초록 ▼

In the representative embodiment of the new and improved methods and apparatus disclosed herein to provide effective real-time management of a spacecraft rocket engine powered by gaseous propellants, real-time measurements representative of the engine performance are compared with predetermined stan

In the representative embodiment of the new and improved methods and apparatus disclosed herein to provide effective real-time management of a spacecraft rocket engine powered by gaseous propellants, real-time measurements representative of the engine performance are compared with predetermined standards to selectively control the supply of propellants to the engine for optimizing its performance as well as efficiently managing the consumption of propellants. A priority system is provided for achieving effective real-time management of the propulsion system by first regulating the propellants to keep the engine operating at an efficient level and thereafter regulating the consumption ratio of the propellants. A lower priority level is provided to balance the consumption of the propellants so significant quantities of unexpended propellants will not be left over at the end of the scheduled mission of the engine.

대표청구항 ▼

A rocket propulsion system for supplying gaseous fuels and oxidizers from pressurized sources of the propellants to the combustion chamber of a rocket engine and comprising: first and second conduits for respectively carrying a gaseous fuel and oxidizer from pressurized sources of the propellants to

A rocket propulsion system for supplying gaseous fuels and oxidizers from pressurized sources of the propellants to the combustion chamber of a rocket engine and comprising: first and second conduits for respectively carrying a gaseous fuel and oxidizer from pressurized sources of the propellants to the combustion chamber of a rocket engine; first and second selectively-operable pressure regulators arranged in said first and second conduits for respectively regulating the feed pressures of a gaseous fuel and a gaseous oxidizer being supplied to the combustion chamber of a rocket engine; means for providing real-time measurements of the combustion chamber pressure of a rocket engine supplied by a gaseous fuel and a gaseous oxidizer respectively flowing in said first and second conduits; and control means responsive to real-time measurements of the pressure in the combustion chamber of a rocket engine for selectively controlling said first and second pressure regulators to regulate the feed pressures of a gaseous fuel and a gaseous oxidizer being supplied to the combustion chamber of a rocket engine for maintaining the pressure in the combustion chamber within a predetermined range of pressures wherein, said control means are selectively responsive to the pressure in the combustion chamber of a rocket engine for maintaining the mass flow rates of a gaseous fuel and gaseous oxidizer in a predetermined ratio only when the combustion chamber pressure is in its said predetermined range of pressures.