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 multi-pulse propulsion system includes at least one pulse chamber containing at least one propellant for igniting during at least one pulse of the multi-pulse propulsion system, at least one additional pulse chamber containing at least one additional propellant for igniting during at least one additional pulse of the multi-pulse propulsion system, and at least one passive fuzing system configured to initiate the at least one additional pulse. The at least one passive fuzing system includes a sensor and an igniter. The sensor is configured to sense an environmental condition and/or a ballistic condition. The igniter is configured to provide a stimulus that causes ignition of the at least one additional propellant in response to the sensor sensing that the environmental condition and/or the ballistic condition has reached or exceeded one or more threshold values.

A control system for a satellite comprises a power source and control system, a propulsion system having individually selectable solid fuel motors, a communication interface and an attitude determination and control system (ADCS). The ADCS receives power from the power source and control system and further receives desired orbital or positional instructions via the communication interface. Based on the desired orbital or position instructions, the ADCS generates and provides commands to the propulsion system. In turn, the propulsion system selects and fires one or more motors of the individually selectable solid fuel motors responsive to the commands received from the ADCS. A satellite may comprise the disclosed satellite control system as well as attitude control components and/or sensor components operatively connected to the satellite control system.

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 projectile for firing from a launcher includes a propulsion stage having non-axisymmetric boosters arranged about a longitudinal axis of the propulsion stage. The propulsion stage may further include a central booster about which the non-axisymmetric boosters are arranged.