Systems and methods for multi-armed robotic capture devices are disclosed. The systems and methods for multi-armed robotic capture devices include a base that is configured to attach to a robotic arm or a servicer and having a tether. The systems and methods for multi-armed robotic capture devices include a body that is coupled to the base via the tether. Additionally, the systems and methods for multi-armed robotic capture devices include a plurality of tentacles coupled to the body and configured to grip a target object. The systems and methods for multi-armed robotic capture devices also include a plurality of tiles positioned on each tentacle of the plurality of tentacles and configured to apply a shear force on the target object to grip the target object using an adhesive force.

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.

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.

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.

A reusable modular spacecraft has a spacecraft bus structure configured to support spacecraft subsystems, at least one interchangeable housing component configured to be interchangeably received and supported by the bus structure, and a wireless system configured to permit wireless communication between the at least one interchangeable housing component and spacecraft subsystems supported by the bus structure. In embodiments of the spacecraft, the wireless system includes a wireless hub and a wireless coordinator for wireless transmission of data between the at least one interchangeable housing component and the spacecraft subsystems. An electrical/power transfer interface unit is provided to the at least one interchangeable housing component for transferring electricity, power, data and/or providing thermal management and control.

A first spacecraft includes a first fluid storage arrangement and a fluid flow metering arrangement including a holding tank coupled with the first fluid storage arrangement, a flow meter disposed proximate to the holding tank, and an active thermal control arrangement controlling the temperature of the flow meter and the holding tank. The first spacecraft is configured to service a second spacecraft, the second spacecraft including a second fluid storage arrangement, by transferring one or both of a propellant and a pressurant from the first fluid storage arrangement to the holding tank, and from the holding tank, through the flow meter, to the second fluid storage arrangement.

Disclosed are systems and methods for a distributed space transportation network. Satellite launches to orbit are more efficiently performed by large rockets. Modern satellites are in smaller form factor, leaving the large launch rockets with excess capacity. Small satellite operators can use ride-shares, but do not have efficient options for delivering their satellites to their desired destination and may be forced to operate their satellites in compromise orbits. The disclosed distributed space transportation network maintains a fleet of space tugs, which can dock with satellites in space at an initial arrival destination and transport the satellites to their final destinations. In one embodiment, the space tugs can dock with satellite depots to obtain fuel and repairs.

Systems, methods, and apparatus for magnetic maneuvering for satellites are disclosed. In one or more embodiments, a method for maneuvering satellites comprises applying, by a current source in a first satellite, current to an electromagnet in the first satellite. The method further comprises generating, by the electromagnet in the first satellite in response to the current, a magnetic field. Further, the method comprises maneuvering, by the first satellite, a second satellite via the magnetic field. In one or more embodiments, the electromagnet comprises a torque rod, an electric motor coil, and/or a solar array. In one or more embodiments, the second satellite comprises a ferromagnetic or ferrimagnetic material, a conductive material, or a combination thereof. In some embodiments, the second satellite comprises an electromagnet.

A transportation network for providing propellant in space can include optical mining vehicles that concentrate solar energy to spall captured asteroids, capture released volatiles, and store them in reservoirs as propellants. The network can also have orbital transfer vehicles that use solar thermal rocket modules that focus solar energy on heat exchangers to force propellant through nozzles, as well as separable aeromaneuvering tanker modules with reusable heatshields and storage tanks. The network can have propellant depots positioned between Earth and a transport destination. The depots can mechanically couple to accept propellant delivery and to supply it to visiting space vehicles.

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.