through the nozzle, having a leading edge near the inlet and trailing edge near the outlet, and having a double wedge shaped cross section symmetric with respect to a plane containing the thrust axis, the surface of the web member defining a pair of ra

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.