Abstract: An integral missile antenna-fuselage assembly (50) is provided for integration into an armament missile (12) which carries primary missile loads, houses internal electronic assemblies, provides mounting surface zones for external sensor antennas (71) , and protects sensitive antenna components from supersonic aerodynamic heating. Each end of the fuselage assembly (50) is formed from a fastener ring (52,54) having a circumferential recess (84,86) which receives a filament wound main structure (60) to form the missile fuselage tube. Preferably, a titanium liner (58) is first joined to each fastener ring with a step-lap joint (94,96) along which it is adhesively bonded. The liner (58) and adjacent fastener ring portions (52,57) provide a mandrel on which a graphite/Bismaleimide (BMI) resin pre-preg is filament wound and co-cured to form the integral fuselage (60).

Abstract: An optical fiber canister (20) is formed of a bobbin (22) having an optical fiber (24) wound in a plurality of layers. The optical fiber layers include a first layer (42) having a plurality of spaced-apart helical wound segments (44), with each pair of helical wound segments (44) being separated by a stepforward wound segment (46). A second layer (50) overlies the first layer (42), the second layer (50) comprising a plurality of spaced-apart helical wound segments (52), with each pair of helical wound segments (52) being separated by a stepforward wound segment (54). The first and second layers (42 and 50) are wound such that the stepforward wound segments (54) of the second layer (50) overlie the helical wound segments (44) of the first layer (42), and the helical wound segments (52) of the second layer (50) overlie the stepforward wound segments (46) of the first layer (42).