A four-wheeled articulated steering vehicle for terrain exploration. The four-wheeled articulated steering vehicle has a pair of robotic tethered two-wheel vehicles that dock, lock, and drive long distances as the four-wheeled, articulated steering vehicle. Two actuated docking mechanisms attached on opposite ends of a central module of the four-wheeled vehicle enable sit/stand functionality. The sit configuration is achieved by aligning each dock mechanism parallel or nearly parallel to the surface, allowing two-wheel vehicle to detach and explore while the other remains docked and serves as a backup. While sitting, the central module rests on the ground and is outfitted with shovel-style wedges for passive anchoring. In order to stand, the exploring two-wheel vehicle reattaches, locks, and both dock mechanisms are rotated until each two-wheel vehicle's caster arm is upright and the central module is lifted off the ground. Once upright, each two-wheel vehicle rotates about a pivot point for articulated, all-wheel steering, which is accomplished by applying differential wheel torques.

A device comprises a tube with a tube HTS solenoid, wherein a projectile in a sabot comprising a sabot HTS solenoid. A method comprises disposing a seed HTS crystal on a growing crystal in contact with an a-b plane of the seed HTS crystal to grow the growing crystal, wherein the a-b plane is perpendicular to a c-axis. A method comprises disposing a seed HTS crystal on a growing crystal in contact with a b-c plane of the seed HTS crystal to grow the growing crystal, wherein the b-c plane is perpendicular to an a-axis. A device comprises a reinforced HTS material in a graphene casing, wherein the HTS in the graphene casing includes a cooling channel and a return channel.

A composition comprises a plurality of continuous ordered fibers embedded in a high temperature superconducting material, wherein the plurality of continuous ordered fibers comprise a core and a reinforcing material. A composition comprises one or more large diameter continuous fibers embedded in a high temperature superconducting material; and one or more small diameter continuous fibers embedded in a high temperature superconducting material. A composition comprising one or more continuous fibers embedded in a high temperature superconducting material, wherein a fiber of the one or more continuous fibers comprise a core and reinforcing material, and wherein one or more magnetic particles are embedded in the core of the fiber.

A device comprises a solenoid of reinforced HTS material, wherein the solenoid of reinforced HTS material comprises a plurality continuous ordered fibers embedded in a high temperature superconducting material. A device comprises one or more coils, wherein the one or more coils comprise HTS solenoids; an armature coupled to a stem in a control valve, wherein the armature comprises a HTS solenoid; and coolant access paths, wherein the coolant access paths enable cooling the one or more coils and the armature. A device comprises a photovoltaic cell; and a parallel array of HTS solenoids, wherein the parallel array of HTS solenoids is coupled to the photovoltaic cell.

A method comprises growing a longitudinal a-b plane high temperature superconducting crystal with a long fiber reinforced seed crystal; and cutting off the long fiber reinforced seed crystal from the longitudinal a-b plane high temperature superconducting crystal. A method comprises adding high temperature superconducting constituent powders; adding intermediate solid state powders to the constituent powders; disposing fiber reinforcement within the intermediate solid state powders and the constituent powders; compressing the intermediate solid state powders and the constituent powders with the fiber reinforcement to form a high temperature superconducting shape; and heating the high temperature superconducting shape to crystalize. A composition comprises a plurality HTS segments, wherein a HTS segment comprises one or more continuous fibers embedded in a high temperature superconducting material; and a wire or a tape, which is mechanically and electrically coupled between a first HTS segment and a second HTS segment.

The present invention relates to an elastic metamaterial for reducing vibrations of a flexible structure such as a main cable of a tether system for controlling an orbit of a satellite revolving around a planet, and a method for improving a vibration reduction performance thereof, and more particularly, to an elastic metamaterial having an improved precision, in which a ratio of a cross-sectional area of a pendulum ring may be adjusted to maintain a frequency characteristic other than a band gap generated due to the elastic metamaterial even in a state where a mass of the pendulum ring is not changed, and a band gap (R_ring) generated due to the pendulum ring of the elastic metamaterial and a band gap (R_beam) generated due to the elastic beams may be combined into one band gap to expand a vibration damping range, and a method for improving a vibration reduction performance thereof.

A device comprises a support net with nodes, wherein each node comprises a HTS photovoltaic-magnetic cell, wherein alignments of the HTS photovoltaic-magnetic cells are arranged with N-S in parallel alignment. A device comprises a tether comprising a plurality of HTS solenoids and a sheath, wherein a solenoid of the plurality of HTS solenoids comprises a high temperature superconducting material and reinforcing fiber. A device comprises propulsion ball or plate with tail, injected in propulsion channel; HTS solenoids disposed along walls of propulsion channel, wherein the propulsion ball or plate with tail are moved through the propulsion channel using magnetic field generated by HTS solenoids; and a collection channel.

A radar satellite of the present invention comprises a radar unit including a plurality of radar panels coupled to each other in a single flat plate shape, each of the plurality of radar panels including a plurality of antennas which transmit and receive radar waves, and a solar cell; and a communication/control unit which performs communications with a spot on an earth or a spacecraft. The radar unit includes: a radar panel array which is a plate-shaped structure including the plurality of radar panels; and a deployable truss structure including a plurality of side frame members supporting the plurality of radar panels, respectively, and coupled to each other in such a manner that the side frame members are foldable and deployable.

A link device comprising a first object and a second object comprises a first strip, capable of passing from a configuration wound about an axis Z about a support fixed to the first object to a configuration deployed along an axis X substantially at right angles to the axis Z, the strip having an end intended to come into contact with the second object, so as to link the first object to the second object.

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 servicing device may include a communication device configured to receive data relating to the target spacecraft from a location remote from the spacecraft servicing device. The servicing device may include a coupling mechanism comprising at least one movable coupling configured to rotate the body relative to the target spacecraft when the spacecraft servicing pod is coupled to the target spacecraft. The at least one spacecraft servicing component may include at least one propulsion device positioned on a boom arm extending away from the body.