A spacecraft for removing space debris is disclosed. The spacecraft includes a satellite bus, a shield member foldable on an outer side face of the satellite bus and disposed facing towards space debris to reduce a movement speed of the space debris, and a support member configured to support the shield member with respect to the satellite bus, in which the shield member includes a central panel configured to overlap one face of the satellite bus, a plurality of first panels connected to peripheral sides of the central panel and radially extended, and a plurality of second panels located between the first panels.

An orbital debris interception vehicle includes a satellite bus and a debris interception module releasably coupled to the satellite bus. The debris interception module includes a debris impact pad, such as a pancake-shaped Whipple shield. A plurality of such vehicles can be deployed into an equatorial orbit and maneuvered to intercept orbital debris as it passes through the equatorial plane. In particular, the satellite bus can release the debris interception module before an intercept and reconnect to it after the intercept.

Exemplary embodiments described herein include innovative engagement devices. Exemplary engagement devices may include on or more tape spring systems. The tape spring system may include a continuous or segmented bi-stable tape spring. The tape spring can be stowed in a rolled up configuration, extended to a deployed configuration, and then triggered to return to a retracted configuration.

A rotation suppressing device 1 includes: a body 10; a shaft 20 extending outward from the body 10 and configured to rotate about a first rotation axis A.sub.1; a rotation part 30 configured to rotate about a second rotation axis A.sub.2 together with the shaft 20; a capture part 40 fixed to the rotation part 30 and configured to capture space debris D; a braking part 50 configured to suppress rotation of the shaft 20; and a body rotation suppressing part 60 configured to suppress rotation of the body 10 occurring when the braking part 50 operates.

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.

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.

An orbital debris interception vehicle includes a satellite bus and a debris interception module releasably coupled to the satellite bus. The debris interception module includes a debris impact pad, such as a pancake-shaped Whipple shield. A plurality of such vehicles can be deployed into an equatorial orbit and maneuvered to intercept orbital debris as it passes through the equatorial plane. In particular, the satellite bus can release the debris interception module before an intercept and reconnect to it after the intercept.

A system is described for locating the barycenter of at least one object orbiting in space, such as for example space debris, adapted to allow the physical and mechanical characterization of the identified object, comprising: at least one remote sensor (1) placed on board a station (2) adapted to detect the space coordinates of certain points (Pi) belonging to the identified object (3), with respect to a space reference system; first means for acquiring data related to positions assumed in time by the points (Pi) for reconstructing the trajectory followed by the points (Pi); second means for determining the instantaneous rotation axes of the identified objects associated with the trajectory, for determining a segment perpendicular to each pair of the instantaneous rotation axes in a sequence and for locating the mean point of the segment; and third means for computing a discrete function d(tk) of the length of the segments, for computing an envelope curve (c) of the local maxima of the discrete function d(tk) and for determining the minimum of the envelope curve (c) for locating the barycenter G(tk*) of the identified object. A process of physical and mechanical characterization of the identified object through the system is further described.

The invention relates to the protection of spacecraft from debris and to de-orbiting devices of the atmospheric drag type, and to debris sweeping apparatus for the removal of debris from the space environment. The debris shielding apparatus for a spacecraft has a shield unit including a shielding surface for impeding incident debris. The shield unit is attached to the spacecraft body and has a drive mechanism for positioning the shield unit in relation to the spacecraft body. The drive mechanism is capable of moving the shield unit between a stowed first position and a deployed second position. In the deployed second position the plane of the shielding surface is at an angle to the spacecraft body.

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. A 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.