A fuel depot in space is provided. The fuel depot has a collapsible housing with a guidance, navigation, and control (GNC) system, a power management system, and a reaction control system (RNC). Connected to the housing are a plurality of fuel tanks that are connected via collapsible rods. The fuel tanks have pipe systems that are in communication with a plurality of pumps to transfer fuel from the tanks through a refueling arm and into a spacecraft during refueling.

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.

A multi-functional rendezvous and capture module containing a mechanical capture system is provided. The multi-functional rendezvous and capture module consists of a system of mutual measurements with a radar module, a technical vision system, a laser rangefinder containing a radar module and two independent locators, a locator with an active phased antenna array and a locator of a radar orthogonal interferometer, and a control unit. The mechanical capture system consists of robot manipulators, a control unit, and damping supports.

An apparatus comprised of positionally directable masses attached to a binding component that includes a coupling device for payload to reduce gravitational deviation of the apparatus' trajectory by alternatingly accelerating and retracting physically bound component masses in equal and opposite directions to the extents of their bindings, initially and optimally perpendicular to the gravitational field and perpendicular to the apparatus trajectory by using in built transduction componentry located within the masses or the binding componentry or both that utilises electromagnetic forces, forces generated by chemical reactions, or other applied or responsive motive force to positionally direct the bound directable masses.

Systems, methods, and devices for robotic capture of an object are provided. A system for robotic-based capture of a free flyer object includes a grapple fixture for mounting to the free flyer object and an end effector for capturing the free flyer object by interfacing with the grapple fixture. The grapple fixture includes a base and a deflectable probe. The end effector includes a probe guiding surface for deflecting and guiding a probe tip of the probe through an opening in the probe guiding surface and into a grappling position. The end effector includes a probe sensing element for sensing when the probe tip is in the grappling position and triggering a capture mechanism. The capture mechanism grapples the probe tip and an actuator retracts the capture mechanism to a predetermined position to establish a load-bearing interface between the free flyer object and the end effector.

Methods and systems for passively slowing the spin rate of an uncontrolled object in space are presented. A damper mechanism is provided that includes a magnet that is free to rotate in any direction about a central point with respect to a carrier or outer housing. The magnet can be carried within an inner element or sphere, that is in turn mounted within an outer sphere. The inner and outer spheres can be separated by a viscous fluid or other mechanism in which damping can be introduced. The damper mechanism can be associated with an attachment mechanism, that secures the resulting damper or despin system to a target object. A method of neutralizing the magnetic field is also included to enable the system to be launched in a passive state.

An unmanned aerial vehicle (UAV) pin array release and capture chamber system includes a chamber assembly having two parallel plates of pin arrays from which a plurality of pins extend and retract vertically opposite each other so as to release and capture a UAV. The pin arrays are separated from each other by a space having two vertical and two horizontal sides, and the space is sized so as to receive the UAV. Each pin arrays may be housed in a pin array chamber enclosure. The chamber assembly may be attached to a moving object, such as an aircraft, or may be stationary with respect to a ground surface.

Embodiments provide a spacecraft airlock system. Embodiments provide a method and apparatus for attaching space exposed payloads to a space station.

Independently moving deployment and positioning space vehicles that are configured to deploy and/or position structures are disclosed. The deployment and positioning vehicles may provide a lighter weight, more flexible, and more reliable deployment and positioning system that enables the deployment of space structures that are potentially much larger than currently possible with mechanical components of the structure itself. The deployment and positioning vehicles could be used for removal of failure prone deployment mechanisms for spacecraft. Solar arrays, antennas, panels, instrument booms, etc. could be pulled open and locked into place, and then potentially repositioned and/or reoriented during a mission.

A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.