A spacecraft includes a plurality of deployable module elements, at least one of the deployable module elements including a robotic manipulator, the spacecraft being reconfigurable from a launch configuration to an on-orbit configuration. In the launch configuration, the deployable module elements are disposed in a launch vehicle in a first arrangement. In the on-orbit configuration, the deployable module elements are disposed in a second configuration. The spacecraft is self-assembled by the robotic manipulator reconfiguring the spacecraft from the launch configuration, through a transition configuration, to the on-orbit configuration. The deployable module elements may be in a stacked arrangement in the launch configuration and may be in a side-by-side arrangement in the on-orbit configuration.

A system for manufacturing a space-based component while on orbit around the Earth. The system includes a spacecraft body and a solar collection device mounted thereto for collecting solar energy from the sun that is converted into heat. The system includes a manipulator device that moves a solar refinery to a position to collect space debris, where the manipulator then moves the solar refinery to location that uses the heat to melt constituent elements in the debris. The solar refinery also includes a collection element capable of separately collecting the heated elements. The system also includes a fabrication module that is operable to obtain solid, molten or vaporized elements from the collection element and fabricate the space-based component therefrom.

A power controller of a linear actuator 10 in a docking device 1 including a six-axis parallel link mechanism 5, wherein a motor driver 11 configured to control rotation speed of a motor M of the linear actuator 10 on the basis of a load produced on the link 4 includes a speed controlling unit 31 that outputs a current command, a current controlling unit 32 that converts the current command to a voltage command, and a current command limiter 33 that limits the current command of the speed controlling unit 31 so that power consumption per one linear actuator 10 is one sixth or less of the power supply capacity for the motor power, thus allowing for mounting the docking device 1 even for a spacecraft with a small power supply capacity, without requiring modification of the power supply capacity.

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. The service satellite also includes a propulsion unit including a first thruster mounted adjacent a Nadir end of the service satellite body, and a balance thruster, the balance thruster being distanced from the first thruster and facing a different direction than the first thruster, propellant for the thruster and the balance thruster; and means for aligning the thrusters so that a thrusting vector passes through a joint center of gravity of the service satellite and the serviced satellite.

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 gateway segment assembly line that allows for the construction of space stations while in orbit by fabricating individual segments in space. An assembly housing provides an open ended structure through which materials are processed in order to construct a segment for a space station. The materials are loaded into a plurality of workstations positioned along the assembly housing through the use of a plurality of external manipulators adjacently connected to the assembly housing. Each of the plurality of workstations provides the equipment for sequentially loading materials into the assembly housing. An assembly line conveyor, positioned throughout the plurality of workstations, guides materials through the assembly housing as the materials are mated to form the segment. Upon completion of the segment, a plurality of segment transport units transports the segment to an orbital construction site, wherein the segment is mated with subsequent segments to form the space station.

A spacecraft including a main body structure and at least a first deployable element is reconfigured from a launch configuration to an on-orbit configuration. In the launch configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a first arrangement. In the on-orbit configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a second arrangement. Reconfiguring the spacecraft includes detaching the first deployable element from the first arrangement, moving the first deployable element with respect to the spacecraft main body structure; and attaching the first deployable element to the second arrangement.

Two objects can be connected, e.g., in space, by maneuvering a gripper proximate a target which may be in space, commanding the snap-band controller to move the snap-band into its open position, maneuvering the gripper to a further position closer to the target to where the controllable snap-band, when closed, at least partially encircles the target, and commanding the snap-band controller to move the controllable snap-band into its closed position to at least partially encircle and capture the target. The gripper comprises a controllable snap-band comprising a selectable open position and closed position which is disposed about an external surface of a housing.

End effectors and systems may capture, release, and/or create a mating engagement between the end effector and a target object. Said end effectors are tolerant of positional and rotational misalignment of the target object, and include a plurality of roller wheels, one or more of which is arranged in a non-parallel plane with respect to one or more other roller wheels. A first roller wheel configured to rotate in a first plane, a second roller wheel configured to rotate in a second plane, and a third roller wheel configured to rotate in a third plane may be arranged such that the end effector is configured to engage a passive receptacle of the target object, to capture the target object. Rotating the roller wheels in the opposite direction may cause the target object to be released or launched, by urging the passive receptacle off of or away from the roller wheels.

A ground simulation device and method for an on-orbit manipulation of a space manipulator is provided. The ground simulation device includes: a dual-arm robot, configured to simulate the space manipulator operating a target object; a suspension device, including a fixed post and passive rods, where the passive rods are movably connected with a top end of the fixed post, and the target object is suspended to the passive rods; and a simulation platform, configured to fix the dual-arm robot and the suspension device thereon. The ground simulation device provides the passive rods on the suspension device and suspends the target object to the passive rods, thus overcoming the gravity of the target object. In addition, the passive rods can drive the target object to move under an influence of an external force, achieving a similar suspension effect to that in space, and providing a desired, safe, and reliable implementation effect.