Cross-feeding propellant between stacked spacecraft
A first spacecraft and a second spacecraft are configured to be disposed together, in a launch configuration, for launch by a single launch vehicle. In the launch configuration, the first spacecraft is mechanically coupled with a primary payload adapter of the launch vehicle, and the second spacecraft is mechanically coupled with the first spacecraft by way of an inter-spacecraft coupling arrangement. The spacecraft are configured to be deployed, following injection into a first orbit by the launch vehicle, by separating the first spacecraft from the primary payload adapter while the second spacecraft is mechanically coupled with the first spacecraft. A first onboard propulsion subsystem of the first spacecraft includes one or more thrusters configured to execute an orbit transfer maneuver from the first orbit to a second orbit. A propellant line arrangement detachably couples the first onboard propulsion subsystem with a second propellant storage arrangement on the second spacecraft.
1. A system comprising:
at least two spacecraft, including at least a first spacecraft and a second spacecraft, the at least two spacecraft disposed together, in a launch configuration, for launch by a single launch vehicle; wherein:
in the launch configuration, the first spacecraft is mechanically coupled with a primary payload adapter of the launch vehicle, and the second spacecraft is mechanically coupled with the first spacecraft by way of an inter-spacecraft coupling arrangement;
the system is configured to be deployed, following injection into a first orbit by the launch vehicle, by separating the first spacecraft from the primary payload adapter while the second spacecraft is mechanically coupled with the first spacecraft;
the first spacecraft includes a first onboard propulsion subsystem including a first propellant storage arrangement;
the second spacecraft includes a second onboard propulsion subsystem including a second propellant storage arrangement;
the first onboard propulsion subsystem includes one or more thrusters configured to execute an orbit transfer maneuver from the first orbit to a second orbit; and
the system includes a propellant line arrangement that detachably couples the first propellant storage arrangement with the second propellant storage arrangement.
2. The system of claim 1 , wherein the one or more thrusters configured to execute the orbit transfer maneuver includes a main satellite thruster (MST).
3. The system of claim 2 , wherein the MST is a high thrust chemical thruster.
4. The system of claim 3 , wherein propellant stored in each of the first propellant storage arrangement and the second propellant storage arrangement is available for use by the MST.
5. The system of claim 1 , wherein the one or more thrusters configured to execute the orbit transfer maneuver includes a high specific impulse electric thruster.
6. The system of claim 5 , wherein propellant stored in each of the first propellant storage arrangement and the second propellant storage arrangement is available for use by the high specific impulse electric thruster.
7. The system of claim 1 , wherein the one or more thrusters configured to execute the orbit transfer maneuver include one or both of a first high specific impulse electric thruster and a first high thrust chemical thruster.
8. The system of claim 7 , wherein propellant stored in each of the first propellant storage arrangement and the second propellant storage arrangement is available for use by at least one of the first high specific impulse electric thruster and a first high thrust chemical thruster.
9. The system of claim 7 , wherein the second onboard propulsion subsystem does not include a high thrust chemical thruster.
10. The system of claim 7 , wherein the second onboard propulsion subsystem includes one or both of a monopropellant thruster and a cold gas thruster, does not include high thrust chemical thruster and does not include a high specific impulse electric thruster.
11. The system of claim 1 , wherein the propellant line arrangement includes a line disconnect including a proximal portion and a distal portion, each of the proximal portion and the distal portion including a respective valving element.
12. The system of claim 11 , wherein the respective valving elements permit propellant flow when the distal portion and the proximal portion are mutually engaged and prevent propellant flow when the distal portion and the proximal portion are detached.
13. A method comprising:
deploying a payload stack including at least a first spacecraft and a second spacecraft, the first spacecraft and the second spacecraft disposed together, in a launch configuration, for launch by a single launch vehicle, wherein deploying the payload stack includes separating the first spacecraft from the single launch vehicle while the second spacecraft is mechanically coupled with the first spacecraft;
executing an orbit transfer maneuver from a first orbit to a second orbit; and
detaching the second spacecraft from the first spacecraft only after executing the orbit transfer maneuver; wherein:
the first spacecraft includes a first onboard propulsion subsystem including a first propellant storage arrangement;
the second spacecraft includes a second onboard propulsion subsystem including a second propellant storage arrangement;
the first onboard propulsion subsystem includes one or more thrusters configured to execute an orbit transfer maneuver from the first orbit to a second orbit; and
the payload stack includes a propellant line arrangement that detachably couples the first propellant storage arrangement with the second propellant storage arrangement.
14. The method of claim 13 , wherein propellant stored in each of the first propellant storage arrangement and the second propellant storage arrangement is available for use by the first onboard propulsion subsystem.
15. The method of claim 13 , wherein the one or more thrusters configured to execute the orbit transfer maneuver include one or both of a first high specific impulse electric thruster and a first high thrust chemical thruster.
16. The method of claim 15 , wherein propellant stored in each of the first propellant storage arrangement and the second propellant storage arrangement is available for use by at least one of the first high specific impulse electric thruster and a first high thrust chemical thruster.
17. The method of claim 15 , wherein the second onboard propulsion subsystem does not include a high thrust chemical thruster.
18. The method of claim 13 , wherein the propellant line arrangement includes a line disconnect including a proximal portion and a distal portion, each of the proximal portion and the distal portion including a respective valving element.
19. The method of claim 18 , wherein the respective valving elements permit propellant flow when the distal portion and the proximal portion are mutually engaged and prevent propellant flow when the distal portion and the proximal portion are detached.
20. The method of claim 19 , wherein detaching the second spacecraft from the first spacecraft includes detaching the proximal portion of the propellant line arrangement from the distal portion of the propellant line arrangement.