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.

Movable platforms for use with a vehicle capture assembly of a capture vehicle and related devices, systems, and methods include floors with rotatable legs extending between the floors. The rotation of the legs relative to one or more of the floors enables the movable platform to move from an initial position to a displaced position as one or more of the floors move relative to each other.

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.

A fluid transfer interface is provided. The fluid transfer interface includes one or more of first and second interface portions. The first interface portion includes a first portion of a fluid connector and one or more ferromagnetic surfaces. The second interface portion includes an extendable second portion of the fluid connector and one or more electropermanent magnets, laterally disposed around the second portion of the fluid connector, configured to be magnetized or demagnetized in unison. The one or more electropermanent magnets are further configured to provide attraction force to the one or more ferromagnetic surfaces when magnetized and couple the first interface portion to the second interface portion and provide no attraction force to the one or more ferromagnetic surfaces when demagnetized and allow the first interface portion to be decoupled from the second interface portion.

Spacecraft servicing systems include a spacecraft servicing device and at least one pod comprising at least one spacecraft servicing component. The spacecraft servicing device is configured to transfer the at least one pod to a target spacecraft in order to service the target spacecraft with the at least one spacecraft servicing component of the at least one pod. Spacecraft servicing pods configured to be supplied to a spacecraft with a spacecraft servicing device include at least one spacecraft servicing component.

Spacecraft servicing devices and related methods may include a propellant tank configured to store a propellant and to be placed into fluid communication with a portion of the target spacecraft.

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.

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.

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.