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.

A space device includes: an adhesion part to adhere to a target existing in the space; and a propulsion part to obtain propulsion power. The space device that adheres to the target at the adhesion part moves together with the target by the propulsion part, thereby conveying the target to a predetermined target position.

A dynamic flex circuit includes a plurality of hole sets arranged along the dynamic flexible circuit. The dynamic flex circuit also includes a plurality of actuator wires coupled to the dynamic flexible circuit by way of intertwining each of the plurality of actuator wires through each hole set in the plurality of hole sets arrange along the dynamic flexible circuit. Each of the plurality of actuator wires are configured to impart a motion onto the dynamic flexible circuit depending on the amount of heat applied to each of the plurality of actuator wires.

A driving mechanism controller included in a capturing device causes one or more driving mechanisms to spread a tethering member having an elongated shape to the outside of a housing by a target spread length. The driving mechanism controller, when an artificial space object is located in the area surrounded by the tethering member, causes the one or more driving mechanisms to retract the tethering member to the inside of the housing until at least a part of the tethering member comes into contact with the artificial space object. The tethering member is stable in a first shape having a curved section orthogonal to a linear extending direction of the tethering member.

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.

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.

Systems, apparatuses, and methods for removal of orbital debris are provided. In one embodiment, an apparatus includes a spacecraft control unit configured to guide and navigate the apparatus to a target. The apparatus also includes a dynamic object characterization unit configured to characterize movement, and a capture feature, of the target. The apparatus further includes a capture and release unit configured to capture a target and deorbit or release the target. The collection of these apparatuses is then employed as multiple, independent and individually operated vehicles launched from a single launch vehicle for the purpose of disposing of multiple debris objects.

A debris removal device includes: a body part; an adhesion part to let the space debris adhere to the body part; a braking part to generate braking force in a specific direction, to act on the space debris adhering to the body part via the adhesion part during circling of the body part around the orbit together with the space debris; and a timing control part to control generation timing of the braking force. The timing control part generates the braking force, during circling of the body part together with the space debris around the orbit, when the body part is located at a specific region on the orbit where a direction of the braking force is substantially parallel to an orbit plane including the orbit and substantially parallel to a tangential line of the orbit, and in substantially an opposite direction of a circling direction of the space debris.

A system for collecting debris includes a collector configured to accumulate debris and retain an electrostatic charge; a deployment mechanism configured to move the collector into a path of the debris; an electrostatic charging array comprising one or more wires or plates operatively connected to the collector; and one or more processors operatively coupled to the collector, the deployment mechanism, and the electrostatic charging array. The one or more processors are configured to track debris in relation to the collector; control movement of the collector and the deployment mechanism; and regulate power to the electrostatic charging array.

Disclosed herein are systems and methods of capturing orbital and sub-orbital extraterrestrial debris. The system is directed to a pouch comprising a semi-penetrable outer fabric covering a debris particle-capturing core. Also disclosed herein are methods of producing the pouch. Further described herein are methods of capturing debris with a deployed pouch.