A spacecraft system and method includes a platform with a dock and an umbilical payout device. A robot is connected to an umbilical paid out by the umbilical payout device and is repeatedly deployable from the dock. The robot includes one or more imagers, an inertial measurement unit, and a plurality of thrusters. A command module receives image data from the one or more robot imagers and orientation data from the inertial measurement unit. An object recognition module is configured to recognize one or more objects from the received image data. The command module determines the robot's orientation with respect to an object and issues thruster control commands to control movement of the robot based on the robot's orientation. The combination of the space platform and robot on umbilical line can be used for towing another object to different orbital location, inspection including self-inspection of the robot carrying platform and for robotic servicing.

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.

There is provided an apparatus for capturing a space object, the apparatus comprising a harpoon element for penetrating the object, the harpoon element being configured to form part of a harpoon for launching towards the object; and penetration control means for controlling the penetration of the harpoon element into the object. The penetration control means can comprise a compressible component, forming part of the harpoon, for absorbing some of the kinetic energy of the harpoon. Alternatively or additionally, it may comprise means for varying the launch speed of the harpoon.

Methods and systems related to space systems and more specifically to tethers for space maneuverability and replated applications are disclosed herein. Specific embodiments disclosed herein improve traditional space tethers by increasing the functionality of the tether, improving the stability of the tether, and enhancing the operational reliability and durability of the tethers. A disclosed method to execute a maneuver for a tether system comprises: obtaining sensor data using a sensor; calculating, using the sensor data, a required command for an actuator to execute the maneuver; and executing the required command to execute the maneuver to traverse an intermediate node along a tether using the actuator. The center of mass of the tether system is thereby altered and the maneuver is executed.

An unmanned vehicle comprising a navigable propulsion system for moving the vehicle in an operating environment and a controllable steering mechanism for steering the vehicle as it moves in the operating environment; and a tethering mechanism for attaching to existing space debris including waste, garbage, derelict satellites and equipment, and other debris; and tethering device for attaching to waste hauling device for disposing of waste generated from inhabited orbiting structures. The propulsion device is a universal transportation device for assorted space debris utilizing connectors for hauling collected waste captured in fibrous formulated cloth material, or individual pieces of debris, or equipment. A telescoping utility arm provides the capability to direct the hook mechanism and tethering device to secure space waste and debris of various shapes, sizes, and conditions for transportation. A fibrous formulated containment device collects waste from inhabited space structures.

A system and method for assisted EVA self-return is provided herein. The system estimates a crewmember's navigation state relative to a fixed location, for example on an accompanying orbiting spacecraft, and computes a guidance trajectory for returning the crewmember to that fixed location. The system may account for safety and clearance requirements while computing the guidance trajectory. According to at least one embodiment, the system actuates the crewmember's safety jetpack to follow the prescribed trajectory to the fixed location. In another embodiment, the system provides the crewmember with a directional cue (e.g., a visual, auditory, or tactile cue) corresponding to the prescribed trajectory back to the fixed location. The system may be activated by the crewmember or remotely by another crewmember and/or system.

A debris removal device includes: an end mass adapted to approach debris to be removed; a debris capture device separably-mounted on the end mass; and a tether connecting the debris capture device and the end mass to each other. The debris capture device includes a harpoon adapted to penetrate into the debris, a shooting device adapted to shoot the harpoon, a guide member positioned to come into contact with the surface of the debris to adjust the shooting angle of the harpoon with respect to the surface of the debris, and a switch that sends the shooting signal to the shooting device. When the harpoon is penetrated into the debris, the end mass is separated from the debris capture device, and the tether is released into outer space.

Circular mass accelerators for off-world applications are disclosed herein. An example system includes a base assembly that is configured to interface with a supporting surface, a vertical support assembly extending from the base assembly, a first drive positioned, a shaft connected to the first drive, a hub assembly having a spool, the hub assembly being coupled to a second drive that is located on a terminal end of the shaft, a first tether and a second tether that can be spooled onto and unspooled from the spool by the second drive, and payloads positioned each of the tethers, the payloads being releasably coupled to tethers in such a way that the payloads can be released upon the payloads being rotated to a target launch velocity.

A device comprises a support net with nodes, wherein each node comprises a HTS photovoltaic-magnetic cell, wherein alignments of the HTS photovoltaic-magnetic cells are arranged with N-S in parallel alignment. A device comprises a tether comprising a plurality of HTS solenoids and a sheath, wherein a solenoid of the plurality of HTS solenoids comprises a high temperature superconducting material and reinforcing fiber. A device comprises propulsion ball or plate with tail, injected in propulsion channel; HTS solenoids disposed along walls of propulsion channel, wherein the propulsion ball or plate with tail are moved through the propulsion channel using magnetic field generated by HTS solenoids; and a collection channel.

The present invention relates to an assembly apparatus for assembling components of spacecraft in space. The assembly apparatus includes: a core platform; and a mobile platform including an end effector configured to perform an assembly or manufacturing task. The mobile platform is connected to the core platform by a tether. The core platform includes a body and a coupling element connected to and extendable from the body such that the coupling element may be spaced from the body of the core platform. The tether connects the mobile platform to the body via the coupling element. The assembly apparatus further includes an actuator configured to vary the length of the tether extending between the coupling element and the mobile platform to control the position of the mobile platform relative to the body of the core platform.