Spacecraft propellant management system
A spacecraft includes a propulsion system including an inert gas stored in a set of pressurant tanks, one or more electric thrusters operable with the inert gas, one or more cold gas thrusters operable with the inert gas; and a pneumatic arrangement including commandable valves.
1. A spacecraft comprising:
a propulsion system for use during a mission life of the spacecraft, the propulsion system including:
an inert gas stored in pressurant tanks;
one or more electric thrusters operable with the inert gas;
one or more cold gas thrusters operable with the inert gas;
a pressure regulator disposed between and pneumatically coupled with the pressurant tanks and the one or more electric thrusters; and
a pneumatic arrangement including commandable valves, the pneumatic arrangement configured such that a first subset of the pressurant tanks is isolatable, by the commandable valves, from a second subset of the pressurant tanks; wherein
in a first mission phase, the commandable valves are configured such that the one or more electric thrusters are pneumatically coupled, by way of the pressure regulator, with the second subset of the pressurant tanks and pneumatically isolated from the first subset of the pressurant tanks and such that the one or more cold gas thrusters are pneumatically coupled so as receive pressurant gas from the first subset of the pressurant tanks, not by way of the pressure regulator, and are pneumatically isolated from the second subset of the pressurant tanks; and
in a second mission phase, subsequent to the first mission phase, the commandable valves are configured such that the one or more electric thrusters and the one or more cold gas thrusters are pneumatically coupled, by way of the pressure regulator, with the first subset of the pressurant tanks and pneumatically isolated from the second subset of the pressurant tanks and such that the one or more cold gas thrusters receive pressurant gas from the first subset of the pressurant tanks, not by way of the pressure regulator.
2. The spacecraft of claim 1 , wherein, for a substantial portion of the first mission phase, a pressure of the inert gas in the first subset of the pressurant tanks is at least 1.5 times higher than a pressure of the inert gas in the second subset the pressurant tanks.
3. An apparatus comprising:
a propulsion system for use during a mission life of a spacecraft, the propulsion system including:
an inert gas stored in pressurant tanks;
one or more electric thrusters operable with the inert gas;
one or more cold gas thrusters operable with the inert gas;
a pressure regulator disposed between and pneumatically coupled with the pressurant tanks and the one or more electric thrusters; and
a pneumatic arrangement including commandable valves, the pneumatic arrangement configured such that a first subset of the pressurant tanks is isolatable, by the commandable valves, from a second subset of the pressurant tanks; wherein:
in a first mission phase, the commandable valves are configured such that the one or more electric thrusters are pneumatically coupled, by way of the pressure regulator, with the second subset of the pressurant tanks and pneumatically isolated from the first subset of the pressurant tanks and such that the one or more cold gas thrusters are pneumatically coupled so as receive pressurant gas from the first subset of the pressurant tanks, not by way of the pressure regulator, and are pneumatically isolated from the second subset of the pressurant tanks; and
in a second mission phase, subsequent to the first mission phase, the commandable valves are configured such that the one or more electric thrusters and the one or more cold gas thrusters are pneumatically coupled, by way of the pressure regulator, with the first subset of the pressurant tanks and pneumatically isolated from the second subset of the pressurant tanks and such that the one or more cold gas thrusters receive pressurant gas from the first subset of the pressurant tanks, not by way of the pressure regulator.
4. A method comprising:
operating a spacecraft, the spacecraft having a mission life, and including a propulsion system that includes an inert gas stored in pressurant tanks, at least one electric thruster operable with the inert gas, at least one cold gas thruster operable with the inert gas, and a pneumatic arrangement including commandable valves, the pneumatic arrangement configured such that a first subset of the pressurant tanks is isolatable, by the commandable valves, from a second subset of the pressurant tanks; wherein operating the spacecraft includes:
in a first mission phase, configuring the commandable valves such that the at least one electric thruster is pneumatically coupled with the second subset of the pressurant tanks and pneumatically isolated from the first subset of the pressurant tanks and such that the at least one cold gas thruster is pneumatically coupled with the first subset of the pressurant tanks and pneumatically isolated from the second subset of the pressurant tanks; and
in a second mission phase, subsequent to the first mission phase, configuring the commandable valves such that the at least one electric thruster and the at least one cold gas thruster are pneumatically coupled with the first subset of the pressurant tanks and pneumatically isolated from the second subset of the pressurant tanks.
5. The method of claim 4 , wherein, for a substantial portion of the first mission phase, a pressure of the inert gas in the first subset of the pressurant tanks is at least 1.5 times higher than a pressure of the inert gas in the second subset the pressurant tanks.