Patent ID: 7069717
Filing Date: 2006-07-04
Classification: F02K

Abstract:
1. An attitude control and propulsion system for a spacecraft, comprising: a supply of oxidizer; at least one attitude control nozzle that expels only the oxidizer; a conduit fluidly coupling the supply of oxidizer and the attitude control nozzle, wherein the conduit provides a pathway for oxidizer to flow in a downstream direction from the supply of oxidizer toward and into the attitude control nozzle; a pressure regulator coupled to the conduit and interposed between the supply of oxidizer and the attitude control nozzle, wherein the pressure regulator regulates the pressure of oxidizer at a location downstream of the pressure regulator and upstream of the attitude control nozzle to a set point pressure at or below a first pressure, wherein the first pressure comprises the pressure required to maintain the oxidizer in a gas state to ensure that the any oxidizer flowing through the conduit is in a gas state prior to entering the attitude control nozzle; a gaseous oxidizer accumulator coupled between the pressure regulator and the attitude control nozzle; wherein the attitude control nozzle is positioned so that thrust produced by the attitude control nozzle adjusts the attitude of the spacecraft and the attitude control nozzle produces its thrust through the expansion of the oxidizer, without combustion of the oxidizer, as the oxidizer in the gas state is expelled from the attitude control nozzle; and a hybrid rocket motor having a main nozzle, the hybrid rocket motor including a combustion chamber in which the oxidizer interacts with a solid fuel to generate thrust via the main nozzle.