Embodiments of the present invention are directed to various devices, systems and methods of providing a restartable, hybrid-rocket system that uses Acrylonitrile Butadiene Styrene (ABS) and compressed air containing oxygen levels up to 40% as a propellant. Alternatively, embodiments of the present invention includes restartable hybrid rocket system that uses a heterogeneous matrix of ABS and a solid oxidizing agent in addition to compressed air as a propellant. When the ABS is exposed to an electrical potential field, the electrical field's effect on the ABS produces localized arcing between multiple layers of the ABS resulting in joule heating and pyrolysis of the ABS. The pyrolysis produces spontaneous combustion of the ABS once the oxidizer flow provides a local oxygen partial pressure greater than two atmospheres at the surface of the ABS.

Embodiments of the present invention are directed to various devices, systems and methods of providing a restartable, hybrid-rocket system that uses Acrylonitrile Butadiene Styrene (ABS) and compressed air containing oxygen levels up to 40% as a propellant. Alternatively, embodiments of the present invention includes restartable hybrid rocket system that uses a heterogeneous matrix of ABS and a solid oxidizing agent in addition to compressed air as a propellant. When the ABS is exposed to an electrical potential field, the electrical field's effect on the ABS produces localized arcing between multiple layers of the ABS resulting in joule heating and pyrolysis of the ABS. The pyrolysis produces spontaneous combustion of the ABS once the oxidizer flow provides a local oxygen partial pressure greater than two atmospheres at the surface of the ABS.

An attitude control system for a guided missile includes a gas generator, an accumulator coupled to the gas generator, and a valve positioned between the gas generator and the accumulator. The gas generator contains propellant that burns to provide hot gas to pressurize the accumulator. The valve is opened to recharge the accumulator with hot gas and closed when it is full. A vent valve can be included to extinguish the propellant in the gas generator. The accumulator can be coupled to thrusters that use the stored hot gas to adjust the attitude of the guided missile.

An attitude control system for a guided missile includes a gas generator, an accumulator coupled to the gas generator, and a valve positioned between the gas generator and the accumulator. The gas generator contains propellant that burns to provide hot gas to pressurize the accumulator. The valve is opened to recharge the accumulator with hot gas and closed when it is full. A vent valve can be included to extinguish the propellant in the gas generator. The accumulator can be coupled to thrusters that use the stored hot gas to adjust the attitude of the guided missile.

Electrically operated propellant is used to supplement the thrust provided by solid rocket motor (SRM) propellant to manage thrust produced by a SRM. The gas produced by burning the electrically operated propellant may be injected upstream of the nozzle to add mass and increase chamber pressure Pc, injected at the throat of the nozzle to reduce the effect throat area At to increase chamber pressure Pc or injected downstream of the throat to provide thrust vector control or a combination thereof. Certain types of electrically operated propellants can be turned on and off provided the chamber pressure Pc does not exceed a self-sustaining threshold pressure eliminating the requirement for physical control valves.

Electrically operated propellant is used to supplement the thrust provided by solid rocket motor (SRM) propellant to manage thrust produced by a SRM. The gas produced by burning the electrically operated propellant may be injected upstream of the nozzle to add mass and increase chamber pressure Pc, injected at the throat of the nozzle to reduce the effect throat area At to increase chamber pressure Pc or injected downstream of the throat to provide thrust vector control or a combination thereof. Certain types of electrically operated propellants can be turned on and off provided the chamber pressure Pc does not exceed a self-sustaining threshold pressure eliminating the requirement for physical control valves.

A satellite has thrusters that are integral parts of its frame. The frame defines cavities therein where thrusters are located. The thrusters may include an electrically-operated propellant and electrodes to activate combustion in the electrically-operated propellant. The frame may be additively manufactured, and the propellant and/or the electrodes may also be additively manufactured, with the frame and the propellant and/or the electrodes also being manufactured in a single process. In addition the thrusters may have nozzle portions through which combustion gases exit the thrusters. The thrusters may be located at corners and/or along edges of the frame, and may be used to accomplish any of a variety of maneuvers for the satellite. The satellite may be a small satellite, such as a CubeSat satellite, for instance having a volume of about 1 liter, and a mass of no more than about 1.33 kg.

The first solid propellant is formed to have a columnar shape so as for a combustion surface to move to a first direction, and to have an end surface exposed to a combustion space. The surface of first solid propellant except for the end surface is covered with a barrier membrane. The position of combustion surface in the first direction is detected by a position sensor device in an always-on measurement or a fixed-point measurement. Based on the detected result, the consumption amount of the first solid propellant is estimated.

Embodiments of the present invention are directed to various devices, systems and methods of providing a restartable, hybrid-rocket system that uses Acylonitrile Butadiene Styrene (ABS) and compressed air containing oxygen levels up to 40% as a propellant. Alternatively, embodiments of the present invention includes restartable hybrid rocket system that uses a heterogeneous matrix of ABS and a solid oxidizing agent in addition to compressed air as a propellant. When the ABS is exposed to an electrical potential field, the electrical field's effect on the ABS produces localized arcing between multiple layers of the ABS resulting in joule heating and pyrolysis of the ABS. The pyrolysis produces spontaneous combustion of the ABS once the oxidizer flow provides a local oxygen partial pressure greater than two atmospheres at the surface of the ABS.

Embodiments of the present invention are directed to various devices, systems and methods of providing a restartable, hybrid-rocket system that uses Acylonitrile Butadiene Styrene (ABS) and compressed air containing oxygen levels up to 40% as a propellant. Alternatively, embodiments of the present invention includes restartable hybrid rocket system that uses a heterogeneous matrix of ABS and a solid oxidizing agent in addition to compressed air as a propellant. When the ABS is exposed to an electrical potential field, the electrical field's effect on the ABS produces localized arcing between multiple layers of the ABS resulting in joule heating and pyrolysis of the ABS. The pyrolysis produces spontaneous combustion of the ABS once the oxidizer flow provides a local oxygen partial pressure greater than two atmospheres at the surface of the ABS.