A system comprising: a plurality of spacecraft mechanically coupled together in a stack in a launch configuration, the plurality of spacecraft comprising: a first spacecraft (102) comprising a first propellant storage (202) and a first thruster (204) coupled with the first propellant storage (202), wherein the first spacecraft (102) is configured to mechanically couple with a payload adapter of a launch vehicle in the launch configuration; and a second spacecraft (102) comprising a second propellant storage (202) and a second thruster (204) coupled with the second propellant storage (202), wherein in the launch configuration the second spacecraft (102) is above the first spacecraft (102) in the stack, wherein the second propellant storage (202) is empty at launch; and a propellant line arrangement (222, 224) that couples the first propellant storage and the second propellant storage (202); wherein the system is configured to: transfer propellant by way of the propellant line arrangement (222, 224), subsequent to a launch phase of the launch vehicle, from the first propellant storage (202) to the second propellant storage (202); deploy the first spacecraft (102) and the second spacecraft (102) from the launch vehicle subsequent to the launch phase; and operate the second thruster (204) with the transferred propellant in the second propellant storage (202) during an orbit raising maneuver of at least the second spacecraft (102) subsequent to the deployment of the first spacecraft (102) and the second spacecraft (102) from the launch vehicle. a plurality of spacecraft mechanically coupled together in a stack in a launch configuration, the plurality of spacecraft comprising: a first spacecraft (102) comprising a first propellant storage (202) and a first thruster (204) coupled with the first propellant storage (202), wherein the first spacecraft (102) is configured to mechanically couple with a payload adapter of a launch vehicle in the launch configuration; and a second spacecraft (102) comprising a second propellant storage (202) and a second thruster (204) coupled with the second propellant storage (202), wherein in the launch configuration the second spacecraft (102) is above the first spacecraft (102) in the stack, wherein the second propellant storage (202) is empty at launch; and a first spacecraft (102) comprising a first propellant storage (202) and a first thruster (204) coupled with the first propellant storage (202), wherein the first spacecraft (102) is configured to mechanically couple with a payload adapter of a launch vehicle in the launch configuration; and a second spacecraft (102) comprising a second propellant storage (202) and a second thruster (204) coupled with the second propellant storage (202), wherein in the launch configuration the second spacecraft (102) is above the first spacecraft (102) in the stack, wherein the second propellant storage (202) is empty at launch; and a propellant line arrangement (222, 224) that couples the first propellant storage and the second propellant storage (202); wherein the system is configured to: transfer propellant by way of the propellant line arrangement (222, 224), subsequent to a launch phase of the launch vehicle, from the first propellant storage (202) to the second propellant storage (202); deploy the first spacecraft (102) and the second spacecraft (102) from the launch vehicle subsequent to the launch phase; and operate the second thruster (204) with the transferred propellant in the second propellant storage (202) during an orbit raising maneuver of at least the second spacecraft (102) subsequent to the deployment of the first spacecraft (102) and the second spacecraft (102) from the launch vehicle. transfer propellant by way of the propellant line arrangement (222, 224), subsequent to a launch phase of the launch vehicle, from the first propellant storage (202) to the second propellant storage (202); deploy the first spacecraft (102) and the second spacecraft (102) from the launch vehicle subsequent to the launch phase; and operate the second thruster (204) with the transferred propellant in the second propellant storage (202) during an orbit raising maneuver of at least the second spacecraft (102) subsequent to the deployment of the first spacecraft (102) and the second spacecraft (102) from the launch vehicle.