Abstract: A reversible thermal compensation joint having a ceramic fairing (20) with a spindle (24) slidably engaged within a metal hinge housing (22). The spindle (24) has a groove (28) with inwardly converging side walls (36) and a flat bottom (38) in which is seated a plurality of arcuate ring sections (30). The ring sections (30) have inwardly converging sides (40) that substantially match the side walls (36) of the groove (28). The ring sections (30) are formed of the same material as the hinge housing (22), such that upon thermal expansion of the reversible thermal compensation joint (10), the ring sections (30) slide up the walls (36) to maintain a tight fit with the expanding hinge housing (22).

Abstract: A thermal stress-free joint assembly for joining a low thermal expansion member and a high thermal expansion member uses a fastener and a bushing fitted within a bore in the low thermal expansion member, wherein the fastener and bushing materials are selected to have predetermined coefficients of thermal expansion. The fastener includes a shank which passes through the bore in the low thermal expansion member. The bushing, bore and shank are dimensioned according to a mathematical relationship to maintain a predetermined clearance or preload as the joint undergoes changes in temperature, without damage to either joined member from thermally induced stress.

Abstract: A missile body and related method for producing a missile body comprising a plurality of coaxially disposed contiguous body sections wherein each body section is a structure having a cross-sectional configuration corresponding to a respective cross section of the missile body, means for fixedly attaching the contiguous body sections together axially to form a hull, and an outer skin physically engaging the hull and constituting the outer skin of the missile body.

Abstract: An integral cooling system for high temperature missile structures which is essentially a passive cooling system integrated into the missile structure. An evaporative material carried in the missile structure is ejected by vapor pressure through openings in the missile's outer skin and cools the missile as it flows along the outer surface thereof.