Abstract: An unmanned aerial vehicle system includes an unmanned aerial vehicle, a tether assembly selectively coupled to the unmanned aerial vehicle, a processor, and a memory. The memory contains instructions thereon, which, when executed by the processor, cause the system to disconnect the tether assembly from the unmanned aerial vehicle.

Abstract: A spacecraft onboard equipment and payload storage system comprising a spacecraft having an interior volume, wherein said interior volume comprises a interior annular portion; a annular storage support track connected to said spacecraft within said spacecraft's interior annular portion; and at least one storage module that is movably connected to said annular storage support track.

Abstract: A lightweight spacecraft dispenser, which consists of a material made from composite materials, and of a ring structure with several payload ports. The ring structure has a surface that extends between opposite ends of the ring structure and that is at least partially spherical. The surface can be completely spherical or partially spherical between the opposite ends.

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

Abstract: A vehicle for intercepting a target object orbiting in space is provided, comprising a launching portion for driving the vehicle into an orbit, and an interception portion for intercepting a target object when the vehicle is in orbit, wherein the interception portion comprises means for engaging with the target object and wherein the launching portion is arranged to drive the vehicle into a first elliptical orbit and the vehicle is arranged to adopt a second elliptical orbit when engaged with the target object in which the first elliptical orbit is arranged so as to intersect the orbit of the target object at an interception point, and the second elliptical orbit is such that the vehicle is arranged to move from the interception point towards the Earth's atmosphere when engaged with the target object.

Abstract: Methods of accelerating a target vehicle to a higher orbit via a Kinetic Energy Storage and Transfer (KEST) vehicle are provided. The KEST vehicle is configured to transfer kinetic energy to the target vehicle by way of a catching mechanism using one or more brakes on one or more associated tethers along which the braking mechanism traverses, accelerating the target vehicle into a higher orbit, potentially even beyond the Earth.

Abstract: Disclosed are a space object disposal device and a space object disposal method using a rotation motion. The device for disposing a space object includes: a disposal orbit calculation unit configured to calculate a disposal orbit of a space object; an escape velocity calculation unit configured to calculate an escape velocity at which the space object moves along the disposal orbit; and a rotation driving unit configured to be connected the space object, rotate the space object on a predetermined rotation orbit so as to reach the escape velocity, and separate the space object at a point of contact of the predetermined rotation orbit and the disposal orbit when the space object rotates at the escape velocity.

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.

Abstract: A tethered spacecraft has a first endmass and a second endmass with a telescoping stacer spring and a tether arranged between the endmasses. The spring is coiled around a center rod and initially contained within a housing, the spring being biased to push the first endmass away from the second endmass. The spring housing is affixed to the first endmass, a first end of the spring being affixed to the spring housing, and tether are affixed to spring at one end and to the second endmass at the other end. A pretensioned loop holds the endmasses abuttingly together, and a burnwire release mechanism cuts the loop to deploy the spring. Upon deployment, the spring extends to its full length to form a cylindrical boom, and the endmasses continue to move outward along the spring centerline until stopped by the tether.

Abstract: A deorbit device comprising a passive electrodynamic conductive tape connected at one end to a spacecraft.

Abstract: A burn wire release mechanism for a spacecraft or other system having two masses initially held together by a pretensioned loop, with a spring configured to push the masses apart. The burn wire release system includes at least one burn wire held in contact with the pretensioned loop material. When an electrical current flows through the burn wire, the wire heats up and severs the pretensioned loop, and the masses are pushed apart by the spring.

Abstract: A spacecraft reaction control system comprising: a spacecraft having a center of mass; a length of tether extending from said spacecraft and offset from said spacecraft's center of mass and means for controllably changing said extension of said offset such that a variable force is exerted upon said spacecraft by said tether, said force being offset from said center of mass.

Abstract: A Kinetic Energy Storage and Transfer (KEST) vehicle and target vehicle kinetic energy transfer method are provided. The KEST vehicle is configured to transfer kinetic energy to the target vehicle, propelling the target vehicle into a higher orbit or beyond the Earth. This is accomplished by a catching mechanism that contacts the target vehicle. The catching mechanism may also include a braking mechanism configured to accelerate the target vehicle, and thus slow the KEST vehicle, as the catching mechanism and target vehicle travel along one or more tethers of the KEST vehicle. Alternatively, the catching mechanism may be attached to an end of the one or more tethers and be configured to slow the target vehicle as the one or more tethers bend.

Abstract: A processing and delivery system is in space around a celestial body having a magnetic field. The system includes at least one facility having supplies and configured for in-space recycling and manufacturing to produce processed objects utilizing space debris objects and the supplies. The system includes at least one space vehicle configured to deliver the space debris objects from their orbits to the at least one facility using electrodynamic propulsion. The system includes at least one space vehicle configured to deliver new supplies to the at least one facility from other orbits using electrodynamic propulsion. The system includes at least one space vehicle configured to deliver the processed objects from the at least one facility to their destination orbits using electrodynamic propulsion.

Abstract: A debris removal management system and a method of removing space debris. In one embodiment, the system includes: (1) a frame, (2) a plurality of net sections coupled to the frame and (3) a plurality of microvehicles, coupled to the plurality of net sections, configured to employ propulsion units therein to be ejected relative to the frame to deploy the plurality of net sections, the plurality of net sections cooperating to form a net configured to capture space debris.

Abstract: A debris removal management system and a method of removing space debris. In one embodiment, the system includes: (1) a frame, (2) a plurality of net sections coupled to the frame and (3) a plurality of microvehicles, coupled to the plurality of net sections, configured to employ propulsion units therein to be ejected relative to the frame to deploy the plurality of net sections, the plurality of net sections cooperating to form a net configured to capture space debris.

Abstract: The effective area of an electric sail depends on the voltage applied to tethers. The use of higher voltages is made possible by moving voltage multipliers to tethers, perhaps 100 meters out from the body of the spacecraft.

Abstract: The invention relates to the energy provision of space transport systems and to the organization of a load flow between spacecraft in planetary orbits. The method comprises a spacecraft tank trapping and accelerating atmospheric air and loads located in the trajectory of movement thereof. The loads are transported beforehand to said trajectory by corresponding spacecraft, including suborbital spacecraft, and are then transferred to other spacecraft. Velocity losses of the spacecraft tank due to the trapping and accelerating of atmospheric air, loads and to aerodynamic drag are compensated for by a propulsion unit. The propulsion unit may use reactive engines—with consumption of part of the incoming load—or electrodynamic cable systems. Operation of the propulsion unit of the spacecraft tank is ensured by a supply of load energy carriers using atmospheric gases.

Abstract: A debris removal management system and a method of removing space debris. In one embodiment, the system includes: (1) a frame, (2) a plurality of net sections coupled to the frame and (3) a plurality of microvehicles coupled to the plurality of net sections and configured to be ejected relative to the frame to deploy the plurality of net sections, the plurality of net sections cooperating to form a net configured to capture space debris.

Abstract: A towing apparatus for a spacecraft when in orbit is provided. The towing apparatus includes a cable, the first end of which is intended to be permanently connected to a spacecraft that must potentially be towed, and the second end of which is provided to be at least temporarily connected to a towing spacecraft for the purpose of towing. An attachment piece is disposed on the second end of the cable for mechanical attachment to a complementary attachment piece of the towing spacecraft, and a positioning aid is disposed to allow for simplified detection of the attachment piece by the towing spacecraft.

Abstract: In some embodiments of the invention, methods and devices are provided that perturb a trajectory of a space-orbital object. For example, a spacecraft may be sent to a location near a space-orbital object orbiting the Earth. A net may be released from the spacecraft in a manner (e.g., with a given alignment, direction and velocity) that results in the net contacting and/or entangling with the object. This contact or entanglement may alter a velocity of the space-orbital object and thereby may alter its orbital path. In some instances, the net's velocity is sufficient to experience increase drag by the Earth's atmosphere, relative to the drag it would have otherwise experienced if the net did not contact the object.

Abstract: A processing and delivery system is in space around a celestial body having a magnetic field. The system includes at least one facility having supplies and configured for in-space recycling and manufacturing to produce processed objects utilizing space debris objects and the supplies. The system includes at least one space vehicle configured to deliver the space debris objects from their orbits to the at least one facility using electrodynamic propulsion. The system includes at least one space vehicle configured to deliver new supplies to the at least one facility from other orbits using electrodynamic propulsion. The system includes at least one space vehicle configured to deliver the processed objects from the at least one facility to their destination orbits using electrodynamic propulsion.

Abstract: A system and method for propelling a carriage on a cable of a space elevator. The space elevator system includes a cable anchored to a terrestrial body on a first end and a counterweight on an opposing second end and a carriage riding along the cable. The system also includes an oscillator for generating a mechanical wave upon the cable. Mechanical energy created by the generated mechanical wave is converted into power to propel the carriage upon the cable. The oscillator may include a pair of opposing pistons contacting the cable on opposite sides of the cable or an electromagnetic driver powered by electromagnets located on opposite sides of the cable.

Abstract: The effective area of an electric sail depends on the voltage applied to tethers. The use of higher voltages is made possible by moving voltage multipliers to tethers, perhaps 100 meters out from the body of the spacecraft.

Abstract: An apparatus and method are disclosed for dual Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter (ESPA) port small satellite designs. The apparatus and method provide payload volume for larger satellites. In one or more embodiments, the apparatus and method include a plurality of small satellite components, a payload adaptor ring, and at least one pivoting hinge system. In at least one embodiment, the plurality of small satellite components includes at least one payload, one bus, and/or one solar panel. The small satellite components are mounted on the payload adaptor ring. At least one pivoting hinge system connects together at least two of the small satellite components. Upon deployment of the small satellite components from the payload adaptor ring, at least one pivoting hinge system combines together at least two small satellite components, thereby creating at least one single larger satellite.

Abstract: An apparatus for orbital change of a satellite incorporates a capture mechanism for space debris and a tether connecting the capture mechanism to a satellite. The tether is extendable to position the capture mechanism relative to the space debris. A controller is employed for timed release of the space debris by the capture mechanism for orbital change by the satellite.

Abstract: A towing apparatus for a spacecraft when in orbit is provided. The towing apparatus includes a cable, the first end of which is intended to be permanently connected to a spacecraft that must potentially be towed, and the second end of which is provided to be at least temporarily connected to a towing spacecraft for the purpose of towing. An attachment piece is disposed on the second end of the cable for mechanical attachment to a complementary attachment piece of the towing spacecraft, and a positioning aid is disposed to allow for simplified detection of the attachment piece by the towing spacecraft.

Abstract: An end effector operatively coupled to an extendable tensile element extended from a first vehicle engages a primary receptacle of a second vehicle. The first and second vehicles are drawn together by retracting the extendable tensile element into the first vehicle until contact therebetween, after which roll axes of the first and second vehicles become substantially aligned responsive to a further retraction of the extendable tensile element into the first vehicle and a resulting tension in the extendable tensile element. At least one alignment post of at least one of the first and second vehicles engages with at least one surface of at least one corresponding secondary receptacle so as to at least substantially align the first and second vehicles in roll responsive to the tension in the extendable tensile element.

Abstract: A system and method for the initial deployment of a space elevator using a tether, doubly spooled from each end, an inertial mass, beacon satellite and positional thrusters, whereby tether is de-spooled from geosynchronous Earth orbit altitude, using gravity and centripetal force gradient, and timed such that when the tethers fully de-spool or near the point of being fully de-spooled, are released and the free ends, one left to fall inwards to Earth anchor point, and the other left to fall outwards to tether end ballast support point, result in an Earth anchored self supporting tension structure.

Abstract: A debris removal management system and a method of removing space debris. In one embodiment, the system includes: (1) a frame, (2) a plurality of net sections coupled to the frame and (3) a plurality of microvehicles coupled to the plurality of net sections and configured to be ejected relative to the frame to deploy the plurality of net sections, the plurality of net sections cooperating to form a net configured to capture space debris.

Abstract: A surveying device and a method for surveying a satellite and its environs is disclosed. The surveying device comprises a docking platform having an interface for physically coupling to a surface of a bus of a spacecraft and an imaging module, releasably coupleable to the docking platform via a semi-rigid tether axially extendable and retractable by command, the imaging module having an imaging sensor for collecting image data, the imaging sensor communicatively coupled with the docking platform via the tether.

Abstract: A surveying device and a method for surveying a satellite and its environs is disclosed. The surveying device comprises a docking platform having an interface for physically coupling to a surface of a bus of a spacecraft and an imaging module, releasably coupleable to the docking platform via a semi-rigid tether axially extendable and retractable by command, the imaging module having an imaging sensor for collecting image data, the imaging sensor communicatively coupled with the docking platform via the tether.

Abstract: An apparatus for orbital change of a satellite incorporates a capture mechanism for space debris and a tether connecting the capture mechanism to a satellite. The tether is extendable to position the capture mechanism relative to the space debris. A controller is employed for timed release of the space debris by the capture mechanism for orbital change by the satellite.

Abstract: Methods and systems for providing space tethers for limiting the dynamic response of structures are disclosed. In one embodiment, a method for limiting the dynamic response of a structure having a base member and a substructure projecting outwardly from the base member includes coupling a first end of an elongated flexible tether to the substructure at a first location spaced apart from the base member; and coupling a second end of the elongated flexible tether to the base member at a second location spaced apart from the substructure, the tether being configured to be in a non-taut configuration when the substructure moves within a design volume with respect to the base member, the tether being further configured to be in a taut position when the substructure displaces to a limit of the design volume.

Abstract: Super strong, super long tensile structures, connected to the anchor(s) on the Moon, ‘suspend’ in the Earth's atmosphere assemblies of wind energy catching devices (like turbines) positioned about 10-20 kilometers above the Earth's surface. The wind is actually an airflow generated by the Earth's rotation. The caught energy is converted to electricity and transmitted to Earth. A flat keel, attached to each assembly of turbines, stabilizes the assembly in the direction of the wind. The entire apparatus is stationary relative to the Moon and rotates around the Earth together with the Moon.

Abstract: A system includes a gravity gradient stabilized space tether. The gravity gradient stabilized space tether includes a tether body having an upper end and a lower end. The gravity gradient stabilized space tether also includes an upper base station located at the upper end of the tether body and a lower base station located at the lower end of the tether body. The gravity gradient stabilized space tether further includes a device coupled to the lower base station. The device can be lowered to a distance below the lower base station to a rendezvous point that is proximate to an orbital path of a sub-orbital vehicle.

Abstract: A transportation node that orbits a celestial body includes a truss having two ends with least at one end of the truss having at least one coupling tether cable with a tether tip at individual ends. The truss, while orbiting the celestial body, rotates around its center of mass in a direction to control the tether tip in relation to a surface of the celestial body and to cancel a relative velocity between the tether tip and the surface for transferring a payload attached to the tether tip to and from the surface. A method of transferring payload to and from a celestial body includes reeling in/out from an orbiting transportation node a coupling tether cable with a tether tip configured to attach to the payload.

Abstract: A system and method for the initial deployment of a space elevator using a tether, doubly spooled from each end, an inertial mass, beacon satellite and positional thrusters, whereby tether is de-spooled from geosynchronous Earth orbit altitude, using gravity and centripetal force gradient, and timed such that when the tethers fully de-spool or near the point of being fully de-spooled, are released and the free ends, one left to fall inwards to Earth anchor point, and the other left to fall outwards to tether end ballast support point, result in an Earth anchored self supporting tension structure.

Abstract: A spacecraft propulsion system includes a plurality of wires (102) or other electrically conductive elongated members deployed from a main body (101) into respective radial directions. An electric potential generator (605) generates an electric potential on board the main body (101). The electric coupling between the electric potential generator (605) and the elongated members is controlled (604) so that all or some of the elongated members (102) assume a high positive potential. An auxiliary propulsion system (203) rotates the main body around a rotational axis (502) that is perpendicular to the radial directions, thus creating a centrifugal supporting force to the elongated members.

Abstract: The invention concerns an observation satellite (1) which is intended to be placed in orbit around a celestial body (2), and which comprises a reflecting device (5), a receiving device (6), a linking mechanical system (19), the whole forming a capture system (3) which is suitable to be able to orient the capture system (3) by gravity gradient in an aiming position in which the electromagnetic radiation corresponding to the information to be captured is received. The invention extends to an observation method and a fleet of such satellites (1).

Abstract: A transportation node system orbits a celestial body. The node system includes a truss having two ends, the truss rotating around its center of mass while orbiting the celestial body. The truss stores payloads. The node system also includes tether tips, each attached to one end of the truss via a tether so that each tether tip can extend from the truss and retract to the truss for transfer of payloads. The tether runs through the length of the truss and connects to each tether tip, each tether tip being capable of engaging payloads. The node further includes at least one tether cable reel that reels in and reels out the tether so the tether tips can extend from and retract to the truss.

Abstract: The invention is a system and method for propellantless, ultrahigh precision satellite formation flying based on ultrahigh precision intracavity laser thrusters and tethers with an intersatellite distance accuracy of nanometers at maximum estimated distances of tens of kilometers. The repelling force of the intracavity laser thruster and the attracting force of tether tension between satellites form the basic forces to stabilize matrix structures of satellites. Users of the present invention can also use the laser thruster for ultrahigh precision laser interferometric metrology, resulting in simplification and payload weight reduction in integrating the thruster system and the metrology system.

Abstract: Methods and systems for providing space tethers for limiting the dynamic response of structures are disclosed. In one embodiment, a method for limiting the dynamic response of a structure having a base member and a substructure projecting outwardly from the base member includes coupling a first end of an elongated flexible tether to the substructure at a first location spaced apart from the base member; and coupling a second end of the elongated flexible tether to the base member at a second location spaced apart from the substructure, the tether being configured to be in a non-taut configuration when the substructure moves within a design volume with respect to the base member, the tether being further configured to be in a taut position when the substructure displaces to a limit of the design volume.

Abstract: Methods and an apparatus for a lifeboat of a space station in orbit to be docked with and used in combination with a separately launched logistics module having an upper stage propulsion capability as a space craft for human pilots and passengers to be flown to orbits and trajectories in deep space beyond low Earth orbit including the Moon, at the lowest practical cost.

Abstract: A space transport system for transporting payloads between points on the ground, in the air, and in outer space, includes a tether wheels able to accept payload from the ground or a low, slow position and transport it at high velocity to either another low, slow location on the same planet, or to a high speed space trajectory.

Abstract: A remotely controlled apparatus for grasping an object such as a satellite in space includes a free-flying grasper unit connected by a selectively extendable cable to an orbital platform. The orbital platform and the grasper unit are preferably each independently propelled by respective propulsion systems including multi-axis maneuvering nozzles respectively provided on the orbital platform and on the grasper unit. The grasper unit preferably includes a grasper unit body and a grasper-arm mechanism having a controllable grasping claw articulately mounted on the end of a controllable telescoping arm that extends from the grasper unit body. The grasper unit preferably further includes a camera and a distance measuring sensor to provide visual and distance feedback data for assisting the remotely controlled maneuvering of the grasper unit and actuation of the grasper-arm mechanism.

Abstract: Mechanism for passively deploying expendable space tethers on orbit, by means of an initial separation impulse only, provided by a simple spring system that is part of the mechanism itself. The passive deployment of the space tether and a tethered end-mass is provided by the particular mechanism devised, having very low deployment friction and resistance. Tether deployment brake towards the final part of deployment is produced by a daisy-like brake, stored within the winding of the fixed tether spool so that it is automatically deployed (opened) and starts its deployment braking or resistance function from a planned point of the tether deployment in space.

Abstract: Capture devices are mounted on a space platform such as a spacecraft or utility satellite. Each capture device includes a folded capture net stored in a housing, guide weights connected to the net and received in spring-loaded ejection tubes oriented at an acute angle relative to the axis of the housing around the perimeter thereof, and a spring-loaded releasable cover that is connected to the net, covers the net in the housing, and holds the weights in the ejection tubes. When the cover is released, it is spring-ejected from the housing while pulling out and unfolding the net, and the weights are spring-ejected out of the ejection tubes while spreading out the net. After the net wraps around a free-flying target object in space, net closure mechanisms reel-in a net pursing line to close the net, which is connected to the space platform by a tether line on a winch.

Abstract: A tether system for providing thrust to or power subsystems of an artificial satellite in a low earth orbit. The tether has three main sections, an insulated section connected to the satellite, a conducting section connected to the insulating section for drawing in and releasing electrons from the space plasma and a non-conducting section for providing a tension to the other sections of the tether. An oxygen resistant coating is applied to the bare wire of the conducting section as well as the insulated wires of the insulated section that prevents breakdown during tether operations in the space plasma. The insulated and bare wire sections also surround a high tensile flexible polymer core to prevent any debris from breaking the tether during use.

Abstract: A system and method for a Space Elevator using a transport tether shaped into double catenary with one catenary below synchronous orbit altitude and the second catenary above synchronous orbit altitude and while also forming a harmonic oscillator using a combination of gravitational and centripetal forces with the zero crossing of the harmonic oscillator at an altitude of approximately one half synchronous orbit altitude of attached elevator.