Abstract: An apparatus communication device (950) communicates with at least one of a parent satellite (310) and a child satellite (320). A control unit (110) generates a control command (51) to capture debris by sandwiching the debris between the parent satellite (310) and the child satellite (320) and carry out an active control operation during orbital descent on a flying object which is the parent satellite (310), the debris, and the child satellite (320) being connected together. Then, the control unit (110) transmits the control command (51) to at least one of the parent satellite (310) and the child satellite (320) via the apparatus communication device (950).

Abstract: The disclosure provides a configurable-mass rideshare dispenser for a rideshare adapter employable with a LV. In one example, the configurable-mass rideshare dispenser includes: (1) a modular chassis having a plurality of walls, wherein each of the plurality of walls includes multiple internal mounts operable to mount at multiple candidate locations a rideshare payload, its associated attachment/deployment mechanisms, signal processing circuitry, and at least one additional mass object, and (2) at least one door coupled to at least one of the plurality of walls, wherein the signal processing circuitry is operable to provide deployment sequencing that operates the at least one door.

Abstract: A reprovisionable spacecraft and reprovisioning subassemblies for mating with a reprovisionable spacecraft are both described. The reprovisionable spacecraft has one or more mechanical, thermal, data, and or electrical mating interfaces for attaching, powering, and communicating with a reprovisioning subassembly, which for one embodiment is a self-contained thruster unit. The self-contained thruster unit preferably comprises a fuel tank, control electronics, and a thruster assembly. Alternately, a reprovisioning subassembly can comprise a fuel tank and control electronics, a fuel tank, or a thruster. Also, a reprovisionable spacecraft may be carried into orbit without reprovisioning subassemblies attached, and then deployed after reprovisioning subassemblies have been attached to their respective mating interfaces. Reprovisioning utilizing a self-contained thruster unit or tank eliminates the large risk associated with refueling satellites in space.

Abstract: A device sized and shaped for insertion into a body comprising: at least one mechanical limb comprising: a support segment; a first flexible section extending from the support segment and terminating in a coupling section; and a second flexible section extending from the coupling section and terminating in a tool or a connector for a tool; wherein a long axis of one or more of the flexible sections is bendable in a single bending plane; wherein a long axis length of the first flexible section is at least double a maximum extent of the first flexible section perpendicular to a flexible section long axis; wherein a long axis length of the second flexible section is at least double a maximum extent of the second flexible section perpendicular to a flexible section long axis.

Abstract: A device sized and shaped for insertion into a body comprising: at least one mechanical limb comprising: a support segment; a first flexible section extending from the support segment and terminating in a coupling section; and a second flexible section extending from the coupling section and terminating in a tool or a connector for a tool; wherein a long axis of one or more of the flexible sections is bendable in a single bending plane; wherein a long axis length of the first flexible section is at least double a maximum extent of the first flexible section perpendicular to a flexible section long axis; wherein a long axis length of the second flexible section is at least double a maximum extent of the second flexible section perpendicular to a flexible section long axis.

Abstract: A method comprising determining, by a function, that a first satellite lacks processing or communication capabilities; and routing data traffic, by the function, from the first satellite to a second satellite, the second satellite having higher processing or communication capabilities than the first satellite. The processing and communication capabilities of the first and second satellite are directly related to their power availability, which is derived from solar energy means. Another method comprising determining, by a function, that a first satellite cannot provide computing or communication resources; migrating data, by the function, from the first satellite to a second satellite that can provide the computing or communication resources; computing the data, by the computing resources of the second satellite; and transmitting computed data, by the function, from the second satellite to the first satellite.

Abstract: A propulsion system for small artificial satellites comprises a plurality of engines (2) fixable to a frame (101) of a satellite (100); a control unit (3) connected functionally to the engines (2) for sending at least one activation signal (AS) for activating at least one engine (2); the system is selectively configurable at least between a first configuration in which at least one of the engines (2) is activated for correcting the orbit of the satellite (100) and a second configuration in which at least one of the engines (2) is activated for dispersing said satellite (100) relative to another adjacent satellite.

Abstract: A system for positioning a row of photovoltaic solar panels (1) on a support structure (S) arranged in an outdoor space includes a vehicle (20) on which the photovoltaic solar panels (1) to be installed are arranged, and a manipulator robot (24) arranged on-board the vehicle (20) for sequentially picking-up one or more photovoltaic panels (1) from the vehicle, and for positioning them on said support structure (S) as the vehicle moves on one side along the support structure (S). An optoelectronic system (27) is used for automatic optical recognition of the correct position in which a photovoltaic solar panel (1) must be picked-up as well as the correct installing position of the photovoltaic solar panel (1) on the support structure (S).

Abstract: A service satellite for providing station keeping services to a host satellite is disclosed. The service satellite may have a body, and a gripping mechanism attached to the body. The gripping mechanism may be adapted to attach to an interface ring extending from an external surface of the host satellite to form an interconnection between the host satellite and the service satellite through the externally extending interface ring. Attaching the gripping mechanism to the interface ring may form an interconnected unit having a combined center of mass. The service satellite may have at least two thrusters and at least one controller. The at least one controller may maintain the interconnected unit in a substantially stationary orbit by selectively orienting the two thrusters such that the thrust vectors from the two thrusters avoid passing through the combined center of mass, and are each offset from the combined center of mass.

Abstract: A quick disconnect apparatus including a first end configured to interface with a legacy fill and drain valve (FDV) of a satellite to be serviced, a second end configured to interface with a refueling tool, and a middle portion including at least one redundant seal to prevent unwanted fuel transfer during connection of the FDV and refueling tool.

Abstract: A first spacecraft includes a first fluid storage arrangement and a fluid flow metering arrangement including a holding tank coupled with the first fluid storage arrangement, a flow meter disposed proximate to the holding tank, and an active thermal control arrangement controlling the temperature of the flow meter and the holding tank. The first spacecraft is configured to service a second spacecraft, the second spacecraft including a second fluid storage arrangement, by transferring one or both of a propellant and a pressurant from the first fluid storage arrangement to the holding tank, and from the holding tank, through the flow meter, to the second fluid storage arrangement.

Abstract: The present invention relates to a forward acoustic scattering based double-transmitter and double-receiver networking target detection system and method thereof. Two transmitting ends and two receiving ends are adopted, anchored at a sea bottom, and arranged in a parallelogram layout. Time of a target crossing transmitting-receiving connection lines is extracted by adopting a proper direct wave suppression method; and unknown parameters of the horizontal distance, the target velocity and the included angle between the target track and the transmitting-receiving connection lines are estimated at corresponding moving time intervals when the target crosses the four transmitting-receiving connection lines according to different crossing modes. An arrangement mode is simple and flexible, and monitoring of sea areas and sea channels can be realized. The information of the time of the target crossing the transmitting-receiving connection lines, extracted by the method, is more accurate and reliable.

Abstract: Disclosed herein is a system including an oxidizer nozzle tool having a first end, a rotary drive and a linear drive mechanism. A component, such as a quick disconnect valve, is attached to the first end of the oxidizer nozzle. The rotary drive actuates the component to engage and seal to a drain valve on a device (such as a satellite) such that the component can open and close the drain value while maintaining the seal, wherein the linear drive mechanism is operable to lock and release the component from the oxidizer nozzle tool. A hose is mated to the oxidizer nozzle tool, wherein upon actuation, fluid flows through the hose to the oxidizer nozzle tool and through the component into the drain valve.

Abstract: A rideshare adapter for a launch vehicle (LV), a configurable-mass rideshare dispenser for a rideshare adapter employable with a LV, and a method of operating a configurable-mass rideshare dispenser for an LV are disclosed herein. In one embodiment, the rideshare adapter includes: (1) an annular peripheral wall that defines an interior of the rideshare adapter and (2) inner support walls, mechanically coupled to the peripheral wall, that are located within the interior and divide the interior into multiple rideshare dispenser compartments.

Abstract: This disclosure generally relates to an automotive drone deployment system that includes at least a vehicle and a deployable drone that is configured to attach and detach from the vehicle. More specifically, the disclosure describes the vehicle and drone remaining in communication with each other to exchange information while the vehicle is being operated in an autonomous driving mode so that the vehicle's performance under the autonomous driving mode is enhanced.

Abstract: A spacecraft including a main body structure and at least a first deployable element is reconfigured from a launch configuration to an on-orbit configuration. In the launch configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a first arrangement. In the on-orbit configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a second arrangement. Reconfiguring the spacecraft includes detaching the first deployable element from the first arrangement, moving the first deployable element with respect to the spacecraft main body structure; and attaching the first deployable element to the second arrangement.

Abstract: Transfer of objects between spacecraft can be achieved in a low gravity environment. A capture device can be part of a module that facilitates visualization of a vessel that approaches the capture device. The module can facilitate positioning of the capture device for reception of the vessel. The capture device can include spring-loaded locking arms that both allow receipt and prevent escape of the vessel. At least a portion of each locking arm can extend radially inwardly and axially toward a cushion damper of the capture device. The locking arms can move radially away from each other upon application of a force from the vessel that is axially toward the cushion damper. The locking arms can move radially toward each other upon application of a force from the vessel that is axially away from the cushion damper.

Abstract: An apparatus and method of wirelessly powering an aerospace vehicle while the vehicle is on the ground is provided to solve a problem of supplying electric power for aircraft while idling on taxiways. Present systems typically require fuel-driven auxiliary power units (APU's) to generate electricity. Running APU's to power aircraft while idling requires over 443 million gallons of jet fuel annually at a cost of $1.3 billion dollars. This results in an estimated 4.7 megatons of carbon dioxide emissions annually. At the gate, shore power is provided via hardline connection.

Abstract: A system for manipulating a space object in space comprises an articulated structure, wherein the articulated structure comprises a single actuator configured to control, equally, the deployment of the structure in space, the gripping of the space object and the folding down of the articulated structure. Developments describe the use of a fixed supporting structure, a threaded rod, a tapped whorl guided by the threaded rod and a set of articulated bars held by pivot links at their interfaces on the tapped whorl and on the fixed supporting structure. Various mechanical configurations are described, notably gripping devices comprising rollers for locking and/or unlocking the space object by separation of the articulated bars. A method of regulation, of control and of adjustment of the manipulation is provided.

Abstract: A spacecraft including a main body structure and at least a first deployable element is reconfigured from a launch configuration to an on-orbit configuration. In the launch configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a first arrangement. In the on-orbit configuration, the first deployable element is mechanically attached with the spacecraft main body structure by way of a second arrangement. Reconfiguring the spacecraft includes detaching the first deployable element from the first arrangement, moving the first deployable element with respect to the spacecraft main body structure; and attaching the first deployable element to the second arrangement.

Abstract: Techniques for performing orbit raising, north-south stationkeeping, east-west stationkeeping, and momentum management with thrusters disposed on a spacecraft are disclosed. The spacecraft includes at least one thruster support mechanism (TSM), including a pointing arrangement and an elongated structural member, the structural member having a long dimension defining a first axis a proximal portion of the structural member is attached to the pointing arrangement each of the thrusters is fixedly coupled with a distal portion of the structural member. The pointing arrangement includes a first, second, and third revolute joint, the first revolute joint being rotatable about the first axis; the third revolute joint being rotatable about a third axis, the third axis being fixed with respect to the spacecraft; and the second revolute joint being rotatable about a second axis, the second axis being orthogonal to each of the first axis and the third axis.

Abstract: A system for performing industrial operations comprises at least one tool head provided with a tool and at least one sensor associated to the tool head. The system further comprises a control module mounted on the tool head including a data-acquisition unit connected to the sensor configured for acquiring the data coming from said at least one sensor, and a wireless transmission unit connected to the acquisition unit for receiving the aforesaid acquired data and for transmitting the data acquired to a receiving unit in a wireless mode. The module further comprises a device for storing electrical energy for electrical supply of the control module. The system further comprises a wireless charging system for charging the device for storing electrical energy comprising a first charging device carried by the tool head and connected to the energy-storage device and a second charging device associated to a stationary workstation.

Abstract: The present disclosure provides derivatives of native lignin suitable for production of carbon fibers wherein the derivatives of native lignin have a certain alkoxy content and/or a certain carbon content. The present lignin derivatives can have acceptable spinnability performance characteristics for producing carbon fibers having acceptable tensile strengths and acceptable modulus of elasticity.

Abstract: Disclosed are methods adapted to aid in a calibration of a robotic end effector. The method includes providing a robotic component having an end effector and a light beam sensor provided in a fixed orientation to the end effector fingers, rotating a light beam of the light beam sensor relative to a geometrical calibration feature of a teach tool mounted in an approximately known orientation to an article, and determining a precise location (e.g., center) of the geometrical calibration feature based upon engagement of the light beam with edges of the geometrical calibration feature. In another aspect, a rotational orientation of the fingers of the end effector are calibrated using the teach tool. A novel teach tool and a robot calibration system including the teach tool are disclosed, as are other aspects.

Abstract: 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.

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: 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.

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: An amount of propellant remaining in an orbiting satellite can be estimated in a more accurate manner than is possible with conventional approached. Pressure and temperature telemetry data received from the satellite can be analyzed using a maximum likelihood estimation approach that reconstructs a predicted tank pressure signal using the temperature data and determines a pressurant volume necessary to make the reconstructed pressure signal match the received pressure signal. Drift of the pressure data received from pressure transducers in the satellite can also be addressed using the current subject matter, as can issues including but not limited to inaccessible propellant due to satellite spin, tank expansion under pressure, and the like. Independent determinations of the amounts of propellant remaining can be made using moment of inertia calculations in situations in which an axis of spin of the satellite is known a priori.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: Provided is a method and system for maneuvering a first spacecraft relative to a nearby second spacecraft that occupies a finite volume of space including obstacles in the vicinity of the second from a measured present relative position to a desired ending relative position. A trajectory is computed for the first spacecraft from the present relative position to the ending relative position using the A* algorithm. One or more thrusters of the first spacecraft are then fired. The first spacecraft's relative position and velocity are then measured and compared to the computed trajectory.

Abstract: A launch system is provided which includes a secondary payload. The secondary payload includes a propellant tank and at least one module that is supported by an adapter ring that is commonly used to secure an upper stage to a primary payload. The propellant tank is launched empty and subsequently filled with residual propellant from the upper stage.

Abstract: A method for pointing control of a laser communication terminal on a spacecraft may include measuring a line-of-sight (LOS) error of the laser communication terminal. The method may also include estimating a LOS error of the laser communication terminal based on measurements from a spacecraft gyro and a gimbal gyro onboard the spacecraft. The method may further include switching from a LOS error measurement feedback to a LOS error estimate feedback to control pointing of the laser communication terminal during a power fade condition.

Abstract: 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.

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: 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.

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: 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.

Abstract: A control device (D) for a spacecraft of a group of spacecraft intended to travel in a chosen formation comprises i) a set of at least three send/receive antennas (A1-A3) installed on at least three differently oriented faces of its spacecraft and adapted to send/receive radio-frequency signals, ii) first measuring means (M1) responsible for determining the power of the signals received by each of the antennas (A1-A3) and for delivering sets of powers each associated with one of the other spacecraft of the group, iii) storage means (BD) responsible for storing sets of cartographic data each representative of the normalized powers of the signals received by each of the antennas (A1-A3) as a function of chosen send directions, and iv) processor means (MT) responsible for comparing each set of powers delivered by the first measuring means (M1) to the stored sets of cartographic data in order to estimate each send direction of the signals sent by the other spacecraft of the group with respect to a system of axes

Abstract: The invention refers to a docking device for the docking of a maintenance device to a nozzle of a satellite, including a distance sensor for determining the distance between the maintenance device and the nozzle of the satellite. Further, a locking device is provided for connecting the docking device with the nozzle of the satellite.

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: 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: 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 device provided on a space shuttle for docking to satellites, has a linkage with a cone at its distal end and a spreader mechanism, actuatable from the shuttle, with lever spreaders having their proximal ends provided with inward projections towards the linkage. At least two lever spreaders 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 concentric to the linkage is provided below the retaining part. 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.

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 demountable docking interface mechanism and method for docking and undocking two spacecraft utilizing the demountable docking interface mechanism.

Abstract: The invention refers to a docking device for the docking of a maintenance device to a nozzle (12) of a satellite, comprising a distance sensor (14) for determining the distance between the maintenance device and the nozzle (12) of the satellite. Further, a locking device is provided for connecting the docking device (10) with the nozzle (12) of the satellite.