Spacecraft servicing devices or pods and related methods may include a body configured to be deployed from a host spacecraft at a location adjacent a target spacecraft and at least one spacecraft servicing component configured to perform at least one servicing operation on the target spacecraft.

The present disclosure relates to a robotically controlled satellite refueling tool and associated robotically controlled support and site preparation tools which facilitates on-orbit refueling by teleoperation of fill/drain valves of various designs and dimensions on satellites not originally prepared for on-orbit servicing, through the installation of quick connect safety valves, using vision-based feedback as well as feedback from sensors embedded in the refueling tool to operate a suite of adaptable and adjustable mechanisms. The refueling tool has an open architecture to allow a refueling tool vision system to see the fill/drain valve and the section of the refueling tool that is engaged with the fill/drain valve. The support tools include a blanket cutter tool, a blanket handler tool, a wire cutter tool, a gripper tool, and the site preparation tools include a B-nut removal tool and a crush seal removal tool. Each of these tools includes a common base structure which is interfaced to the end effector of the robotic arm for transmitting rotation and torque to the various tools.

An object is to notify an appropriate intrusion alert by determining whether debris will intrude into an orbit area of a satellite constellation. A passage determination unit (110) determines whether debris will pass through a satellite orbit area, based on satellite orbit forecast information in which a forecast value of an orbit of a satellite is set and debris orbit forecast information in which a forecast value of an orbit of debris is set. When it is determined that debris will pass through the satellite orbit area, an alert generation unit (120) generates an intrusion alert (111) including a predicted time, predicted location coordinates, and predicted velocity vector information that relate to passage of the debris. An alert notification unit (130) notifies the intrusion alert (111) to a management business device (40) used by a management business operator that manages a satellite that flies in the satellite orbit area.

A method for coupling an energy supplying device to an energy consuming device in space and to a system including an energy supplying device, an energy consuming device and a mobile assembly unit residing in space. The energy supplying device is operable in space and includes solar panel units to convert received light into electrical energy, first coupling members to couple the solar panel units with each other, and a second coupling member to electrically couple the energy supplying device with the energy consuming device. The energy supplying device is configured to supply electrical energy to the energy consuming device in space. A configuration of the solar panel units is changeable in space according to an operational requirement of the energy consuming device.

Methods and systems for mitigating or reducing the risk of an electrostatic discharge due to static charge differentials between a first spacecraft and a second spacecraft as the first spacecraft approaches the second spacecraft may be accomplished using a passive electrostatic discharge mitigation device. In some embodiments, mitigation of static potential between the first spacecraft and the second spacecraft may be actively accomplished by an electric propulsion system provided on the first spacecraft. In some embodiments, mitigation may be provided by both actively and passively mitigating static potential between the first spacecraft and the second spacecraft.

Capture assemblies and compliant extension assemblies may be utilized for insertion into a nozzle of a liquid engine of a spacecraft. The capture assembly may include an apparatus such as a probe for insertion into the nozzle and an assembly at least partially enclosed in a forward portion of the probe. The assembly may include a plurality of actuated fingers for deploying outwardly from the probe when the probe is inserted into the nozzle. The compliant extension assembly may be at least partially enclosed in a housing connected to the capture assembly for axial movement of the probe. The compliant extension assembly may facilitate axial movement of the probe between a retracted position and an extended position, wherein the probe is extended forwardly, relative to the housing.

A service satellite having a body, a controller and a docking unit including a telescopic arm, mounted on a 6-DOF parallel manipulator, and two additional gripping arms. The telescopic arm, deployed from the 6-DOF manipulator, is equipped with a pair of rapid closure digits. The telescopic arm facilitates capturing the launch adaptor ring of a client spacecraft, even during tumbling. The 6-DOF parallel manipulator has force sensors and can accommodate post capturing relative motion through active compliance control and controlled de-tumbling, for avoiding generation of high forces in the telescopic arm. After relative rate annihilation, the telescopic arm retracts and the client ring is secured to the 6-DOF manipulator with the help of a pair of clamps. After the ring is secured, two additional gripping arms secure a rigid connection with the launcher ring so that the docking connection comprises three equally spaced connections.

Satellite systems and methods to perform rendezvous and docking between a servicer satellite and an on-orbit satellite, and specifically to satellite systems and methods to perform rendezvous and docking between a servicer satellite and an on-orbit client satellite using electric propulsion thrusters. In one aspect, a servicer satellite with a set of thruster arms each attached to an electric propulsion thruster performs acceleration, deceleration, and steering maneuvers through six degree of freedom positioning of the thrusters, the same set of thruster arms and thrusters performing station keeping of the docked servicer-client satellite system.

The present disclosure relates to a robotically controlled satellite refueling tool and associated robotically controlled support and site preparation tools which facilitates on-orbit refueling by teleoperation of fill/drain valves of various designs and dimensions on satellites not originally prepared for on-orbit servicing, through the installation of quick connect safety valves, using vision-based feedback as well as feedback from sensors embedded in the refueling tool to operate a suite of adaptable and adjustable mechanisms. The refueling tool has an open architecture to allow a refueling tool vision system to see the fill/drain valve and the section of the refueling tool that is engaged with the fill/drain valve. The support tools include a blanket cutter tool, a blanket handler tool, a wire cutter tool, a gripper tool, and the site preparation tools include a B-nut removal tool and a crush seal removal tool. Each of these tools includes a common base structure which is interfaced to the end effector of the robotic arm for transmitting rotation and torque to the various tools.

Satellite systems and methods to perform rendezvous and docking between a servicer satellite and an on-orbit satellite, and specifically to satellite systems and methods to perform rendezvous and docking between a servicer satellite and an on-orbit client satellite using electric propulsion thrusters. In one aspect, a servicer satellite with a set of thruster arms each attached to an electric propulsion thruster performs acceleration, deceleration, and steering maneuvers through six degree of freedom positioning of the thrusters, the same set of thruster arms and thrusters performing station keeping of the docked servicer-client satellite system.