Microwave energy is used to ignite and control the ignition of electrically operated propellant to produce high-pressure gas. The propellant includes conductive particles that act as a free source of electrons. Incoming microwave energy accumulates electric charge in an attenuation zone, which is discharged in the form of dielectric breakdowns to create local randomly oriented currents. The propellant also includes polar molecules. The polar molecules in the attenuation zone absorb microwave energy causing the molecules to rapidly vibrate thereby increasing the temperature of the propellant. The increase in temperature and the local current densities together establish an ignition condition to ignite and sustain ignition of an ignition surface of the attenuation zone as the zone regresses without igniting the remaining bulk of the propellant.

Microwave energy is used to ignite and control the ignition of electrically operated propellant to produce high-pressure gas. The propellant includes conductive particles that act as a free source of electrons. Incoming microwave energy accumulates electric charge in an attenuation zone, which is discharged in the form of dielectric breakdowns to create local randomly oriented currents. The propellant also includes polar molecules. The polar molecules in the attenuation zone absorb microwave energy causing the molecules to rapidly vibrate thereby increasing the temperature of the propellant. The increase in temperature and the local current densities together establish an ignition condition to ignite and sustain ignition of an ignition surface of the attenuation zone as the zone regresses without igniting the remaining bulk of the propellant.

A solid rocket motor comprises a pressure vessel, a solid propellant structure within the pressure vessel, and a flight termination system overlying the pressure vessel. The flight termination system comprises a shaped charge configured and positioned to effectuate ignition of an inner portion of the solid propellant structure and a reduction in an ability of the pressure vessel to withstand a change in internal pressure. Another solid rocket motor, a multi-stage rocket motor assembly, and a method of destroying a launch vehicle in flight are also described.

A solid rocket motor comprises a pressure vessel, a solid propellant structure within the pressure vessel, and a flight termination system overlying the pressure vessel. The flight termination system comprises a shaped charge configured and positioned to effectuate ignition of an inner portion of the solid propellant structure and a reduction in an ability of the pressure vessel to withstand a change in internal pressure. Another solid rocket motor, a multi-stage rocket motor assembly, and a method of destroying a launch vehicle in flight are also described.

A solid propellant auxiliary booster intended to be attached to the main body of a launcher comprises a cylindrical body extending in a longitudinal direction between a rear face in communication with a nozzle and a front face formed by a conical structure connected to the cylindrical body of the booster. The cylindrical body delimits a first internal volume and the conical structure of the front face delimits a second internal volume. The auxiliary booster contains a solid propellant charge. The first internal volume of the cylindrical body communicates with the second internal volume of the conical structure. The solid propellant charge is present both in the first and second internal volumes.

A solid propellant auxiliary booster intended to be attached to the main body of a launcher comprises a cylindrical body extending in a longitudinal direction between a rear face in communication with a nozzle and a front face formed by a conical structure connected to the cylindrical body of the booster. The cylindrical body delimits a first internal volume and the conical structure of the front face delimits a second internal volume. The auxiliary booster contains a solid propellant charge. The first internal volume of the cylindrical body communicates with the second internal volume of the conical structure. The solid propellant charge is present both in the first and second internal volumes.

A number of devices and methods for biopassivating explosive ordnance are disclosed. In some embodiments, a biopassivation reactor device is used to render energetic material in an explosive ordnance less explosive and/or non-explosive. This can be done by coupling the biopassivation reactor device to the fuse opening of the explosive ordnance. This can also be done by incorporating the biopassivation reactor device into the explosive ordnance at the time of manufacture. The biopassivation reactor device can include a housing enclosing microorganisms, water, additives, and/or the like. In some embodiments, an entire ordnance magazine can be operated as a bioreactor to passivate the explosive ordnance inside.

The present invention relates to improved rocket engine systems. In one embodiment, an improved rocket engine system includes a propellant source, at least one power source, at least one power source motor, a rocket engine, and at least one pump. The improved rocket engine system may further include at least one of the following: at least one controller, at least one propellant valve, and a propellant pressurizing source.

The present invention relates to improved rocket engine systems. In one embodiment, an improved rocket engine system includes a propellant source, at least one power source, at least one power source motor, a rocket engine, and at least one pump. The improved rocket engine system may further include at least one of the following: at least one controller, at least one propellant valve, and a propellant pressurizing source.

A solid rocket motor includes a first solid propellant and a second solid propellant at least partially surrounding the first solid propellant. The second solid propellant is resistant to fragment impact and the first solid propellant has a higher impulse than the second solid propellant.