Flexible propulsion system
View Patent ↗A spacecraft propulsion system includes at least one chemical thruster operable with a liquid propellant, at least one electric thruster operable with an inert gas, and a first quantity ‘n’ of pressurant tanks, each of the ‘n’ pressurant tanks having a substantially identical volume. The propulsion system results from assembling a plurality of subassemblies, such that a first selectable number ‘e’ of the first quantity of pressurant tanks are manifolded together with the at least one electric thruster, and a second selectable number ‘c’ of the first quantity of pressurant tanks are manifolded together with the at least one chemical thruster. The first selectable number ‘e’ is an integer in the inclusive range of 1 to ‘n’, and c=n−e.
1. An apparatus comprising:
a propulsion system for use on a spacecraft including:
at least one chemical thruster operable with a liquid propellant;
at least one electric thruster operable with a high atomic weight inert gas; and
a first quantity ‘n’ of identically sized pressurant tanks; wherein:
the propulsion system results from assembling a plurality of subassemblies, such that a first selectable number ‘e’ of the first quantity of identically sized pressurant tanks are manifolded together with the at least one electric thruster and loaded with the high atomic weight inert gas such that the at least one electric thruster is provided with the high atomic weight inert gas, and a second selectable number ‘c’ of the first quantity of identically sized pressurant tanks are manifolded together with the at least one chemical thruster and loaded with helium or other low atomic weight pressurant;
‘e’ is an integer;
c=n−e; and
‘e’ is less than ‘n’ and greater than zero.
2. The apparatus of claim 1 , wherein each of the first quantity of identically sized pressurant tanks is interchangeable.
3. The apparatus of claim 1 , wherein a propellant management assembly is disposed between the at least one electric thruster and the first selectable number ‘e’ of the first quantity of identically sized pressurant tanks.
4. The apparatus of claim 1 , wherein a pressure control module is disposed between the at least one chemical thruster and the second selectable number ‘c’ of the first quantity of identically sized pressurant tanks.
5. The apparatus of claim 1 , wherein the propulsion system is configured to perform orbit raising of the spacecraft from a launch vehicle transfer orbit to a geosynchronous orbit.
6. The apparatus of claim 5 , wherein a first amount of the orbit raising is performed by firing the at least one chemical thruster and a second amount of the orbit raising is performed by firing the at least one electric thruster.
7. A method of fabricating a propulsion system for use on a spacecraft, the method comprising:
assembling a plurality of subassemblies of the propulsion system, including a first quantity ‘n’ of identically sized pressurant tanks, at least one chemical thruster operable with a liquid propellant and at least one electric thruster operable with a high atomic weight inert gas;
making a first determination of a first selectable number ‘e’ of the first quantity of identically sized pressurant tanks to be manifolded together with the at least one electric thruster and loaded with the high atomic weight inert gas such that the at least one electric thruster is provided with the high atomic weight inert gas;
making a second determination of a second selectable number ‘c’ of the first quantity of identically sized pressurant tanks to be manifolded together with the at least one chemical thruster and loaded with helium or other low atomic weight pressurant; and
fabricating the propulsion system from the plurality of subassemblies in accordance with the first determination and the second determination; wherein
‘e’ is an integer;
c=n−e; and
‘e’ is less than ‘n’ and greater than zero.
8. The method of claim 7 , wherein each of the identically sized pressurant tanks is interchangeable.
9. The method of claim 7 , wherein a propellant management assembly is disposed between the at least one electric thruster and the first selectable number ‘e’ of the first quantity of identically sized pressurant tanks.
10. The method of claim 7 , wherein a pressure control module is disposed between the at least one chemical thruster and the second selectable number ‘c’ of the first quantity of identically sized pressurant tanks.
11. The method of claim 7 , wherein the propulsion system is configured to perform orbit raising of the spacecraft from a launch vehicle transfer orbit to a geosynchronous orbit.
12. The method of claim 11 , wherein a first amount of the orbit raising is performed by firing the at least one chemical thruster and a second amount of the orbit raising is performed by firing the at least one electric thruster.
13. A spacecraft comprising:
a propulsion system including:
at least one chemical thruster operable with a liquid propellant;
at least one electric thruster operable with a high atomic weight inert gas; and
a first quantity ‘n’ of identically sized pressurant tanks; wherein:
the propulsion system results from assembling a plurality of subassemblies, such that a first selectable number ‘e’ of the first quantity of identically sized pressurant tanks are manifolded together with the at least one electric thruster and loaded with the high atomic weight inert gas such that the at least one electric thruster is provided with the high atomic weight inert gas, and a second selectable number ‘c’ of the first quantity of identically sized pressurant tanks are manifolded together with the at least one chemical thruster and loaded with helium or other low atomic weight pressurant;
‘e’ is an integer c=n−e; and
‘e’ is less than ‘n’ and greater than zero.
14. The spacecraft of claim 13 , wherein the propulsion system is configured to perform orbit raising of the spacecraft from a launch vehicle transfer orbit to a geosynchronous orbit.
15. The spacecraft of claim 14 , wherein a first amount of the orbit raising is performed by firing the at least one chemical thruster and a second amount of the orbit raising is performed by firing the at least one electric thruster.