초록 ▼

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

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.

대표청구항 ▼

1. A rocket motor assembly having a longitudinal axis and comprising a propulsion system, said propulsion system comprising: an array of eccentric rocket engines offset from the longitudinal axis of said rocket motor assembly to permit attitude control of said rocket motor assembly by independent fi

1. A rocket motor assembly having a longitudinal axis and comprising a propulsion system, said propulsion system comprising: an array of eccentric rocket engines offset from the longitudinal axis of said rocket motor assembly to permit attitude control of said rocket motor assembly by independent firing of a selected one or group of said eccentric rocket engines, said eccentric rocket engines each comprising a respective combustion chamber; one or more oxidizer-fluid sources in operative communication with said eccentric rocket engines to permit oxidizer fluid to be supplied to said selected one or group of said eccentric rocket engines; one or more ignition-fluid sources in operative communication with said eccentric rocket engines to permit ignition fluid to be supplied to said selected one or group of said eccentric rocket engines for initiating a combustion reaction between said oxidizer fluid and a fuel component; a flow pathway connecting one or more of said oxidizer-fluid sources to one or more of said ignition-fluid sources; and at least one cooling device positioned along the pathway for cooling said ignition fluid and permitting said ignition fluid to pressurize said oxidizer fluid in one or more of said oxidizer-fluid sources.