A solid rocket motor, comprising: a combustion chamber; a nozzle coupled to the combustion chamber, said nozzle having a throat with an effective throat area At; one or more segments of solid rocket motor propellant within the combustion chamber; a thermal ignition coupled to at least one of the one or more segments of SRM propellant, each said segment of SRM propellant, once ignited, burns to completion to produce pressurized gas in the combustion chamber at a chamber pressure Pc that flows through the throat of the nozzle to produce thrust; an electrically operated propellant; and an electrical ignition configured to apply an electrical input to the electrically operated propellant, wherein in an ignition condition the electrically operated propellant burns to produce gas to (a) add mass into the chamber upstream of the nozzle throat to increase the chamber pressure Pc, (b) reduce the effective throat area At to increase chamber pressure Pc or (c) to inject mass downstream of the nozzle throat to provide thrust vector control or a combination thereof, characterized in that said electrically operated propellant has a self-sustaining threshold pressure at which the propellant once ignited cannot be extinguished and below which the propellant can be extinguished by interruption of the electrical signal, said electrical ignition configured in an extinguishment condition to interrupt the electrical input to extinguish the electrically operated propellant, said electrical ignition reconfigured in the ignition condition to apply the electrical input to reignite the electrically operated propellant. a combustion chamber; a nozzle coupled to the combustion chamber, said nozzle having a throat with an effective throat area At; one or more segments of solid rocket motor propellant within the combustion chamber; a thermal ignition coupled to at least one of the one or more segments of SRM propellant, each said segment of SRM propellant, once ignited, burns to completion to produce pressurized gas in the combustion chamber at a chamber pressure Pc that flows through the throat of the nozzle to produce thrust; an electrically operated propellant; and an electrical ignition configured to apply an electrical input to the electrically operated propellant, wherein in an ignition condition the electrically operated propellant burns to produce gas to (a) add mass into the chamber upstream of the nozzle throat to increase the chamber pressure Pc, (b) reduce the effective throat area At to increase chamber pressure Pc or (c) to inject mass downstream of the nozzle throat to provide thrust vector control or a combination thereof, characterized in that said electrically operated propellant has a self-sustaining threshold pressure at which the propellant once ignited cannot be extinguished and below which the propellant can be extinguished by interruption of the electrical signal, said electrical ignition configured in an extinguishment condition to interrupt the electrical input to extinguish the electrically operated propellant, said electrical ignition reconfigured in the ignition condition to apply the electrical input to reignite the electrically operated propellant.