A space information recorder (100) acquires space object information (500), which is orbit forecast information of a plurality of space objects (60), from a management business device (40) used by a management business operator that manages the plurality of space objects (60), and records the space object information (500). The space object information (500) includes a forecast epoch, a forecast orbital element, and a forecast error of each of the plurality of space objects (60). When it is foreseen that a space object A included in the plurality of space objects (60) will intrude into a range at orbital altitudes of 300 km to 1000 km in which a satellite group of LST 10:00 to 11:00 is present, a time period from intrusion to exit and orbit forecast information are recorded.

Disclosed are a method, a device, an apparatus for capturing a non-cooperative target using a space robotic arm, and a non-transitory storage medium, and relates to the technical field of on-orbit servicing. The method is applied to a space robotic arm with a magnetic capture device as an end actuator. The method includes: establishing a magnetic attractive force model for the magnetic capture device, determining a magnetic attractive force characteristic of the magnetic capture device based on the magnetic attractive force model, determining a capture strategy for the non-cooperative target based on the magnetic attractive force characteristic of the magnetic capture device, capturing the non-cooperative target according to the capture strategy, and determining whether the non-cooperative target is captured based on a preset determination condition.

Disclosed are a system and a method for capturing a space target. The system includes a plurality of capturing devices, a delivery device, a launching device, and a deceleration and recovery device, each of the plurality of capturing devices is configured to be launched into a target orbit to capture a defunct space target, the delivery device is configured to deliver, along a preset delivery trajectory, each of the plurality of capturing devices to a first preset location in the launching device, the launching device is configured to launch each of the plurality of capturing devices located at the first preset location into the target orbit to capture the defunct space target, and the deceleration and recovery device is configured to decelerate each of the plurality of capturing devices after it is launched and flies a preset distance.

According to an aspect of the present invention, there is provided a method for rendezvous with an orbiting object comprising: launching a tug and a servicer into a client orbit; separating the servicer from the tug; and docking the servicer with a client. According to another aspect of the present invention, there is provided system for rendezvous with an orbiting object comprising: a first spacecraft comprising a tug capable of towing a second spacecraft, wherein the second spacecraft is a servicer configured to dock with a tumbling client orbiting object.

Exemplary embodiments provided herein include connection systems in which a gripper is actuated through introduction of a material to an interior cavity. Embodiments may include more than one cavity such that deployment and actuation may be separately controlled. Additional cavities may also be used and/or selection of valves between cavities such that actuation and/or deployment may further be controlled.

A material collection system includes a planar structure, at least one actuator, and a plurality of pull cables. The planar structure includes a plurality of interconnected geometric panels having a plurality of holes therethrough, and each interconnection between two geometric panels defines a foldable coupling. The plurality of pull cables pass through the holes such that a first end of each pull cable is coupled with at least one geometric panel and a second end of each pull cable is coupled with the at least one actuator. The planar structure is operable between a first stable geometric state and a second stable geometric state. An actuation to pull each of the plurality of pull cables transitions the planar structure between the first stable geometric state and the second stable geometric state.

The system and method for decelerating space objects moving at high velocities are provided. The system comprises at least one closed volume containing a combination of gas, liquid, solid particles, or a mixture thereof. The volume can be transported to the targeted location using a range of means, including a chemical gun, light gas gun, electromagnetic coil gun, superconducting quench gun, a rocket, or a combination thereof. The volume is strategically positioned on the trajectory of the moving object. Upon penetrating the walls of the volume, the object passes through it, experiencing deceleration.

According to an aspect of the present invention, there is provided a method comprising: propelling a servicing spacecraft to an object; deploying one or more counter mass(es) away from a servicing spacecraft bus to offset the center of mass of the servicing spacecraft into an empty volume; approaching the object, by the servicing spacecraft; positioning the center of mass of the servicing spacecraft in approximately the same location as the center of mass of the object; imparting angular momentum to the servicing spacecraft to match the tumble rate of the object; and contacting the object with one or more mechanical attachments to the servicing spacecraft.

Exemplary embodiments provided herein include connection systems in which a gripper is actuated through introduction of a material to an interior cavity. Embodiments may include more than one cavity such that deployment and actuation may be separately controlled. Additional cavities may also be used and/or selection of valves between cavities such that actuation and/or deployment may further be controlled.

Space debris capture systems include an outer assembly and an inner assembly. The Outer assembly includes an outer membrane and an inner membrane, where, in a deployed state, the outer membrane is separated from the inner membrane by a separation gap. The inner assembly is arranged within the inner membrane of the outer assembly. The inner assembly is formed of a plurality of sheets of material arranged at a plurality of orientations relative to the inner membrane and define a plurality of cells within the outer assembly when in the deployed state. A first group of the cells are defined within surfaces of the plurality of sheets of material and a second group of cells are defined between the surfaces of the inner assembly and an inner surface of the inner membrane.