A propulsion system including an extinguishable rocket motor and an incorporated maneuver control system. The rocket motor may be of the solid fuel type. One or more proportional axial thrust valves in communication with a pressure vessel or motor case containing a solid fuel propellant may be used to release combustion products for creating axial thrust. A plurality of proportional maneuver control valves in communication with the pressure vessel and having associated maneuver control thrusters may be selectively actuated in different modes of operation to provide control of pitch, yaw and roll. Fully opening all valves in communication with the pressure vessel may be used to cause rapid depressurization to extinguish the propellant. Reignition of the rocket motor may be effected upon repressurization of the pressure vessel through closing at least some of the valves. Ignition grains may be employed to shorten reignition time, and multiple propellant grains may be provided for multiple pulses.

Steerable, intermittently operable rocket propulsion system

A thruster stack assembly and method for manufacturing the same is provided. The thruster stack assembly includes a plurality of grain elements having a common core region (e.g., a channel or passageway), where each grain element comprises a volume of electrically ignitable propellant. The thruster stack assembly further includes electrodes associated with the plurality of grain elements, the electrodes adapted for selectively igniting the plurality of grain elements. In one example, one or more of the grain elements may be ignited and combusted without igniting or damaging adjacent grain elements of the stack. The core region serves to channel combustion gases and exhaust from the thruster stack. Multiple stacks may be assembled together to form three-dimensional thruster arrays.

Controllable digital solid state cluster thrusters for rocket propulsion and gas generation

Methods and apparatus for performing optimizations for a mobile network device such as a Mobile Node or Mobile Router supporting multiple links to a Home Agent (or Correspondent Node in a Mobile IPv6 environment) are disclosed. During the registration process, link characteristics are transmitted in the registration request. From the link characteristics, it is possible to determine whether the mobile network device has roamed from a high to a low bandwidth link, or vice versa. A first set of optimizations may be performed when the mobile network device has roamed from a high to a low bandwidth link, while a second set of optimizations may be performed when the mobile network device has roamed from a low to a high bandwidth link. Some optimizations may be performed during the establishment of a TCP session, while others may be performed during or upon completion of the Mobile IP registration process.

Mobile network device multi-link optimizations

A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design,

Stereolithographic rocket motor manufacturing method

A hybrid propulsion system comprises a liquid fuel section and a solid fuel section. The liquid fuel section contains an aqueous solution of hydrogen peroxide. An injector system is located between the liquid fuel section and the solid fuel section. The injector system injects a stream of hydrogen peroxide or a decomposed stream of hydrogen peroxide at elevated temperatures into the solid fuel section to effect combustion of the fuel grain in the solid fuel section.

Liquid/solid fuel hybrid propellant system for a rocket

This propulsion system of a rocket motor assembly includes an array of attitude-control rocket engines, one or more oxidizer-fluid sources, one or more ignition-fluid sources, and, optionally, one or more primary rocket engines. Each of the attitude-control rocket engines has a respective combustion chamber and is offset from the longitudinal axis of the rocket motor assembly so that when a selected one or group of the attitude-control rocket engines is fired, the flight path of the assembly is diverted and/or the rocket assembly spins. The oxidizer-fluid and ignition-fluid sources are in operative communication with the attitude-control rocket engines to respectively permit oxidizer fluid and ignition fluid to be supplied to selected ones or groups of the attitude-control rocket engines. Optionally, a portion of the ignition fluid from the ignition-fluid source can be cooled and used to pressurize the oxidizer-fluid source.

Rocket propulsion system including array of attitude-control rocket engines

Hybrid rocket propulsion system including array of hybrid or fluid attitude-control rocket engines

Hybrid-raketenantrieb mit einer anordnung von zusatzraketenmotoren zur positionskontrolle

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Steerable, intermittently operable rocket propulsion system

Rocket propulsion system including array of attitude-control rocket engines

Hybrid rocket propulsion system including array of hybrid or fluid attitude-control rocket engines

Hybrid-raketenantrieb mit einer anordnung von zusatzraketenmotoren zur positionskontrolle