Abstract: Embodiments include active protection systems and methods for an aerial platform. An onboard system includes radar modules, detects aerial vehicles within a threat range of the aerial platform, and determines if any of the aerial vehicles are an aerial threat. The onboard system also determines an intercept vector to the aerial threat, communicates the intercept vector to an eject vehicle, and causes the eject vehicle to be ejected from the aerial platform to intercept the aerial threat. The eject vehicle includes alignment thrusters to rotate a longitudinal axis of the eject vehicle to substantially align with the intercept vector, a rocket motor to accelerate the eject vehicle along an intercept vector, divert thrusters to divert the eject vehicle in a direction substantially perpendicular to the intercept vector, and attitude control thrusters to make adjustments to the attitude of the eject vehicle.

Abstract: An induction heating compaction system is provided. The system includes an induction heating member and a compaction member. The induction heating member is configured to generate an electromagnetic field at a select frequency. The select frequency causes at least one of the fibers and matrix in pre-preg material to heat up. The compaction member has at least a portion that is made from a material that is transparent to the select frequency of the electromagnetic field generated by the induction heating member. The compaction member includes a cooling assembly that is configured and arranged to extract heat from the pre-preg material, while compacting the pre-preg material.

Abstract: Embodiments include engagement management systems and methods for managing engagement with aerial threats. Such systems include radar modules and detect aerial threats within a threat range of a base location. The systems also track intercept vehicles and control flight paths and detonation capabilities of the intercept vehicles. The systems are capable of communication between multiple engagement management systems and coordinated control of multiple intercept vehicles.

Abstract: A dome connector for a flywheel rim to shaft attachment is provided. The dome connector includes a helically wound composite band that extends from a first port to a second port. The helically wound composite band has a helical angle in relation to a line perpendicular to a center of axis of the dome connector. The helical angle is selected to at least in part achieve a desired stiffness in the dome connector.

Abstract: Propellant structures and stimulation tools incorporating propellant structures may comprise composite propellant structures including two or more regions of propellant having different compositions, different grain structures, or both. An axially extending initiation bore containing an initiation element may extend through a center of the propellant structure, or may be laterally offset from the center. An offset initiation bore may be employed with a composite grain structure. Methods of tailoring ballistic characteristics of propellant burn to result in desired operational pressure pulse characteristics are also disclosed.

Abstract: A flight safety assembly onboard an aerial vehicle includes a first sensor configured to sense first information related to flight of the aerial vehicle and a second sensor configured to sense second information related to the flight of the aerial vehicle. A sensor input is adapted to receive third information related to the flight of the aerial vehicle. A processor is operably coupled to the first sensor, the second sensor, and the sensor input. The processor is configured to determine three independent instantaneous impact points for the aerial vehicle by independently analyzing each of the first information, the second information and the third information. The processor is also configured to generate three independent onboard flight termination indicators for each of the three independent instantaneous impact points that intersects with a region to be protected.

Abstract: A precursor formulation of a liner comprising a polymer and at least two curatives. One of the at least two curatives comprises a more reactive curative and the other of the at least two curatives comprises a less reactive curative. The more reactive curative is formulated to crosslink the polymer. A method of lining a rocket motor is also disclosed, as is a rocket motor including the liner.

Abstract: A multi-spectral detection device is provided that includes a housing, a bezel spacer, a microphone, an end cap and electro-optical sensors mounted to the end cap. The housing has an inner chamber that holds sensor components. The bezel spacer has a first end and an opposed, second end. The first end of the bezel spacer extends from a first end of the housing. The bezel spacer has a central bezel passage leading to the inner chamber of the housing. The bezel spacer further has at least four side walls. Each side wall is positioned 90 degrees away from an adjacent side wall. A microphone is coupled to each side wall of the bezel spacer in such a manner that each microphone is faced 90 degrees with respect to an adjacent microphone to form a compact acoustic array. The end cap is coupled to the second end of the bezel spacer and the electro-optical sensors are mounted to the end cap.

Abstract: A strain measurement device includes a reference material, and a displacement sensor configured to detect relative changes in distance between the sensor and the reference material. At least one of the displacement sensor and the reference material is coupled with a pre-cured elastomeric material. The displacement sensor generates a data signal to a processor that is configured to determine a strain of another elastomeric material based at least in part on the data signal received from the sensor. A displacement sensor and a reference material may be positioned within an elastomeric material within a casing of a solid rocket motor for determining strain experienced by the elastomeric material, such as the propellant of the solid rocket motor. A method includes installing a sensor of an elastomeric material. Another method includes determining strain of an elastomeric material of a solid rocket motor.

Abstract: Methods of preparing propellant compositions for power loads and firearms that include providing pre-shaped particle sized starting material, shaped consistent with a desired final propellant product shape, and thereafter nitrating and stabilizing the pre-shaped starting material using boiling stabilization processes. The resulting nitrated propellants of the methods reliably exhibit complete stabilization, high nitrogen substitution, high shelf life and acceptable ballistic performance.

Abstract: A fragmentation body comprising a substantially monolithic structure comprising a metal material and comprising a major surface having an indentation pattern therein, and an opposing major surface having an opposing indentation pattern therein, the opposing indentation pattern being substantially aligned with the indentation pattern. A warhead and an article of ordnance are also described.

Abstract: A combustor including a housing, an injector body, insulation, an air/fuel premix injector, a hot surface igniter, a fuel injector and a burner. The housing forms a main combustion chamber. The injector body is coupled within the housing and the injector body includes an initial combustion chamber. The insulation lines the initial combustion chamber. The air/fuel premix injector is configured and arranged to dispense a flow of air/fuel mixture into the initial combustion chamber. The hot surface igniter is configured and arranged to heat up and ignite the air/fuel mixture in the initial combustion chamber. The fuel injector dispenses a flow of fuel and the burner dispenses a flow of air. The flow of fuel from the fuel injector and the flow of air from the burner are ignited in the main combustion chamber by the ignition of the air/fuel mixture in the initial combustion chamber.

Abstract: An optical sensor comprising a light source; a sensor substrate, arranged to receive a force to be detected, the sensor substrate including an interference pattern generator, optically coupled to the light source for receiving light from the light source, and generating an interference pattern, and a detector, optically coupled to the sensor substrate for receiving the interference pattern and providing a signal which can be used to determine the force applied to the sensor substrate.

Abstract: A direct contact heat exchanger assembly is provided. The direct contact heat exchanger assembly includes an evaporator jacket and an inner member. The inner member is received within the evaporator jacket. A sleeve passage is formed between the evaporator jacket and the inner member. The sleeve passage is configured and arranged to pass a flow of liquid. The inner member has an inner exhaust chamber that is configured to pass hot gas. The inner member further has a plurality of exhaust passages that allow some of the hot gas passing through the inner exhaust chamber to enter the flow of liquid in the sleeve passage.

Abstract: A fracturing apparatus in a wellbore, having a housing with at least one injection port; an injection fluid supply interface to provide injection fluid for the fracturing apparatus; and at least one high pressure combustor received within the housing. The housing further includes a combustible medium interface that is in fluid communication with the at least one high pressure combustor, which is configured and arranged to provide repeated ignition cycles that include a combustion cycle that ignites the combustible medium and a fuel delivery cycle that delivers the combustible medium to the combustor, wherein pressure resulting from the combustion cycle forces the injection fluid out an injection port to cause fracturing in a portion of the earth around the wellbore.

Abstract: An inspection fixture is provided that includes a fixture, a lens, an ultrasonic phase array, a mirror and a liquid supply connector. The fixture body includes an inner chamber and an opening to the inner chamber. The lens defines a portion of the inner chamber. The ultrasonic phase array generates ultrasonic signals and is positioned to send the ultrasonic signals through the lens. The mirror is received within the inner chamber and is positioned at 45° in relation to the lens to reflect the ultrasonic signals from the lens out an opening to an inspection area of a body to be inspected and to reflect returned ultrasonic signals from the inspection area to the lens. The liquid supply connector is in fluid communication with the inner chamber.

Abstract: An illumination composition comprising at least one oxidizer, at least one of a fuel and a binder, and at least one combustion rate modifier. The at least one oxidizer is selected from the group consisting of a potassium-containing oxidizer and a rubidium-containing oxidizer, the at least one oxidizer present in the illumination composition at from about 50 wt % to about 70 wt % and comprising particles each independently having a size within a range of from about 25 ?m to about 325 ?m. Additional illumination compositions, illumination flares, and methods of illuminating a target are also disclosed.

Abstract: Mechanisms for deploying a solar array include an elongated deployment member routed along a first panel, along an extension, and at least partially along a second panel. The elongated deployment member is configured to, upon retraction of the elongated deployment member by a deployment motor, move the extension into an extended position and rotate the second panel about a hub located at a distal end of the extension. Solar array assemblies include such a mechanism. Methods of deploying a solar array include retracting an elongated deployment member to rotate an extension into an extended position and further retracting the elongated deployment member to rotate a panel coupled to the extension approximately 360° about a hub of the extension.

Abstract: An apparatus and method for initiating the ignition of a pyrotechnic material in a controlled manner. The invention is suitable for use with less sensitive pyrotechnic material or charges, such as, but not limited to, boron potassium nitrate (B/KNO3) and nitrocellulose (NC). The invention is particularly suitable for incorporation with an ignition system for the ignition of pyrotechnic materials used in solid propellant missile and rocket motors. The invention is particularly resistant to spurious radio frequency interference and/or other electromagnetic interference and is readily capable of operating on a minimum fire or triggering voltage in excess of 500 volts.

Abstract: Charged projectile assemblies include a housing and an electronic assembly configured to produce an electric field about at least a portion of the housing of the projectile. Cartridge assemblies for use with firearms include charged projectiles. Methods of charging a projectile include forming an electric field about at least a portion of a projectile and extending the electric field at least partially between a forward portion of the projectile and an aft portion of the projectile.