초록 ▼

A spacecraft propulsion system which integrates the function of the apogee kick motor (AKM) and reaction control system (RCS) is disclosed. In accordance with this invention, a pump-fed AKM is employed which results in lightweight main tanks and pressurization systems. The RCS thrusters are operated

A spacecraft propulsion system which integrates the function of the apogee kick motor (AKM) and reaction control system (RCS) is disclosed. In accordance with this invention, a pump-fed AKM is employed which results in lightweight main tanks and pressurization systems. The RCS thrusters are operated by small bellows tanks which are intermittently pressurized by a gas pressurization system to provide high pressure for operation of the RCS thrusters. The system according to this invention enables use of lighter weight main propellant tanks since they do not have to withstand high internal pressures and also enables realization of the numerous advantages of a pump-fed AKM. Several embodiments describe various methods for cycling the bellows tanks.

대표청구항 ▼

A satellite propulsion system adapted to supply liquid propellant to a first thruster at a first flow rate and to a second thruster at a second higher flow rate, comprising: a gas pressure source, a propellant tank for holding said propellant, a bellows tank, a collapsible bellows in said bellows ta

A satellite propulsion system adapted to supply liquid propellant to a first thruster at a first flow rate and to a second thruster at a second higher flow rate, comprising: a gas pressure source, a propellant tank for holding said propellant, a bellows tank, a collapsible bellows in said bellows tank which divides said bellow tank into a gas side and a propellant side, the relative volume of said gas side and said propellant side varying as said bellows collapses and expands, a first conduit communicating said propellant tank with said propellant side of said bellows tank, a first valve means in said first conduit for controlling propellant flow in said first conduit, a second conduit communicating said gas pressure source with said gas side of said bellows tank, a second valve means in said second conduit, a third conduit communicating said first thruster with said propellant side of said bellows tank, a third valve means in said third conduit for controlling the flow of propellant to said first thruster, a fourth conduit communicating said propellant tank with said second thruster, a fourth valve means in said fourth conduit for controlling the flow of propellant to said second thruster, a propellant pump in said fourth conduit for pressurizing the propellant flowing to said second thruster, a fifth conduit communicating to said gas side of said bellows tank and for venting said gas side of said bellows, and a fifth valve means in said fifth conduit wherein, when said propellant side of said bellows is filled with propellant, said gas side of said bellows may be pressurized, thereby pressurizing said propellant which is transmitted to said first thruster when said third valve means is opened, and wherein said propellant side of said bellows may be refilled with propellant by opening said fifth valve means and closing said second valve means, thereby venting said gas side of said bellows tank and enabling said propellant to refill said propellant side of said bellows tank.