Abstract: An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.

Abstract: An in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.

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 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 in-space spacecraft servicing system (10) includes a servicing spacecraft (22) and a propellant module (24). The servicing spacecraft includes a client servicing system (136), as well as navigation avionics (108) for independent flight operation and a servicing propellant tank (170). The propellant module moves the servicing module from an upper stage drop off location and releases it in proximity to a client spacecraft (16) for a servicing mission. It has a propellant tank (172) with capacity for multiple missions and is used to refill the servicing spacecraft's propellant tanks between missions. Either or both the servicing spacecraft and the propellant module may have navigation avionics. The servicing spacecraft also has a universal docking adaptor (70) for different client spacecraft, and can convert a client spacecraft from non-cooperative to cooperative.

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 cryogenic propellant depot and sunshield are provided for operation in earth orbit to fuel or refuel other space vehicles. The sunshield is deployed to effectively mitigate solar radiation emanating from the earth and the sun thereby providing a long term storage solution for cryogenic fluids prone to boil-off. The depot has supporting subsystems to include station keeping equipment and communication equipment so that the depot can be independently controlled. Inflatable booms are used to deploy the sunshield in a desired pattern around the depot.

Abstract: A cryogenic propellant depot and sunshield are provided for operation in earth orbit to fuel or refuel other space vehicles. The sunshield is deployed to effectively mitigate solar radiation emanating from the earth and the sun thereby providing a long term storage solution for cryogenic fluids prone to boil-off. The depot has supporting subsystems to include station keeping equipment and communication equipment so that the depot can be independently controlled. Inflatable booms are used to deploy the sunshield in a desired pattern around the depot.

Abstract: Disclosed is a Host Transfer Vehicle methods and computer-readable medium for enabling the capture and berthing of passive cargo containers in space with an orbiting system, such as the International Space Station. A method embodiment positions a Host Transfer Vehicle (HTV) in proximity to an orbiting system, captures a passive cargo container launched from a ground by a grappling arm of the HTV, couples the passive cargo container to the HTV to form an HTV/cargo container stack, propels the HTV/cargo container stack within proximity of an orbiting system, and through the use of a grappling arm of the orbiting system berths the HTV/cargo container stack via a coupling structure on the cargo container to the orbiting system. The cargo container can then receive cargo from the orbiting system and either return to the ground or the cargo container can be burned up in the atmosphere.

Abstract: An In Orbit Transportation & Recovery System (IOSTAR™) (10) is disclosed. 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.

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 method of insuring against launch failure is provided to reduce the business risk to the satellite owner and insurance underwriters against satellite launch failure. The launch insurance includes provision for guaranteeing a rapid response recovery mission, preferably at no cost, in the event that a satellite suffers a boost failure during launch resulting in a fully-functional satellite being launched to an unintended inoperable orbit. Preferably, the launch insurance also provides for additional insurance against failure of the recovery mission to provide compensation to the satellite owner in the event that the recovery mission is also unsuccessful.

Abstract: A propellant depot (40, 150) includes a utility box (42, 42?) that has space flight equipment. A propellant cartridge adaptor (95) is coupled to the utility box (42, 42?) and to an exchangeable propellant cartridge system (41). The propellant depot (40, 150) also includes a docking adaptor (44) for coupling to an approaching spacecraft (24). A controller (66) controls the transfer of propellant from within the exchangeable propellant cartridge system (41) to the spacecraft (24). A method of providing propellant to a spacecraft in space includes launching an orbital propellant depot (40, 150) into space. The spacecraft is docked to the orbital propellant depot (40, 150) in space. Propellant is transferred to the spacecraft. The spacecraft is separated from the orbital propellant depot (40, 150).

Abstract: A device provided on a space shuttle for docking to satellites, in particular communication or navigation satellites, which device comprises a linkage with a cone at its distal end—relative to the space shuttle—and a spreader mechanism, actuatable from the space shuttle, with spreader elements in the form of lever spreaders having their proximal ends—relative to the space shuttle—provided with noses protruding inward towards the linkage. At least two lever spreaders of the device are pivotally arranged at a retaining part concentric to the linkage; the curvature at the distal end of each lever spreader is adapted to the curvature of the nozzle neck of the jet nozzle of a satellite engine. A rotatable sleeve is provided below the retaining part, which sleeve is concentric to the linkage.

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: 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: 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 pincer system is comprised of an array of pincers. Each pincer includes an inner disk having legs that are pushed downwards onto a pliable material to cause protuberances, while an outer disk is rotated to simultaneously squeeze the extruded material between its legs and those of the stationary inner disk. Tracks provide for slideable movement of the individual pincers. The system, carrying an attached micro-satellite, translates across a pliable material covering a spacecraft by coordinating the movement of the pincers with their grasping of the pliable material. This abstract is provided to comply with the rules requiring an abstract, and is intended to allow a searcher or other reader to quickly ascertain the subject matter of the technical disclosure. It is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims.

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: 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.

Abstract: A system for transportation and storage of cargo in space includes one or more platforms. The platforms are operable to hold multiple removable propellant tanks and rendezvous with one or more other platforms in space. The platforms also include one or more thruster systems and positioners. Each positioner has an effector operable to grip a band disposed around each propellant tank. Each positioner is operable to facilitate the transfer of the multiple removable propellant tanks between platforms during the rendezvous.