Abstract: The rate of combustion of an electrically operated propellant having a self-sustaining threshold of at least 1,000 psi is controlled to produce chamber pressures that are sufficient to produce a desired pressure profile in the airbag to accommodate a range of human factors and crash conditions yet never exceeding the self-sustaining threshold. The combustion of the propellant is extinguished to control the total pressure impulse delivered to the airbag. Propellants formed with an ionic perchlorate-based oxidizer have demonstrated thresholds in excess of 1,500 psi and higher.

Abstract: The rate of combustion of an electrically operated propellant having a self-sustaining threshold of at least 1,000 psi is controlled to produce chamber pressures that are sufficient to produce a desired pressure profile in the airbag to accommodate a range of human factors and crash conditions yet never exceeding the self-sustaining threshold. The combustion of the propellant is extinguished to control the total pressure impulse delivered to the airbag. Propellants formed with an ionic perchlorate-based oxidizer have demonstrated thresholds in excess of 1,500 psi and higher.

Abstract: An electrically operated propellant is configured to ignite and extinguish over a range of pressures. In examples, the electrically operated propellant is included in a gas generation system having a combustion chamber and at least two electrodes coupled with the propellant. The electrically operated propellant is configured to ignite at an ignition condition and extinguish under an extinguishing condition. In the ignition condition an electrical input is applied across the electrodes to ignite the electrically operated propellant. In the extinguishing condition the electrical input is interrupted while the pressure within the combustion chamber is greater than 200 psi, and the ignited electrically operated propellant extinguishes.

Abstract: An electrically operated propellant is configured to ignite and extinguish over a range of pressures. In examples, the electrically operated propellant is included in a gas generation system having a combustion chamber and at least two electrodes coupled with the propellant. The electrically operated propellant is configured to ignite at an ignition condition and extinguish under an extinguishing condition. In the ignition condition an electrical input is applied across the electrodes to ignite the electrically operated propellant. In the extinguishing condition the electrical input is interrupted while the pressure within the combustion chamber is greater than 200 psi, and the ignited electrically operated propellant extinguishes.

Abstract: A gas generator assembly includes a propellant chamber housing an amine based propellant. A reaction chamber is coupled with the propellant chamber. The reaction chamber includes a reaction chamber housing, and a porous reaction matrix within the reaction chamber housing. The reaction matrix includes a catalyzing agent, and the catalyzing agent is configured to non-combustibly catalyze the amine based propellant into one or more pressurized gases. An injector is in communication with the propellant chamber. The injector is configured to deliver the amine based propellant to the porous reaction matrix. A discharge nozzle is coupled with the reaction chamber and is configured to accelerate and discharge the one or more pressurized gases. In one example, the gas generator is coupled with one or more of an impulse turbine assembly and an electric generator to form a micro power unit.

Abstract: A gas generator assembly includes a propellant chamber housing an amine based propellant. A reaction chamber is coupled with the propellant chamber. The reaction chamber includes a reaction chamber housing, and a porous reaction matrix within the reaction chamber housing. The reaction matrix includes a catalyzing agent, and the catalyzing agent is configured to non-combustibly catalyze the amine based propellant into one or more pressurized gases. An injector is in communication with the propellant chamber. The injector is configured to deliver the amine based propellant to the porous reaction matrix. A discharge nozzle is coupled with the reaction chamber and is configured to accelerate and discharge the one or more pressurized gases. In one example, the gas generator is coupled with one or more of an impulse turbine assembly and an electric generator to form a micro power unit.

Abstract: A solid fuel rocket motor, a castellated propellant cartridge and a method of controlling a pressure differential in a cartridge-loaded rocket motor are disclosed. The rocket motor may include a housing having an inside surface, a plurality of propellant cartridges disposed within the housing, an igniter disposed to ignite propellant material within the propellant cartridges, and a nozzle disposed to exhaust combustion gases out of the housing. At least some of the propellant cartridges may be castellated propellant cartridges.

Abstract: There is disclosed a solid fuel rocket motor including a center-perforated solid fuel grain. The solid fuel grain may be adapted to burn outwardly from a center surface facing the center perforation when ignited by a primary igniter during a normal mode of operation. The solid fuel grain may be further adapted to burn longitudinally from an end face when ignited by a secondary igniter during a safety mode of operation.

Abstract: A motor includes an annular solid fuel between an inside diameter and an outside diameter. The solid fuel has a series of radial notches that define segments of fuel between them. The notches allow for faster burning of the fuel, while still allowing structural integrity of the fuel segments to be retained during the burning process.

Abstract: A method of defeating an incoming missile, such as a rocket propelled grenade, includes soft launching an interceptor missile, and then using pitch over motors of the interceptor missile to alter course of the missile to a desired interception direction. By launching at a relatively slow speed, such as a speed less than or equal to 40 m/sec (130 ft/sec), the interceptor missile may reach the desired interception direction within 250 milliseconds of launch. The interceptor missile may be able to cover substantially all interception directions over a hemisphere or greater extent around a launch location. For example, the interceptor missile may be launched vertically from a ground vehicle, and be capable of altering course to any above-ground trajectory within 250 milliseconds.

Abstract: A method of defeating an incoming missile, such as a rocket propelled grenade, includes soft launching an interceptor missile, and then using pitch over motors of the interceptor missile to alter course of the missile to a desired interception direction. By launching at a relatively slow speed, such as a speed less than or equal to 40 m/sec (130 ft/sec), the interceptor missile may reach the desired interception direction within 250 milliseconds of launch. The interceptor missile may be able to cover substantially all interception directions over a hemisphere or greater extent around a launch location. For example, the interceptor missile may be launched vertically from a ground vehicle, and be capable of altering course to any above-ground trajectory within 250 milliseconds.

Abstract: A reliable and inexpensive attitude control system uses a plurality of pitch-over thrusters to perform rapid and precise attitude maneuvers for a flight vehicle. The pitch-over thrusters create rotational moments that directly pitch and yaw the flight vehicle. The use of very simple thrusters and control techniques provides for a reliable and cost effective solution. The ability to perform overlapping pitch and yaw maneuvers with single-shot fixed-impulse thrusters provides for high-speed maneuverability. Although this approach is applicable to provide attitude control for any flight vehicle including all types of missiles, kill-vehicles and space craft, it is particularly applicable for smaller highly maneuverable cost-constrained missile systems. One such system is an “Active Protection System” or APS in which a missile system is integrated with a vehicle such as a HumVee or armored personnel carrier to provide defensive counter-measures against possible attack.

Abstract: A new rocket motor assembly configuration is disclosed. Amine based oxidizer is decomposed in the presence of a metallic catalyst to generate an oxygen rich hot gas stream. The hot gas stream is used to trigger a Magnesium based solid fuel in the combustion chamber. The thrust of the rocket motor may be regulated at multiple points. This design thus offers an IM compliant, thrust-adjustable rocket motor that is of a low hazard classification without compromising its performance.

Abstract: Embodiments of a buoyancy dissipater and method for deterring an errant vessel are generally described herein. In some embodiments, a volume of gas is generated from a propellant and diffused below a waterline of a vessel. The resulting gas bubble dissipates the buoyancy of the vessel providing a non-lethal deterring effect. The buoyancy dissipater includes a diffuser having radially-positioned diffusion ports to radially diffuse the gas generated by a gas generator below the waterline. In some embodiments, the radially-positioned diffusion ports comprise holes positioned radially around the diffuser to diffuse the gas around the buoyancy dissipater.

Abstract: There is disclosed a solid fuel rocket motor including a center-perforated solid fuel grain. The solid fuel grain may be adapted to burn outwardly from a center surface facing the center perforation when ignited by a primary igniter during a normal mode of operation. The solid fuel grain may be further adapted to burn longitudinally from an end face when ignited by a secondary igniter during a safety mode of operation.

Abstract: A reliable and inexpensive attitude control system uses a plurality of pitch-over thrusters to perform rapid and precise attitude maneuvers for a flight vehicle. The pitch-over thrusters create rotational moments that directly pitch and yaw the flight vehicle. The use of very simple thrusters and control techniques provides for a reliable and cost effective solution. The ability to perform overlapping pitch and yaw maneuvers with single-shot fixed-impulse thrusters provides for high-speed maneuverability.

Abstract: A reliable and inexpensive attitude control system uses a plurality of pitch-over thrusters to perform rapid and precise attitude maneuvers for a flight vehicle. The pitch-over thrusters create rotational moments that directly pitch and yaw the flight vehicle. The use of very simple thrusters and control techniques provides for a reliable and cost effective solution. The ability to perform overlapping pitch and yaw maneuvers with single-shot fixed-impulse thrusters provides for high-speed maneuverability.

Abstract: A solid fuel rocket motor, a castellated propellant cartridge and a method of controlling a pressure differential in a cartridge-loaded rocket motor are disclosed. The rocket motor may include a housing having an inside surface, a plurality of propellant cartridges disposed within the housing, an igniter disposed to ignite propellant material within the propellant cartridges, and a nozzle disposed to exhaust combustion gases out of the housing. At least some of the propellant cartridges may be castellated propellant cartridges.

Abstract: Embodiments of a buoyancy dissipater and method for deterring an errant vessel are generally described herein. In some embodiments, a volume of gas is generated from a propellant and diffused below a waterline of a vessel. The resulting gas bubble dissipates the buoyancy of the vessel providing a non-lethal deterring effect. The buoyancy dissipater includes a diffuser having radially-positioned diffusion ports to radially diffuse the gas generated by a gas generator below the waterline. In some embodiments, the radially-positioned diffusion ports comprise holes positioned radially around the diffuser to diffuse the gas around the buoyancy dissipater.

Abstract: Embodiments of a buoyancy dissipater and method for deterring a vessel are generally described herein. In some embodiments, a volume of gas is generated from a propellant and diffused below a waterline of a vessel. The resulting gas bubble dissipates the buoyancy of the vessel providing a non-lethal deterring effect.