Solid rocket motors are provided herein. In certain embodiments, a solid rocket motor includes a housing containing thin layers of fuel and thin layers of an inert oxidizer, separated by a thin nonconductive layer. The housing has a nozzle at the end for gas release and channeling. Prior to use, the inert oxidizer is activated by electrochemical oxidation which can generate an active oxidizer and additional fuel. Ignition of the oxidizer and fuel can be triggered whereby the contents of the housing can ignite, generating hot gasses to be channeled out through the nozzle to generate thrust. Replacing current state solid rocket motors with embodiments described herein can improve cost, safety and increase capability. The disclosed embodiments can be safe to transport, store, and handle. Additionally, there can be no moving parts unlike hybrid or liquid rocket motors.

Solid rocket motors are provided herein. In certain embodiments, a solid rocket motor includes a housing containing thin layers of fuel and thin layers of an inert oxidizer, separated by a thin nonconductive layer. The housing has a nozzle at the end for gas release and channeling. Prior to use, the inert oxidizer is activated by electrochemical oxidation which can generate an active oxidizer and additional fuel. Ignition of the oxidizer and fuel can be triggered whereby the contents of the housing can ignite, generating hot gasses to be channeled out through the nozzle to generate thrust. Replacing current state solid rocket motors with embodiments described herein can improve cost, safety and increase capability. The disclosed embodiments can be safe to transport, store, and handle. Additionally, there can be no moving parts unlike hybrid or liquid rocket motors.

A propulsion system for use with a satellite comprises a substrate, a communication network and a cluster of individually selectable solid fuel motors mounted on the substrate and operatively connected to the communication network. A controller is also operatively connected to the communication network and operative to select any one of more motors of the cluster of individually selectable solid fuel motors and transmit signals to fire the one or more motors of the individually selectable solid fuel motors. The substrate may have various configurations. The cluster of motors may comprise 10-1000 motors, which may be arranged in a rectangular array or other formation. Subsets of motors having different impulse capabilities may be employed. In this manner, lighter, smaller, flexible and more efficient propulsions systems may be provided for use in attitude control, etc. of satellites.

A propulsion system for use with a satellite comprises a substrate, a communication network and a cluster of individually selectable solid fuel motors mounted on the substrate and operatively connected to the communication network. A controller is also operatively connected to the communication network and operative to select any one of more motors of the cluster of individually selectable solid fuel motors and transmit signals to fire the one or more motors of the individually selectable solid fuel motors. The substrate may have various configurations. The cluster of motors may comprise 10-1000 motors, which may be arranged in a rectangular array or other formation. Subsets of motors having different impulse capabilities may be employed. In this manner, lighter, smaller, flexible and more efficient propulsions systems may be provided for use in attitude control, etc. of satellites.

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.

A high density, generally recognized as safe, hybrid rocket motor is described, having a density-specific impulse similar to a solid rocket motor, with good performance approaching or equal to a liquid rocket motor. These high density hybrid motors resolve the packaging efficiency/effectiveness problems limiting the application of safe, low cost hybrid motor technology.

A high density, generally recognized as safe, hybrid rocket motor is described, having a density-specific impulse similar to a solid rocket motor, with good performance approaching or equal to a liquid rocket motor. These high density hybrid motors resolve the packaging efficiency/effectiveness problems limiting the application of safe, low cost hybrid motor technology.

A process for removing webs formed on a wall of a central channel of a propellant charge, the process including removing webs by levelling the wall of the central channel of the propellant charge with a levelling tool installed on an articulated robotic arm during which the movements of the robot arm are controlled by a user interface which includes a controller configured to be used by a user; a force sensor measures the force applied by the levelling tool; a control unit connected to the force sensor regulates the movements of the robot arm by maintaining the force applied by the levelling tool below a first predetermined force threshold, the control unit also regulating the movements of the robot arm by maintaining a movement speed of the levelling tool which is below a predetermined speed threshold value.

A process for removing webs formed on a wall of a central channel of a propellant charge, the process including removing webs by levelling the wall of the central channel of the propellant charge with a levelling tool installed on an articulated robotic arm during which the movements of the robot arm are controlled by a user interface which includes a controller configured to be used by a user; a force sensor measures the force applied by the levelling tool; a control unit connected to the force sensor regulates the movements of the robot arm by maintaining the force applied by the levelling tool below a first predetermined force threshold, the control unit also regulating the movements of the robot arm by maintaining a movement speed of the levelling tool which is below a predetermined speed threshold value.

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.