Abstract: Radial loads and vibrations and axial loads on a rotor are balanced by a fluid bearing controlled by a self-regulating system that supplies fluid flow or pressure to the gap between the rotor and stator in response to signals of imbalance generated in the machinery itself. The resulting balancing force is thus created by fluidics, and in certain embodiments the sensing circuit is fluidics-based as well. This system provides enhanced flexibility and response time relative to conventional fluid bearings.

Abstract: Radial loads and vibrations and axial loads on a rotor are balanced by a fluid bearing controlled by a self-regulating system that supplies fluid flow or pressure to the gap between the rotor and stator in response to signals of imbalance generated in the machinery itself. The resulting balancing force is thus created by fluidics, and in certain embodiments the sensing circuit is fluidics-based as well. This system provides enhanced flexibility and response time relative to conventional fluid bearings.

Abstract: 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.