Abstract: A spacecraft servicing system to provide in-orbit servicing through the umbilical connectors of a spacecraft. In one embodiment, a manipulator arm maneuvers a servicer umbilical to form an electrical connection between a servicer spacecraft and an umbilical connector of a client spacecraft, the umbilical connector conventionally used solely for ground-based operations. In one feature, the electrical connection is used to provide power or software upgrades to the client spacecraft.

Abstract: A service satellite for providing station keeping services to a host satellite is disclosed. The service satellite may have a body, and a gripping mechanism attached to the body. The gripping mechanism may be adapted to attach to an interface ring extending from an external surface of the host satellite to form an interconnection between the host satellite and the service satellite through the externally extending interface ring. Attaching the gripping mechanism to the interface ring may form an interconnected unit having a combined center of mass. The service satellite may have at least two thrusters and at least one controller. The at least one controller may maintain the interconnected unit in a substantially stationary orbit by selectively orienting the two thrusters such that the thrust vectors from the two thrusters avoid passing through the combined center of mass, and are each offset from the combined center of mass.

Abstract: A service satellite for providing station keeping services to a host satellite is disclosed. The service satellite may have a body, and a gripping mechanism attached to the body. The gripping mechanism may be adapted to attach to an interface ring extending from an external surface of the host satellite to form an interconnection between the host satellite and the service satellite through the externally extending interface ring. Attaching the gripping mechanism to the interface ring may form an interconnected unit having a combined center of mass. The service satellite may have at least two thrusters and at least one controller. The at least one controller may maintain the interconnected unit in a substantially stationary orbit by selectively orienting the two thrusters such that the thrust vectors from the two thrusters avoid passing through the combined center of mass, and are each offset from the combined center of mass.

Abstract: A spacecraft servicing system to provide in-orbit servicing through the umbilical connectors of a spacecraft. In one embodiment, a manipulator arm maneuvers a servicer umbilical to form an electrical connection between a servicer spacecraft and an umbilical connector of a client spacecraft, the umbilical connector conventionally used solely for ground-based operations. In one feature, the electrical connection is used to provide power or software upgrades to the client spacecraft.

Abstract: A service satellite for providing station keeping services to a host satellite is disclosed. The service satellite may have a body, and a gripping mechanism attached to the body. The gripping mechanism may be adapted to attach to an interface ring extending from an external surface of the host satellite to form an interconnection between the host satellite and the service satellite through the externally extending interface ring. Attaching the gripping mechanism to the interface ring may form an interconnected unit having a combined center of mass. The service satellite may have at least two thrusters and at least one controller. The at least one controller may maintain the interconnected unit in a substantially stationary orbit by selectively orienting the two thrusters such that the thrust vectors from the two thrusters avoid passing through the combined center of mass, and are each offset from the combined center of mass.

Abstract: A service satellite for providing station keeping services to a host satellite is disclosed. The service satellite may have a body, and a gripping mechanism attached to the body. The gripping mechanism may be adapted to attach to an interface ring extending from an external surface of the host satellite to form an interconnection between the host satellite and the service satellite through the externally extending interface ring. Attaching the gripping mechanism to the interface ring may form an interconnected unit having a combined center of mass. The service satellite may have at least two thrusters and at least one controller. The at least one controller may maintain the interconnected unit in a substantially stationary orbit by selectively orienting the two thrusters such that the thrust vectors from the two thrusters avoid passing through the combined center of mass, and are each offset from the combined center of mass.

Abstract: A service satellite for providing station keeping services to a host satellite has a body, and a gripping mechanism attached to the body. The gripping mechanism is adapted to attach to an interface ring extending from an external surface of the host satellite to form an interconnection between the host satellite and the service satellite through the externally extending interface ring. Attaching the gripping mechanism to the interface ring forms an interconnected unit having a combined center of mass. The service satellite has at least two movable thrusters and at least one controller. The at least one controller maintains the interconnected unit in a substantially stationary orbit by selectively orienting the two thrusters such that the thrust vectors from the two thrusters do not pass through the combined center of mass, and are each offset from the combined center of mass.

Abstract: The present invention relates to a service satellite having a body, a controller and a docking unit. The docking unit includes at least two foldable, adjustable gripping arms pivotally mounted on the satellite body, each gripping arm being pivotable relative to the satellite body, and a gripping end at each free end of the gripping arms, wherein the gripping ends are adapted and configured to capture and grip a target portion of an orbiting satellite. Each gripping arm is controllable independently by the controller, which coordinates the motion of the arms.

Abstract: A service satellite for providing station keeping services to a host satellite has a body, and a gripping mechanism attached to the body. The gripping mechanism is adapted to attach to an interface ring extending from an external surface of the host satellite to form an interconnection between the host satellite and the service satellite through the externally extending interface ring. Attaching the gripping mechanism to the interface ring forms an interconnected unit having a combined center of mass. The service satellite has at least two movable thrusters and at least one controller. The at least one controller maintains the interconnected unit in a substantially stationary orbit by selectively orienting the two thrusters such that the thrust vectors from the two thrusters do not pass through the combined center of mass, and are each offset from the combined center of mass.

Abstract: The present invention relates to a service satellite having a body, a controller and a docking unit. The docking unit includes at least two foldable, adjustable gripping arms pivotally mounted on the satellite body, each gripping arm being pivotable relative to the satellite body, and a gripping end at each free end of the gripping arms, wherein the gripping ends are adapted and configured to capture and grip a target portion of an orbiting satellite. Each gripping arm is controllable independently by the controller, which coordinates the motion of the arms.

Abstract: Micro satellite is disclosed with foldable solar panels that may be winded around the body of the micro satellite so that the growth in outer dimensions of the satellite is no more than 10-20 mm along each one of the length, width and height of the microsatellite so that the micro satellite may be launched in an auxiliary payload volume of a launcher. The foldable solar panels may be deployed to employ area that exceeds 9 times the product of the length by the width of the satellite and 6 times the product of the height by the length. The solar power produced by the solar panel and their light weight enable carrying of cargo that is at least 0.6 of the of the total mass of the satellites.

Abstract: Micro satellite is disclosed with foldable solar panels that may be winded around the body of the micro satellite so that the growth in outer dimensions of the satellite is no more than 10-20 mm along each one of the length, width and height of the microsatellite so that the micro satellite may be launched in an auxiliary payload volume of a launcher. The foldable solar panels may be deployed to employ area that exceeds 9 times the product of the length by the width of the satellite and 6 times the product of the height by the length. The solar power produced by the solar panel and their light weight enable carrying of cargo that is at least 0.6 of the of the total mass of the satellites.