Abstract: An autonomous compliance controlled generic mooring station includes a pair of mooring systems connected to each other. The pair of mooring systems includes a pair of mooring interfaces, allowing the pair of mooring systems to change between a mooring state and a release state. One of the pair of mooring interfaces includes an electropermanent magnet and the other one of the pair of mooring interfaces includes a ferromagnetic plate. The electropermanent magnet and the ferromagnetic plate are configured to connect the pair of mooring systems together.

Abstract: An orbit transition apparatus that transitions an orbit of a payload in outer space includes a rotating body, an adapter disposed on a center part of the rotating body for docking a payload, a launch module disposed outside of the rotating body for launching the payload, and a thruster for rotating the rotating body. The launch module may launch the payload to a target orbit.

Abstract: A stability frame for the installation of a wind turbine on an offshore substructure, wherein the wind turbine comprises a tower configured to be anchored to a rigging assembly below the barycenter of the wind turbine, has a main body configured to be mounted about the upper part of the tower; and a plurality of guides, which extend outwardly from the main body and are configured for constraining parts of the rigging assembly so as to laterally support the wind turbine by the rigging assembly.

Abstract: Vehicle capture assemblies and related devices, systems, and methods include one or more probe assemblies for engaging with and securing the target vehicle. The one or more probe assemblies may include one or more attenuation features or movable joints to enable and/or dampen movement of the one or more probe assemblies relative to a capture vehicle.

Abstract: 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.

Abstract: Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.

Abstract: Berthing systems for visiting spacecraft and associated methods. In one embodiment, a non-sealing berthing system includes a tunnel having an interface surface that mates with a docking system of a target spacecraft. The berthing system further includes sliding hooks disposed circumferentially on the interface surface of the tunnel, preload members disposed circumferentially at the interface surface of the tunnel and configured to extend and retract from the interface surface in an axial direction, guide petals spaced around an inner peripheral surface of the tunnel, and soft capture petals spaced around the inner peripheral surface of the tunnel. The soft capture petals include capture latches configured to engage mechanical latch strikers on the docking system of the target spacecraft.

Abstract: Berthing systems for visiting spacecraft and associated methods. In one embodiment, a berthing system includes a tunnel having an interface surface that defines a hard capture mating plane for mating with a docking system of a target spacecraft. The berthing system further includes hooks disposed circumferentially on the interface surface, one or more pressure seals disposed on the interface surface, spring-loaded guide petals spaced around an inner peripheral surface of the tunnel that are configured to independently slide in the axial direction, and capture latches spaced around the inner peripheral surface that are configured to engage mechanical latch strikers on the docking system.

Abstract: An exploration method includes: a step of exploring a natural resource on a satellite, a minor planet, or a planet; a step of acquiring the natural resource detected by the exploration; and a step of storing the acquired natural resource.

Abstract: Provided herein are various enhancements to spacecraft or other vehicles, including spacecraft docking mechanisms and vehicle mating systems. In one example, a vehicle mating mechanism includes a latch assembly of a vehicle having soft capture elements and hard capture elements. The soft capture elements accept a bar element of a mating vehicle and retain the bar element to within an envelope that provides a soft capture with the mating vehicle. The hard capture elements move within the envelope to engage the bar element and draw the bar element toward the vehicle to provide a hard capture with the mating vehicle. The vehicle mating mechanism can also include a cup-cone interface element of the vehicle that mates with a cup-cone interface element of the mating vehicle during the hard capture to establish an alignment between the vehicle and the mating vehicle.

Abstract: A first spacecraft comprises a drive mechanism. A second spacecraft comprises a valve for filling/draining the second spacecraft. The coupling assembly comprises a first connector comprising an actuating member configured to engage and open the valve and a coupling member configured to couple to the drive mechanism. A second connector comprises a stop portion and a bore for transferring fluid. Operation of the drive mechanism rotates the coupling member and the second connector together to screw the second connector onto the valve until the stop portion engages the valve, the actuating member being prevented from moving relative to the second connector to open the valve whilst the lock is in the locked state. Once the stop portion engages the valve, operation of the drive mechanism to exert a torque on the coupling member greater than a predetermined torque level moves the lock to an unlocked state wherein the actuating member is moveable relative to the second connector to engage and open the valve.

Abstract: A device for automatically hand-swaying beverage cups is disclosed, comprising a robotic arm and a cover, wherein the robotic arm has a plurality of movable arms and a plurality of joints that pivotally connect each of the movable arms to each other, and at the extreme end of such movable arms there install a pair of symmetrical clamping components and a clamping controller, and also includes a host computer electrically connected to each of the movable arms, each of the joints and the clamping controller, respectively; in addition, the cover respectively has a conical surface on the outside, an inner hole is openly configured on the bottom surface of the cover, and each of the clamping components can collectively clamp the cover and the cup thus facilitating the hand-swaying operations of the cup with the robotic arm.

Abstract: A representative spacecraft system includes a connecting device, which in turn includes a housing having a common port opening, a first connecting element carried by the housing and positioned to connect with a corresponding first spacecraft connecting structure having a first configuration, and a second connecting element carried by the housing and positioned to connect with a corresponding second spacecraft connecting structure having a second configuration different than the first configuration. At least one of the first and second connecting elements is moveable relative to the other between an operational position and a non-operational position, and each of the first and second connecting elements, when connected to the corresponding first or second spacecraft connecting structure, is positioned to allow transport through the common port opening.

Abstract: A satellite rescue system (SRS) (1) for rescue and recertification of dormant satellites, said SRS having a thruster end (13) with a primary propulsion nozzle (11) and maneuvering thrusters (12) and a satellite connection end (8) with a body (15) between both ends. The satellite connection end of the SRS has an interface ring (14) with clinch clamps (4) that securely attach to a ring (3) on the rescued satellite. An umbilical connector (7) on the satellite connecting end of the SRS provides power and data to the rescued satellite.

Abstract: A moving robot includes: a main body; a traveling unit configured to rotate and move the main body; a sensing unit configured to sense position information of a specific point of a front portion of a docking device; and a controller configured to, based on sensing result of the sensing unit, determine i) whether a first condition, which is preset to be satisfied when the docking device is disposed in a front of the moving robot, is satisfied, and ii) whether a second condition, which is preset to be satisfied when the moving robot is disposed in a front of the moving robot, is satisfied, to control an operation of the traveling unit so as to satisfy the first condition and the second condition, and to move to the front so as to attempt to dock in a state where the first condition and the second condition are satisfied.

Abstract: An example system includes a processor and a non-transitory computer-readable medium having stored therein instructions that are executable to cause the system to perform various functions. The functions include: (i) acquiring an image of a first aerial vehicle, the image depicting an object of a second aerial vehicle prior to contact between the object and a surface of the first aerial vehicle; (ii) providing the image as input to a data-driven analyzer that is trained in a supervised setting with example images for determining a predetermined point of contact between the object and the surface of the first aerial vehicle; (iii) determining, based on an output of the data-driven analyzer corresponding to the input, an estimated point of contact between the object and the surface of the first aerial vehicle; and (iv) providing the estimated point of contact to a display system.

Abstract: A method of achieving orbital rendezvous with a target satellite includes launching a spacecraft with a launch vehicle at an optimal time; steering the launch vehicle out-of-plane based on the orbital elements of the target satellite's orbit; and entering a predetermined rendezvous envelope of the target satellite before the target satellite completes one complete orbit from the target satellite's position at the optimal time.

Abstract: Example magnetic recovery systems and magnetic docking mechanisms for fixed-wing UAVs are disclosed herein. An example capture mechanism for an unmanned aerial vehicle (UAV) includes a first member attached to a capture vehicle, the first member having a first portion having a first shape and a magnetic portion; and a second member attached to the UAV, the second member having a second portion having a second shape, wherein the first member and the second member mutually self-align responsive to incidental contact of the first shape and the second shape, and the magnetic portion is to capture the second member.

Abstract: Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.

Abstract: 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.

Abstract: A spacecraft docking system and method thereof are provided. The system comprises an active docking device and a passive docking device. The active docking device comprises an active docking ring and a docking frame. The active docking device further comprises three sets of buffer mechanisms, each set of the buffer mechanisms comprises a main buffer, two screw nut assemblies, and a self-difference buffer. An upper end and a lower end of the screw nut assembly are movably connected to the active docking ring and the docking frame, respectively. The two screw nut assemblies in each set are simultaneously driven and stretched by the main buffer, being also connected to each other through the self-difference buffer, and able to be relatively adjusted and stretched through the self-difference buffer.

Abstract: The present disclosure relates to a low mass system for releasably securing a robotic arm to a spacecraft and also securing various payloads to the robotic arm and to each other, permitting the robotic arm to be both moved from one location to another suitably equipped location on a spacecraft to another and to allow the free end of the robotic arm to be secured to any payload also similarly equipped such that this payload may be manipulated by the robotic arm.

Abstract: According to the present invention, the device, which is provided with a male element secured to one of the parts and a female element secured to the other of said parts, comprises a plurality of resilient fastening strips forming a flared receptacle for said male element inside said female element. This receptacle is slidably movable so as to capture, pull and hold said male element inside said female element.

Abstract: A capturing plate is attached to an on-orbit device, and the capturing plate is attached to a part of the on-orbit device where a capturing device bonds to the on-orbit device in space with a bonding component, including adhesive, of the capturing device. A method for capturing the on-orbit device includes moving the capturing device including the bonding component to the on-orbit device and letting the bonding component of the capturing device adhere to the on-orbit device.

Abstract: Techniques for performing spacecraft rendezvous and/or docking include operating a first orbiting spacecraft, the first spacecraft including a sensor arrangement, a first processor and a first inter-satellite link (ISL) arrangement and performing one or both of a rendezvous operation and a docking operation with the first spacecraft and a second orbiting spacecraft, the second spacecraft including one or more actuators. The performing one or both of the rendezvous operation and the docking operation includes determining a pose and pose rate of the second spacecraft relative to the first spacecraft using observations made by the sensor arrangement and determining a desired approach trajectory for the second spacecraft.

Abstract: Provided herein are a measurement device and an operation method thereof. The measurement device senses a distance variation between the measurement device and an object using a built-in proximity sensor and accordingly determines whether to turn on or turn off a track sensing module and an optical ranging module such that the measurement device provides intelligent selection to achieve energy saving without being interfered with by other sensors being turned on.

Abstract: A faucet including a faucet head, a body and a magnetic coupling releasably coupling the faucet head to the faucet body.

Abstract: A system for imparting linear momentum transfer may include a catching mechanism of a target space vehicle and a tether that is configured to impart a linear momentum transfer from the tether to the target space vehicle. The tether may be fixedly or detachably connected to a Kinetic Energy Storage and Transfer (KEST) vehicle that maneuvers and potentially retrieves the tether. Alternatively, the tether may be separate from the KEST vehicle and may be retrieved by a suitable retrieving mechanism, such as a robotic arm.

Abstract: An aircraft-to-aircraft retrieval system can be used to capture a remote aircraft for retrieval into and service by a transport aircraft during a flight mission. An aircraft capture device can be towed from the transport aircraft and brought into proximity with the remote aircraft during flight. A probe of the remote aircraft can be received within a receptacle of the aircraft capture device, and locking cables or locking arms of the aircraft capture device can be secured onto a portion of the probe. The aircraft capture device can be provided with an activation switch for detecting contact with the probe located in the receptacle and for transmitting an indication of the contact to initiate engagement of the probe. The aircraft capture device can be locked to the probe while it is reeled to the transport aircraft for retrieval of the remote aircraft.

Abstract: Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station.

Abstract: A system and method for transferring a satellite from an initial orbit into a mission orbit. The method includes anchoring to the satellite of an external unit having a tank containing a reserve of propellants. The system includes an autonomous spacecraft having an electric propulsion module and a small internal reserve of propellants, located in a parking orbit close to the initial orbit. The spacecraft with the external unit attached to the satellite is docketed in an initial orbit, to produce a fluidic connection of the propellant tank of the external unit to the propulsion module of the spacecraft. The external unit and satellite is transferred into the mission orbit by the electric propulsion module of the spacecraft supplied with propellants directly from the external unit, thereby releasing the satellite into the mission orbit.

Abstract: There is disclosed a Payload Ejection System (PES) able to store any set of payloads for launch and eject that set of payloads at a controlled speed with a low tumble rate while accommodating any offset centre of mass within a restricted volume. The need for ballasting or balancing is eliminated thus freeing up the design space for these payloads. Insensitivity to centre of mass location is enabled by the use of a deployment hinge assembly arrangement which uses two or more non-parallel folding hinge arrangements that allow for linear motion of the output link in one direction while restricting the motion all other directions. One embodiment of the current PES concept uses four (4) hinge panel assemblies, selected to provide optimal stiffness around the entire mechanism. The stiffness of the PES is integral to managing offset centre-of-mass locations by allowing the mechanism to translate the effective force vector to the center of mass location.

Abstract: A space device includes: an adhesion part to adhere to a target existing in the space; and a propulsion part to obtain propulsion power. The space device that adheres to the target at the adhesion part moves together with the target by the propulsion part, thereby conveying the target to a predetermined target position.

Abstract: Disclosed are systems and methods for protection of a technological system (TS) from cyber attacks. An exemplary method comprises: obtaining a real state of the TS; initializing a cybernetic control system (CCS) by synchronizing the CCS with the TS; comparing, by the CCS, the real state of the TS with an ideal state of the TS; based on the comparison, identifying a deviation of the real state of the TS from the ideal state of the TS; when the deviation is identified, checking an integrity of at least functional interconnections of the states of one or more elements of the TS; determining whether the ideal state of the TS is a modeling error based on one or more confirmed sustained functional interconnections between elements of the TS; and identifying anomalies in the TS based on one or more disturbed functional interconnections between elements of the TS.

Abstract: There is disclosed a Payload Ejection System (PES) able to store any set of payloads for launch and eject that set of payloads at a controlled speed with a low tumble rate while accommodating any offset center of mass within a restricted volume. The need for ballasting or balancing is eliminated thus freeing up the design space for these payloads. Insensitivity to center of mass location is enabled by the use of a deployment hinge assembly arrangement which uses two or more non-parallel folding hinge arrangements that allow for linear motion of the output link in one direction while restricting the motion all other directions. One embodiment of the current PES concept uses four (4) hinge panel assemblies, selected to provide optimal stiffness around the entire mechanism. The stiffness of the PES is integral to managing offset center-of-mass locations by allowing the mechanism to translate the effective force vector to the center of mass location.

Abstract: Described are retroreflective marker devices, which encode information that can be read by optical sensors, such as LiDAR devices, and that do not detract from human safety. Also described are kits for retrofitting existing markers.

Abstract: A habitation module that provides an artificial gravity environment. In one embodiment, the habitation module includes a core structure having cylindrical sections spaced apart from one another, and a hub that slides over one of the cylindrical sections of the core structure to span a distance between the cylindrical sections. The hub includes a plurality of portals spaced radially around a circumference of the hub, and gravity chambers attach to portals of the hub. A drive mechanism rotates the hub about an axis in relation to the core structure to simulate a gravitational force within the gravity chambers. Rotary seals form an air-tight seal between the hub and the cylindrical sections of the core structure so that the interior of the hub and the gravity chambers may be pressurized.

Abstract: A habitation module that provides an artificial gravity environment. In one embodiment, the habitation module includes a stationary structure including a hub having a plurality of portals spaced radially around an outer cylindrical surface of the hub, and a rotating structure that attaches to the outer cylindrical surface of the hub using rotatable attachment members to rotate about an axis in relation to the hub. The rotating structure includes a platform that attaches to the rotatable attachment members and is configured to revolve around the outer cylindrical surface of the hub on the rotatable attachment members. The rotating structure also includes a gravity chamber that attaches to the platform, and projects radially from the axis. A drive mechanism is configured to rotate the rotating structure about the axis in relation to the hub to simulate a gravitational force within the gravity chamber.

Abstract: A habitation module that provides an artificial gravity environment. In one embodiment, the habitation module includes a stationary structure and a rotating structure. The stationary structure includes circular side walls that are coaxially aligned and attached by one or more support beams. The rotating structure slides onto the stationary structure, and rotates about an axis in relation to the stationary structure. The rotating structure includes a cylindrical hub, and a plurality of gravity chambers that are permanently affixed to the cylindrical hub and project radially from the axis. Radial seals form an air-tight seal between the rotating structure and the stationary structure.

Abstract: Disclosed is a sensor system for a docking station including a receiving portion, a topside of the receiving portion for receiving an electronic device, a bottom side of the receiving portion, a first magnetic sensor on the bottom side of the receiving portion for detecting the presence of the electronic device. The sensor system can further include a second magnetic sensor on the bottom side of the receiving portion for detecting the presence of the electronic device. The first sensor can be positioned to correspond to the position of the first speaker when the electronic device is seated in the topside of the receiving portion and the second sensor can be positioned to correspond to the position of the second speaker when the electronic device is seated in the topside of the receiving portion. Sensor system can detect the presence and proper position of an electronic device in a docking station by having magnetic sensors to detect a magnetic field emitted by the speakers of the electronic device.

Abstract: A multi-use resupply system for a space-based platform may include a multi-use tug to swap old and new cargo containers on a launch vehicle upper stage. The system can rely on the launch vehicle upper stage to provide the function of cargo de-orbit and disposal. The launch vehicle upper stage may be provided with sufficient propellant and propulsion functionality to operate for a long enough period in space to maneuver a new cargo container to a rendezvous trajectory, support the swapping of cargo containers, and then perform a de-orbit burn with the old cargo container.

Abstract: The present invention relates to a vision based inspection tool for setting of an initial origin of an automation machine tool, and more particularly, to a built-in type of vision based inspection tool for setting of an initial origin capable of improving setting precision of a current automation machine tool that depends on initial setting and increasing productivity depending on individual automatic setting by automatically sensing a machining origin in order to perform initial machining and re-machining of an existing workpiece using an automation machine tool and compensating for the machining origin to eliminate a time required for setting machining origins for various shapes in a jog mode.

Abstract: Systems and methods for interconnecting dual manifested spacecraft for launch by a launch vehicle are disclosed. Different motive forces are utilized to couple a first spacecraft to a second spacecraft and to restrict demating of the second spacecraft from the first spacecraft. Some systems and methods utilize pneumatic pressure to permit mating of a first spacecraft to a second spacecraft and utilize spring force to restrict demating of the second spacecraft from the first spacecraft.

Abstract: A three-dimensional (3D) coordinate measurement device combines tracker and scanner functionality. The tracker function is configured to send light to a retroreflector and determine distance to the retroreflector based on the reflected light. The tracker is also configured to track the retroreflector as it moves, and to determine 3D coordinates of the retroreflector. The scanner is configured to send a beam of light to a point on an object surface and to determine 3D coordinate of the point. In addition, the scanner is configured to adjustably focus the beam of light.

Abstract: The present invention provides a capture mechanism for capturing and locking onto the Marman flange located on the exterior surfaces of spacecraft/satellites. The capture mechanism achieves its goal of quickly capturing a client spacecraft by splitting the two basic actions involved into two separate mechanisms. One mechanism performs the quick grasp of the target while the other mechanism rigidises that grasp to ensure that the target is held as firmly as desired.

Abstract: A method for positioning an access or loading assembly against the fuselage of an aircraft during the loading or unloading process, in which at least two multichannel scanners are oriented toward the aircraft fuselage and disposed above one another at a distance from each other, each with several light emitting units and at least one detector. First, a reference position is determined by using the scanners, then a current position of the aircraft fuselage relative to the access or loading assembly is determined at determined time intervals by the multichannel scanners. The current position is compared with the reference position to determine a deviation. In case of a deviation between the two positions, a signal is transmitted to the control system of the positioning drive for realigning the access or loading assembly and reducing the deviation.

Abstract: A debris removal system that includes at least a control module that includes a debris contact module storage area, a maneuverable arm and camera storage area, a maneuverable arm, a camera, and a universal coupler socket; a guidance, control, and communications unit; a maneuvering module, wherein the maneuvering module includes fuel/propellant storage containers that provide fuel/propellant, via a control and fuel/propellant delivery conduit, to one or more control thrusters; a propulsion module, wherein the propulsion module includes fuel/propellant storage containers that provide fuel/propellant to at least one primary thrust device; and a debris contact module, wherein the debris contact module includes a debris contact member attached or coupled to a debris contact element, and wherein a universal coupler pin extends from the debris contact member so as to allow the debris contact module to be attached or coupled to the universal coupler socket of the control module.

Abstract: A method and apparatus for docking a spacecraft. The apparatus comprises elongate members, movement systems, and force management systems. The elongate members are associated with a docking structure for a spacecraft. The movement systems are configured to move the elongate members axially such that the docking structure for the spacecraft moves. Each of the elongate members is configured to move independently. The force management systems connect the movement systems to the elongate members and are configured to limit a force applied by the each of the elongate members to a desired threshold during movement of the elongate members.

Abstract: A spacecraft carrier is disclosed. The carrier has a large internal volume for housing at least one spacecraft. The carrier can be used as a repair and maintenance facility in space for spacecraft. Manned and unmanned devices can be stored, repaired and resupplied. The carrier can also transport a number of spacecraft to other locations allowing for an efficient coordinated movement of many spacecraft.

Abstract: For capturing satellites and other orbital objects, one or more independent capturing units are releasably arranged on a spacecraft serving as a steerable carrier vehicle. Each capturing unit has a propellant charge and at least one braking thrust nozzle of its own, and a closeable capture net releasably connected to the capturing unit via a tether line. The net is deployed from the capturing unit to capture the orbital object. Position or attitude control engines of the carrier vehicle are operated for orienting the combination including the capturing unit and the orbital object captured in the net. The capturing unit is then released from the carrier vehicle, and applies a braking thrust to the captured object so as to deorbit the captured object together with the capturing unit.