Satellite Refueling

A satellite refueling method comprising:

• positioning a refueling satellite having a first and a second fuel tank each carrying fuel, control circuitry comprising wireless communication circuitry, a first processor executing software, a first data repository and activators adapted to operate mechanisms of the refueling satellite, a first fuel hose connected at a first end to the first fuel tank of the refueling satellite, a second fuel hose connected at a first end to the second fuel tank of the refueling satellite, a first end effector connected at a second end of the first fuel hose, the first end effector comprising a plurality of thrusters providing thrust in a plurality of directions, a first fuel supply port connected through a first valve in a body of the first end effector to the first fuel hose, a first gripper mechanism adapted to grip a first fuel receptor nozzle on a satellite to be refueled, one or more imaging devices capturing images in an immediate environment of the first end effector, and first computerized circuitry adapted to provide wireless communication with the first processor at the refueling satellite, and to operate the first valve, to operate the first gripper, and to selectively operate individual ones of the plurality of thrusters of the first end effector in response to wireless signals from the first processor, and a second end effector connected at a second end of the second fuel hose, the second end effector comprising a plurality of thrusters providing thrust in a plurality of directions, a second fuel supply port connected through a second valve in a body of the second end effector to the second fuel hose, a second gripper mechanism adapted to grip a second fuel receptor nozzle on the satellite to be refueled, one or more imaging devices capturing images in an immediate environment of the second end effector, and second computerized circuitry adapted to provide wireless communication with the first processor at the refueling satellite and to operate the second valve, to operate the second gripper, and to selectively operate individual ones of the plurality of thrusters of the second end effector in response to wireless signals from the remote processor of the refueling satellite, in a position in space proximate a satellite to be refueled having a first receptor nozzle connected to a first internal storage tank and a second receptor nozzle connected to a second internal storage tank of the satellite to be refueled;
• deploying the first and the second fuel hoses with the first and second end effectors joined to the second ends from the refueling satellite by the mechanisms adapted to deploy the fuel hoses;
• maneuvering the first end effector, by selectively operating individual ones of the plurality of thrusters, to a position proximate the first receptor nozzle of the satellite to be refueled;
• maneuvering the first end effector to engage the first fuel supply port of the first end effector with the intake port of the first receptor nozzle;
• engaging the gripper of the first end effector with the first receptor nozzle and sealing the fuel supply port of the first end effector to the intake port of the first receptor nozzle;
• opening the first valve of the first end effector, flowing fuel into the first internal storage tank, and closing the first valve after fueling;
• maneuvering the second end effector, by selectively operating individual ones of the plurality of thrusters, to a position proximate the second receptor nozzle of the satellite to be refueled;
• maneuvering the second end effector to engage the second fuel supply port of the second end effector with the intake port of the second receptor nozzle;
• engaging the gripper of the second end effector with the second receptor nozzle and sealing the fuel supply port of the second end effector to the intake port of the second receptor nozzle;
• opening the second valve of the second end effector, flowing fuel into the second internal storage tank, and closing the second valve after fueling.

A satellite refueling system, comprising:

• a refueling satellite having a first and a second fuel tank each carrying fuel, and control circuitry comprising wireless communication circuitry, a first processor executing software, a first data repository and activators adapted to operate mechanisms of the refueling satellite;
• a satellite to be refueled having a first and a second receptor nozzle each having an intake port connected to an internal storage tank of the satellite to be refueled, the first and second receptor nozzles having parallel axes separated by a distance D on a region of the satellite to be refueled;
• a first fuel hose connected at a first end to the first fuel tank of the refueling satellite;
• a second fuel hose connected at a first end to the second fuel tank of the refueling satellite and joined at points along a full length to the first fuel hose;
• an end effector connected at a second end of the joined first and second fuel hoses, the end effector comprising a plurality of thrusters providing thrust in a plurality of directions, a first fuel supply port connected through a first valve in a body of the end effector to the first fuel hose, a second fuel supply port separated from the first fuel port by the distance D and connected through a second valve in the body of the end effector to the second fuel hose, a gripper mechanism adapted to grip a first fuel receptor nozzle on the satellite to be refueled, one or more imaging devices capturing images in an immediate environment of the end effector, and first computerized circuitry adapted to provide wireless communication with the first processor at the refueling satellite, and to selectively operate both the first and second valve, to operate the gripper, and to selectively operate individual ones of the plurality of thrusters of the end effector in response to wireless signals from the first processor.

A satellite refueling method comprising:

• positioning a refueling satellite having a first and a second fuel tank each carrying fuel, control circuitry comprising wireless communication circuitry, a first processor executing software, a first data repository and activators adapted to operate mechanisms of the refueling satellite, a first fuel hose connected at a first end to the first fuel tank of the refueling satellite, a second fuel hose connected at a first end to the second fuel tank of the refueling satellite, the first and second fuel hoses joined at points along a full length, an end effector connected at a second end of the joined fuel hoses, the end effector comprising a plurality of thrusters providing thrust in a plurality of directions, a first fuel supply port connected through a fuel conduit along an axis of the end effector and through a first valve to the first fuel hose, a second fuel supply port separated from the first fuel supply port by a lateral distance D, connected through a second valve in the body of the end effector to the second fuel hose, a gripper mechanism adapted to grip a fuel receptor nozzle on the satellite to be refueled, one or more imaging devices capturing images in an immediate environment of the end effector, and first computerized circuitry adapted to provide wireless communication with the first processor at the refueling satellite, and to operate the first and the second valves, to operate the gripper, and to selectively operate individual ones of the plurality of thrusters of the end effector in response to wireless signals from the first processor, at a position in space proximate a satellite to be refueled having a first receptor nozzle connected to a first internal storage tank and a second receptor nozzle connected to a second internal storage tank of the satellite to be refueled, the first and second receptor nozzles having parallel axes separated by the distance D on a region of the satellite to be refueled;
• deploying the joined first and second fuel hoses with the end effector joined to the second ends from the refueling satellite by the mechanisms adapted to deploy the fuel hoses;
• maneuvering the end effector, by selectively operating individual ones of the plurality of thrusters, to a position proximate the first and second receptor nozzles of the satellite to be refueled;
• maneuvering the end effector to engage the first fuel supply port of the end effector with the intake port of the first receptor nozzle and the second fuel supply port with the intake port of the second receptor nozzle;
• engaging the gripper of the end effector with the first receptor nozzle and sealing the fuel supply ports of the end effector to the intake ports of the first and the second receptor nozzles;
• opening the first and second valves of the end effector, flowing fuel into the first and second internal storage tanks and closing the valves after fueling.