Systems and methods for transferring, storing, and/or processing materials, such as fuel or propellant, in space, are disclosed. A representative system includes a flexible container that is changeable between a stowed configuration in which the flexible container is contained within a satellite, and a deployed configuration in which the flexible container extends away from the satellite. The system can include a tanker with a storage container to dock with and refuel a satellite. Another representative system includes a controller programmed with instructions that position a spacecraft with a storage container in a first orbit, transfer the spacecraft to a second orbit, dock the spacecraft with a satellite in the second orbit, transfer material between the storage container and the satellite, undock the spacecraft from the satellite, and, optionally, return the spacecraft to the first orbit. An androgynous coupling system with mechanical and fluid connectors facilitates docking and material transfer.

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 system for transferring a fluid from a first spacecraft to a second spacecraft. The first spacecraft includes a fluid transfer system comprising: a pressurant supply system, a first fluid tank to store a fluid to be transferred, one or more transfer feedlines to provide fluidic connection between the first fluid tank and the second spacecraft, a connector for connecting the first spacecraft to the second spacecraft, an accumulator tank comprising a first portion connected to the pressurant supply system, a second portion configured in fluidic communication with the one or more transfer feedlines, and a flexible separator to separate the first portion and the second portion. The pressurant supply system supplies pressurant gas to the first fluid tank for pressurising the first fluid tank and to supply pressurant gas to the first portion of the accumulator tank for pressurising the first portion of the accumulator tank.

The present invention relates to couplers for transferring fluid between space assets, particularly in a vacuum microgravity environment with radiation exposure. In particular, the couplers provide for transfer of fluids, such as propellants, coolants, pressurant gases, or life-support fluids, preferably between assets in the space environment or in terrestrial environments such as Earth, the Moon, or Mars. The couplers provide self-alignment features which enable their use in blind-mate, telerobotic, fully autonomous robotic systems. The invention provides a common design architecture for different fluids accommodating a variety of flow rates and pressure drops depending upon the particular fluid. The basic wetted component design of the invention involves a rigid, centrally-disposed nozzle on the Passive Side which contacts and opens a poppet valve on the Active Side as the two sides are coupled; and a rigid annular nozzle on the Active Side, coaxially located with but occupying a different radius than the Passive Side nozzle, which contacts and opens a corresponding contamination cover on the Passive Side.

A coupling system comprising a first androgynous coupler and a second androgynous coupler. The first androgynous coupler comprises a first male coupling section having a first recess extending radially and a first female coupling section comprising a first blocking element and a first positioning element. The second androgynous coupler comprises a second male coupling section having a second recess extending radially, where the second male coupling section is configured to form-fit with the first female coupling section. When the second male coupling section is form-fit with the first female coupling section, axial movement of the first positioning element causes the first blocking element to move radially into the second recess to couple the first androgynous coupler to the second androgynous coupler.

An example system for controlling a target satellite includes: a satellite-control spacecraft including: a propulsion subsystem configured to propel and navigate the spacecraft proximate the target satellite; and a satellite-capture subsystem configured to: capture the target satellite; apply a control medium to the target satellite, the control medium including an electrically conducting and/or magnetic material; and release the target satellite; and an energization assembly configured to energize the control medium to release energy for controlling, propelling and navigating the target satellite.

A single-person spacecraft includes a pressurized crew enclosure, an external equipment bay, and an overhead crown assembly.

A method for locating a target (C) relative to a vehicle (V), the target including at least one three-dimensional external component (Cs) presenting a quadratic surface, the method being implemented by a computer and including capturing an image of the target comprising an area of interest in which the external component of the target is visible in the form of an elliptical contour, for each of a plurality of pixels of the area of interest in the image, calculating an intensity gradient of the image around the pixel, and determining, based on the intensity gradient, the parameters of a line presenting a direction normal to the gradient at the pixel, selecting, among the set of determined lines, a set of lines that are tangents to the elliptical contour, and estimating the parameters of the elliptical contour on the image based on the parameters of the tangents to the elliptical contour.

A refinery spacecraft comprises a hub section defining a longitudinal axis, an excavator segment to convey material into the hub section, first, second and third rotary ring segments rotatable about the hub section with adjustable speed and direction, each rotary ring segments comprising three modules configured to carry out refining or storage processes and wherein two of the three modules in each rotary ring segment have adjustable angular positions relative to the longitudinal axis. Methods of collecting and refining substances from an asteroid, derelict orbiting spacecraft or other space junk, can comprise attaching a refining spacecraft to an asteroid, extracting material from the asteroid, transferring material into a refining hub, transferring material to refining rings orbiting the refining hub, and controlling orbiting of the refining rings about the hub to establish and maintain angular momentum of the refining spacecraft at a stable condition.

An orbital satellite has a pair of multi-axis booms including both thrusters for course/attitude adjustment and an end effector for grappling payloads and manipulating other tools and objects. The satellite may launch with a primary payload affixed to a bus and one or more secondary payloads affixed to an ESPA ring. Once in orbit, the end effector may be used to grapple the primary and/or secondary payloads and rearrange them on the bus. In further aspects, the end effector may be used to make bus repairs or take measurements, or hold tools that are used to make bus repairs or take measurements.