Abstract: 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.

Abstract: 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.

Abstract: A first satellite and a second satellite are configured to be disposed together, in a launch configuration, for launch by a single launch vehicle. The launch vehicle includes a primary payload adapter and the first satellite includes a secondary payload adapter. In the launch configuration, the first satellite is mechanically coupled with the primary payload adapter and the second satellite is mechanically coupled with the secondary payload adapter. Following injection into a first orbit by the launch vehicle, the first satellite separates from the primary payload adapter while the second satellite is mechanically coupled with the secondary payload adapter. The second satellite is detached from the secondary payload adapter of the first satellite only after an orbit transfer maneuver executed by a propulsions system of the first satellite. In the launch configuration, the mass of the second satellite is at least 30% of the mass of the first satellite.