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).