| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244172400 | Rendezvous or docking | 26 |
| 20090001221 | SPACECRAFT GRAPPLE ASSEMBLY AND DOCKING SYSTEM EMPLOYING THE SAME - 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. | 01-01-2009 |
| 20090101757 | Architecture and method of constructing a Geosynchronous Earth Orbit platform using solar electric propulsion - 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. The tug is also transports the fuel-depleted propulsion stages from higher-Earth orbit back to the propellant depot in lower-Earth orbit, where both the tug and the propellant stages are refueled and reloaded for another trip to the construction area in higher-Earth orbit. As additional supplies they are transported from Earth to the propellant depot in lower-Earth orbit. | 04-23-2009 |
| 20090146011 | DOCKING SYSTEM - 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. | 06-11-2009 |
| 20090173832 | DOCKING SYSTEM - 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. | 07-09-2009 |
| 20090173833 | DOCKING SYSTEM - 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. | 07-09-2009 |
| 20090294595 | INFLATABLE CAPTURE DEVICE - 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. | 12-03-2009 |
| 20100301169 | Space Shuttle With a Device for Docking to a Satellite - In a space shuttle with a device for docking to a satellite, especially a communication or navigation satellite, at least two spreading elements in the form of lever spreaders ( | 12-02-2010 |
| 20120228435 | METHODS AND APPARATUS FOR A GRAPPLING DEVICE - A device for grappling orbital debris includes a chain of interconnected links, each having a corresponding contact sensor (for sensing contact with the orbital debris), and each connected to a subsequent link by an actuator (e.g., a worm drive assembly or the like). The actuators are configured to sequentially cause rotation of each link in the chain until the corresponding contact sensor indicates that the link has made contact with the orbital debris. Subsequently, the next link in the chain is rotated, and so on, until the chain of interconnected links substantially surrounds at least a portion of the orbital debris. | 09-13-2012 |
| 20130126678 | SPACE VEHICLE RENDEZVOUS - A method and apparatus provide for a basket of passively-safe thruster-burn positions within a context of rendezvous between a space-vehicle and a resident-space-object while in orbit around the Earth, for example. The basket of positions is defined by an intersection of a plurality of half-spaces determined based on a keep-out-zone associated with the resident-space-object, and a nominal position of the space-vehicle. The plurality of half-spaces defines a corresponding plurality of half-space boundary conditions within which the basket of positions is disposed. When a position of the space-vehicle is within the basket of positions at a time of a scheduled thruster-burn, then the scheduled thruster-burn is ensured to result in passive-safety. | 05-23-2013 |
| 20130140403 | Direct to facility capture and release - A method for delivering a payload to a space facility is provided. The method includes detecting the relative position and velocity of a launch vehicle stage, the launch vehicle stage including the payload and one or more thrusters. The method also includes providing guidance information to the launch vehicle stage. The launch vehicle stage does not include a relative navigation system. In response to receiving the guidance information, the method further includes activating one or more thrusters corresponding to the guidance information, and guiding a capture head of a boom into capture proximity to the payload. One end of the boom is coupled to the space facility and the other end of the boom is coupled to the capture head. The method also includes capturing the payload, removing any residual relative velocity of the payload relative to the space facility, and moving the captured payload to the space facility. | 06-06-2013 |
| 20140306066 | Methods of Delivering Items in Space - This claim is for methods of delivering items in space which allow for increases in the efficiency of mass based propulsion systems. This claim is based upon existing knowledge that professionals in the field of rocketry should understand with no need of reference materials. | 10-16-2014 |
| 20150008290 | Docking node transporter tug - A docking node transporter tug is disclosed. The tug can dock with various spacecraft to allow access by people between the spacecraft. Further, the tug may dock with other specialty tugs to form a custom system. | 01-08-2015 |
| 20150053823 | Spacecraft capture tug - A spacecraft capture tug is disclosed. The tug can capture objects in space, including spacecraft and satellites, using an engagement system and provide propulsion for the object to a point of servicing, repair, or other desired operations. Further, the tug may dock with other specialty tugs to form a custom transport system. | 02-26-2015 |
| 20160130020 | DEVICE FOR SENSING A SPACE OBJECT, INCLUDING A PRESSURE ELEMENT AND AT LEAST TWO RESEALABLE ELEMENTS ON THE SPACE OBJECT - A device for capturing a space object, the device comprising a pressure element configured to come into direct mechanical contact with the space object to be captured. The device comprises at least two reclosable elements movable between an open position for capturing the space object and a closed position for retaining the space object. The device also comprises an apparatus to mechanically transmit movement from the pressure element to each reclosable element, the mechanical transmission apparatus being configured to entrain each reclosable element in displacement between the open position and the closed position by pressure of the space object on the pressure element. | 05-12-2016 |
| 244172500 | Including satellite servicing | 12 |
| 20090146012 | Space shuttle with a device for docking to a satellite - 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. A distal annular portion of the sleeve is formed with respective alternating engaging positions of different heights, and wherein, from the proximal end portion of the sleeve, two pins project that are guided by associated obliquely oriented slide faces in a stationary housing, the pins being provided for setting the adjustment travel of the linkage. | 06-11-2009 |
| 20090242704 | IN ORBIT SPACE TRANSPORTATION & RECOVERY SYSTEM - An In Orbit Transportation & Recovery System (IOSTAR™) ( | 10-01-2009 |
| 20100038491 | SYSTEM AND METHOD FOR TRANSFERRING CARGO CONTAINERS IN SPACE - 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. | 02-18-2010 |
| 20110031352 | Two Part Spacecraft Servicing Vehicle System with Adaptors, Tools, and Attachment Mechanisms - An in-space spacecraft servicing system ( | 02-10-2011 |
| 20110042522 | ROBUST CAPACITIVE DISTANCE SENSOR - The invention refers to a docking device for the docking of a maintenance device to a nozzle ( | 02-24-2011 |
| 20120080563 | ROBOTIC SATELLITE REFUELING TOOL - A tool for fuelling an unprepared or partially prepared client satellite required for accessing, opening and closing a 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 tool includes interchangeable socket modules, a support frame, a socket module holder mechanism, a socket drive mechanism, a clamping mechanism to secure the tool to a reaction area on the fuel fill valve and oxidizer fill valve, and a valve actuation mechanism. The interchangeable socket modules include a first module for removing and replacing the access valve cap, a second module for coupling the fuel fill line to the fuel tank, a third module for engaging the access valve cap on the oxidizer fill valve, and a fourth module for coupling the oxidizer fill line to the oxidizer tank. | 04-05-2012 |
| 20120325972 | ROBOTIC SATELLITE REFUELLING TOOL - A tool mounted on a servicer satellite for fuelling an unprepared or partially prepared client satellite. The tool includes a robotic arm mounted on the servicer satellite and a valve tool configured to be releasibly gripped by the robotic arm. The valve tool includes a housing with a support frame and a wrench mechanism mounted on the support frame. The wrench mechanism is configured for removing and replacing the first access valve cap on the first fill-drain valve and coupling a first propellant fill line to the first propellant tank optionally removing and replacing the second access valve cap on the second fill-drain valve on the second propellant tank and coupling a second propellant fill line to the second propellant tank, and actuating the valve actuation nut on the first fill-drain valve, and optionally actuating the valve actuation nut on the second fill-drain valve. | 12-27-2012 |
| 20130119204 | PROPELLANT TRANSFER SYSTEM AND METHOD FOR RESUPPLY OF PROPELLANT TO ON-ORBIT SPACECRAFT - Herein is disclosed a propellant transfer system and method for refueling on-orbit spacecraft. The system and method are configured to allow for resupply of spacecraft configured to be fueled by either a bipropellant (oxidizer and fuel) or a monopropellant (typically hydrazine). The system and method are particularly suited for resupply of satellites not originally prepared for refueling as well but the system may also be used for as satellites specifically designed for refueling. | 05-16-2013 |
| 20130153710 | Tool for accessing satellite fill/drain valves during propellant resupply - Herein is disclosed a tool, system and method for refueling on-orbit spacecraft. The tool and system are configured to allow for resupply of spacecraft configured to be propelled by either a bipropellant (oxidizer and fuel) or a monopropellant (typically hydrazine). The refueling tool is particularly suited for resupply of satellites not originally prepared for refueling but the system may also be used for satellites specifically designed for refueling. | 06-20-2013 |
| 20150314893 | SPACECRAFT CAPTURE MECHANISM - 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. | 11-05-2015 |
| 20160039543 | SYSTEM AND TOOL FOR ACCESSING SATELLITE FILL/DRAIN VALVES DURING PROPELLANT RESUPPLY - Herein is disclosed a tool, system and method for refueling on-orbit spacecraft. The tool and system are configured to allow for resupply of spacecraft configured to be propelled by either a bipropellant (oxidizer and fuel) or a monopropellant (typically hydrazine). The refueling tool is particularly suited for resupply of satellites not originally prepared for refueling but the system may also be used for satellites specifically designed for refueling. | 02-11-2016 |
| 20160039544 | SYSTEM AND TOOL FOR ACCESSING SATELLITE FILL/DRAIN VALVES DURING PROPELLANT RESUPPLY - Herein is disclosed a tool, system and method for refueling on-orbit spacecraft. The tool and system are configured to allow for resupply of spacecraft configured to be propelled by either a bipropellant (oxidizer and fuel) or a monopropellant (typically hydrazine). The refueling tool is particularly suited for resupply of satellites not originally prepared for refueling but the system may also be used for satellites specifically designed for refueling. | 02-11-2016 |
