Abstract: A mechanism uses a magnetic field to dock a satellite to a host vehicle. A docking component of the mechanism residing on the host vehicle has a magnet that is used to induce a coupled magnetic field with a docking component of the mechanism residing on the satellite. An alignment guide axially aligns the docking component of the satellite with the docking component of the host device dependent on the coupled magnetic field. Rotational alignment guides are used to rotationally align the docking component of the satellite with the docking component of the host device. A ball-lock mechanism is used to mechanically secure the docking component of the host vehicle and the docking component of the satellite.

Abstract: A system and method for refueling unmanned aerial vehicles. The system is adapted to refuel a first unmanned aerial vehicle from a second unmanned aerial vehicle and includes an arrangement for flying the first and second vehicles to proximity within a predetermined range and for connecting an umbilical from the second vehicle to the first vehicle in flight. In the illustrative embodiment, the arrangement for connecting includes a targeting system for electromagnetically detecting a refueling receptacle on the first vehicle. The targeting system includes a first coil around a refueling receptacle on the first vehicle. A seeker is disposed at a first end of said umbilical on the second vehicle. The seeker includes three detector coils adapted to detect a magnetic signal from the first coil around the receptacle on the first vehicle. The coils are mounted such that the detector coils point in different directions.

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: Systems and methods to deliver crew, cargo and other logistics services to space platforms. In one embodiment, a rendezvous and docking vehicle (RDV) comprises two docking mechanisms coupled to the RDV body. A pressurizable passageway connects the docking mechanisms. In one embodiment, the two docking mechanisms are different. An alternative embodiment comprises docking mechanisms which are the same. Also included is a flight control system. The flight control system may vary between embodiments, being autonomous, automated, or remotely controlled (e.g., remote pilot). One embodiment can also include a docking control system in the RDV. A propulsion system is coupled to the RDV in some embodiments, and the RDV may be augmented by a mated spacecraft's propulsion system in other embodiments. The mated spacecraft's propulsion system may even be under the control of the RDV.

Abstract: The method for lightening the weight of fuel stowed onboard during an interplanetary mission is characterized in that it consists: in launching (10a) a first orbiter spacecraft (1) from the Earth on a first interplanetary trajectory (31, 33) towards a target planet to be explored, in launching (10b) a second orbiter spacecraft (2) from the Earth on a second interplanetary trajectory (32, 34) towards a rendezvous spot (38), the second interplanetary trajectory not comprising any phase of placing in orbit around the target planet, in recovering a load to be transported and in loading it onto the first orbiter spacecraft (1), in returning the first orbiter spacecraft (1) and the load from the target planet to the rendezvous spot (38), in effecting a docking (14) of the two orbiter spacecraft (1, 2), in returning at least the second orbiter spacecraft (2) and the load, from the rendezvous spot (38) to a terrestrial orbit (41).

Abstract: Systems and methods for releasing a spacecraft payload at a substantially constant velocity are disclosed. A linear actuator is used that includes a spring loaded and fluid filled chamber. The spring drives against a piston within the chamber that includes a control orifice that restricts the fluid flowing from one side of the piston to the other and results in a substantially constant damped motion of the piston. The piston drives a rod from the chamber that is attached to a capture device that holds a flange of the spacecraft payload. The capture device moves along a linear guide toward an open end. Spring loaded latches are held in a closed position by the side walls of the guide as the capture device moves. The latches release the flange as exit the open end of the guide.

Abstract: A capture device for capturing at least one free-flying body in space, to be installed onboard a space apparatus. The capture device comprises an inflatable primary body, a capture volume, which is at least partially defined by the inflatable primary body, and an inlet mouth cooperating with the capture volume. In particular, the free-flying body to be captured may pass through the inlet mouth, so that the capture volume may receive the body.

Abstract: A preferred In Orbit Transportation & Recovery System (IOSTAR™) (10) includes a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.

Abstract: A docking target indicator for a docking device is provided. The docking target indicator comprises a base layer, having a rear surface and a front surface; wherein the front surface of the base layer is reflective; and a baffle structure is secured to the base layer.

Abstract: A preferred In Orbit Transportation & Recovery System (IOSTAR™) (10) includes a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.

Abstract: The present invention relates to a spacecraft (P) comprising a propulsion system (1) making it possible to exert a force of variable magnitude and orientation on the spacecraft, a control system designed to control the propulsion system in terms of magnitude and orientation so as to make the spacecraft approach a target around a planet, with the aid of a force which comprises at least one component (fx, fy, fz), in the rotating reference frame tied to the target, which depends substantially linearly on the corresponding coordinate (x, y, z) of the craft in this reference frame.

Abstract: An aerospace frame accommodates propellant tanks for facilitating propellant operations in space. The frame includes at least two plates for supporting the propellant tanks; at least one brace supporting the plates; and a cavity between two plates that accommodates a removable propellant tank.

Abstract: First and second releasably connectable portions of a docking system are moved together. A relatively central concave element of the second portion of the docking system contacts a corresponding relatively central mating convex element of the first portion of the docking system. A plurality of relatively distal coupling elements rigidly connected to one of the first and second portions of the docking system are inserted into a corresponding plurality of relatively distal sockets of the other of the first and second portions of the docking system. The plurality of relatively distal coupling elements are captured with a corresponding plurality of relatively distal latch mechanisms associated with the plurality of relatively distal sockets responsive to inserting the plurality of relatively distal coupling elements into the corresponding plurality of relatively distal sockets.

Abstract: A convex forward surface of a forward-biased probe head of a first portion of a docking system engages a central concave conical surface of a second portion of the docking system. A first linear actuator moves a flexible docking cable assembly relative to a support structure through bores therein and through the probe head. An aftward retraction of the docking cable assembly causes a linearly-actuated cam element thereof to rotate a rotary cam follower pivoted from the support structure, which engages an aft edge portion of the probe head, forcing the probe head forward. A plurality of distal coupling elements operatively coupled to the support structure around a central axis thereof engage with and become releasably captured by a corresponding socket and associated capture mechanism of a mating second portion of the docking system, and rigidized when the probe head is forced against the central concave conical surface.

Abstract: A capture mechanism provides for receiving a necked coupling element within a socket, providing for the necked coupling element to slide therewith, biasing a latch lever in an open position so as to provide for receiving the necked coupling element within the socket adjacent to the latch lever, rotating the latch lever with the necked coupling element from the open position to a closed position as the necked coupling element is slid within the socket towards a bottom of the socket, biasing a latch lock against the latch lever, engaging the latch lock with the latch lever when the latch lever is in the closed position so as to provide for latching the latch lever in the closed position and capturing the necked coupling element within the socket, and providing for unlatching the latch lever by releasing the latch lock from engagement with the latch lever.

Abstract: An androgynous mating system for mating two exoatmospheric space modules comprising a first mating assembly capable of mating with a second mating assembly; a second mating assembly structurally identical to said first mating assembly, said first mating assembly comprising; a load ring; a plurality of load cell subassemblies; a plurality of actuators; a base ring; a tunnel; a closed loop control system; one or more electromagnets; and one or more striker plates, wherein said one or more electomagnets on said second mating assembly are capable of mating with said one or more striker plates on said first mating assembly, and wherein said one or more striker plates is comprised of a plate of predetermined shape and a 5-DOF mechanism capable of maintaining predetermined contact requirements during said mating of said one or more electromagnets and said one or more striker plates.

Abstract: A reusable module is affixed atop a reusable orbital vehicle (OV). Various configurations of the reusable module have identical external dimensions in the region of attachment to the OV to permit interchangeability. Different configurations can accommodate a variety of missions of different type and duration. A variety of cargo modules of different configurations allow cargo to be uplifted into orbit. In one embodiment, the cargo module is an unpressurized cargo module in which the cargo is exposed to the environment of space during the unloading process. The cargo module may also be a pressurized cargo module. In an alternative embodiment, the cargo module may include both a pressurized cargo module and unpressurized cargo module.

Abstract: A space construction method and system transports construction materials, a propellant depot, solar electric propulsion (SEP) vehicles, and robotic equipment from Earth into a lower-Earth orbit. The SEP vehicles are used to transport payload between the lower-Earth orbit and a construction area in higher-Earth orbit, such as GEO. The robotic equipment transfers materials between various vehicles and assembles the transported construction materials in the higher-Earth orbit. A tug SEP vehicle transports heavier construction materials from the propellant depot in lower-Earth orbit to the construction area in higher-Earth orbit. A propulsion stage SEP vehicles transport lighter construction materials from the propellant depot to the construction area.

Abstract: This invention is a method and supporting apparatus for autonomously capturing, servicing and de-orbiting a free-flying spacecraft, such as a satellite, using robotics. The capture of the spacecraft includes the steps of optically seeking and ranging the satellite using LIDAR, and matching tumble rates, rendezvousing and berthing with the satellite. Servicing of the spacecraft may be done using supervised autonomy, which is allowing a robot to execute a sequence of instructions without intervention from a remote human-occupied location. These instructions may be packaged at the remote station in a script and uplinked to the robot for execution upon remote command giving authority to proceed. Alternately, the instructions may be generated by Artificial Intelligence (AI) logic onboard the robot. In either case, the remote operator maintains the ability to abort an instruction or script at any time as well as the ability to intervene using manual override to teleoperate the robot.

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: A spacecraft docking system configured to permit the docking of a spacecraft to a target object is provided. The docking system includes a grapple and docking interface, which is mounted on the target object. The grapple includes a body coupled to the spacecraft and at least one latching wing coupled to the body. The at least one latching wing is movable between a retracted position and an extended position, and configured to move into the extended position and latch onto the docking interface when the grapple is inserted therein.

Abstract: The present invention provides a method, system and apparatus for robotic refueling of satellites. The system may include a dedicated refueling satellite launched directly from either earth, or alternatively it could be launched from another larger mother spacecraft or space station in which the refueling satellite is ferried into space in the case of the larger space craft or it may be stored on the space station until needed from which it can be launched. The system includes a robotic arm, suitable tools which can be affixed to the end effector of the robotic arm required for accessing, opening and closing the fuel fill valve on the satellite being serviced, storage and retrieval stations on a tool caddy on which the tools and various fuel fill valve caps are stored. The system is under teleoperation by a remotely located operator, for example located on earth, in the mother station or in the space station.

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: In a space platform supply system, a canister containing supply for a space platform is launched into orbit using a launch vehicle. An intermediate space vehicle rendezvous and docks with the canister while the attached launch vehicle provides the necessary orbit maintenance and stabilization to enable the docking. After docking, the intermediate space vehicle detaches the canister from the launch vehicle element or the launch vehicle element may initiate detachment from the intermediate space vehicle/canister. In either event, the intermediate space vehicle then can provide propulsion and attitude control to allow the canister to be transported to and docked with the space platform being supplied, thus eliminating the need for the canister to include propulsion and attitude control of its own.

Abstract: A docking target indicator for a docking device is provided. The docking target indicator comprises a base layer, having a rear surface and a front surface; wherein the front surface of the base layer is reflective; and a baffle structure is secured to the base layer.

Abstract: Methods and systems for assembling spacecraft in space are provided. A modular spacecraft comprises a plurality of spacecraft modules, wherein each spacecraft module includes one or more of bonding posts and receiving plates mounted to an exterior surface each spacecraft module, wherein the one or more bonding posts and receiving plates are adapted to form one or more of, an electro-weld bond and an adhesive bond, with the one or more receiving plates.

Abstract: Apparatus and methods for performing satellite proximity operations such as inspection, recovery and life extension of a target satellite through operation of a “Satellite Inspection Recovery and Extension” (“SIRE”) spacecraft which can be operated in the following modes (teleoperated, automatic, and autonomous). The SIRE concept further consists of those methods and techniques used to perform certain (on-orbit) operations including, but not limited to, the inspection, servicing, recovery, and lifetime extension of satellites, spacecraft, space systems, space platforms, and other vehicles and objects in space, collectively defined as “target satellites”. The three basic types of SIRE proximity missions are defined as “Lifetime Extension”, “Recovery”, and “Utility”. A remote cockpit system is provided to permit human control of the SIRE spacecraft during proximity operations.

Abstract: A platform for storage and transfer of propellant tanks in space includes frames configured to releasably support plural propellant tanks in storage positions, and transfer mechanisms configured to transfer propellant tanks to and from the storage positions. The platform includes a central structure to which the plural frames are connected at predetermined spaced intervals. The transfer mechanisms include extendable telescoping arms mounted to the central structure. The arms have end effectors configured to grip bands on propellant tanks. Two platforms may be positioned adjacent each other for the transfer of propellant tanks therebetween.

Abstract: An In Orbit Transportation & Recovery System (IOSTAR™) (10) One preferred embodiment of the present invention comprises a space tug powered by a nuclear reactor (19). The IOSTAR™ includes a collapsible boom (11) connected at one end to a propellant tank (13) which stores fuel for an electric propulsion system (12). This end of the boom (11) is equipped with docking hardware (14) that is able to grasp and hold a satellite (15) and as a means to refill the tank (13). Radiator panels (16) mounted on the boom (11) dissipate heat from the reactor (19). A radiation shield (20) is situated next to the reactor (19) to protect the satellite payload (15) at the far end of the boom (11). The IOSTAR™ (10) will be capable of accomplishing rendezvous and docking maneuvers which will enable it to move spacecraft between a low Earth parking orbit and positions in higher orbits or to other locations in our Solar System.