SMALL SATELLITE PROPULSION SYSTEM

摘要

A small satellite propulsion system using a gaseous oxidizer and a gaseous fuel as primary propellants with a liquid as a film coolant for the inner surface of the rocket motor. The gaseous fuel is also used as a pressurant for the coolant and as a cold gas propellant for attitude control system (hereinafter “ACS”) thrusters. The oxidizer, fuel, and coolant tanks, as well as most valves and plumbing, are integrated into a single core unit along with the rocket motor, rocket motor plumbing, and safety valves. Attitude control thrusters may be remotely located with plumbing to the fuel tank. The core unit is four inches high and less than four inches deep and wide. The small satellite propulsion system uses no pyrotechnics and no hazardous toxic materials.

主权项

1. A small satellite propulsion system comprising:
a. a gaseous fuel tank; b. a gaseous oxidizer tank; c. a liquid coolant tank; and d. a rocket motor in valve-controlled fluid communication with said gaseous fuel tank, said gaseous oxidizer tank, and said liquid coolant tank, wherein said rocket motor is fixed within an elongated enclosure comprising at least one side formed, at least in part, by at least one of said gaseous fuel tank, said gaseous oxidizer tank, and said liquid coolant tank.