Raytheon Company

Hughes Missile Systems Company

Oscar Kenneth Ohanian

Andrew B Facciano

Wayne Lee Sunne

Thomas A Olden

Robert P Johnson

Edward B Liguori

Rodney H Krebs

James L Neumann

James Samonte

Damian C Athey

Michael Kevershan

James Dolan

Ronald N Hopkins

Embodiments of a non-lethal delivery canister, a bomber/perpetrator threat-mitigation system, and methods of mitigating bomber and perpetrator threats are generally described herein. In some embodiments, the non-lethal delivery canister may include a shell, a plastic-fabric liner within the shell to hold the shell together, and an entrapment device within the liner. The shell may be configured to break away and disintegrate after launch and prior to target impact to help ensure non-lethality. In some embodiments, the delivery canister may include an exhaust-gas generator (EGG) to generate a high-pressure gas, and an exhaust-gas director within the liner to direct the high-pressure gas generated by the EGG into the liner cause the entrapment device to expel.

Non-lethal delivery canister, threat mitigation system, and methods for mitigating bomber and perpetrator threats

A missile has a body with a substantially circular nose opening therein, and a ceramic radome sized to cover the nose opening. A compliant metallic circular transition element is disposed structurally between the radome and the body. The transition element includes an elongated compliant arm region and a crossbar region positioned adjacent to the radome such that a lower margin surface of the radome rests against an upper side of the crossbar region. A brazed butt joint is formed between the lower margin surface of the radome and the upper side of the crossbar region of the transition element. A second brazed lap joint is formed between the vehicle body and the elongated compliant arm of the transition element.

Vehicle having a ceramic radome affixed thereto by a compliant metallic

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). A plurality of Graphite/BMI doublers (62,63,64,65) are axisymmetrically positioned on the fuselage external surface to form four antenna cavities (66,67,68,69) which receive antennas (71) therein. Subsequently, antenna spacers (72,73,74,75) encase the antennas (71) about which a radome overwrap (70) is filament wound with a Quartz/BMI pre-preg. The entire structure (70) is then integrally cured to the internal fuselage (60) and antenna spacers (72,73,74,75) afterwhich it is surface treated (76) and overcoated (78).

Integral missile antenna-fuselage assembly

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Tucson, AZ, United States of America

Oscar Kenneth Ohanian