Space debris capture apparatus and methods for implenting the same

A satellite, comprising:

• at least one structural element that is deformable during a collision with one or more space objects, the at least one structural element comprising:
• a first side comprising a first laver of material;
• a second side spaced apart from the first side to define an interior portion between the first side and the second side, the second side comprising a second laver of material;
• and
• at east one material disposed within the interior portion, the at least one material designed to absorb energy over time during a collision process with each of the one or more space objects, wherein one or more of the first laver of material, the second laver of material and the at least one material that is disposed within the interior portion are configured to capture and alter orbit of the satellite and the one or more space objects captured thereby after collision with the satellite;
• and
• a coil of electrically conductive material with a mass on one end thereof, wherein the coil is configured to release after a collision with the one or more space objects to initiate deorbiting of the satellite.

A satellite, comprising:

• at least one structural element that is deformable during a collision with one or more space objects, the at least one structural element comprising:
• a first side comprising a first layer of material;
• a second side spaced apart from the first side to define an interior portion between the first side and the second side, the second side comprising a second layer of material;
• at least one material disposed within the interior portion, the at least one material designed to absorb energy overtime during a collision process with each of the one or more space objects, wherein one or more of the first layer of material, the second layer of material and the at least one material that is disposed within the interior portion are configured to capture and alter orbit of the satellite and the one or more space objects captured thereby after collision with the satellite, and wherein the at least one material is formed in a shape of one or more coils, and wherein each coil comprises:
• a length of material that is wound or arranged in a spiral configuration or as a sequence of rings, wherein each coil is oriented either:
• substantially parallel to a longitudinal axis defined by the interior portion, or substantially perpendicular to the longitudinal axis defined by the interior portion.

A satellite, comprising:

• at least one structural element that is deformable during a collision with one or more space objects, the at least one structural element comprising:
• a first side comprising a first layer of material;
• a second side spaced apart from the first side to define an interior portion between the first side and the second side, the second side comprising a second layer of material;
• and
• at least one material disposed within the interior portion, the at least one material designed to absorb energy overtime during a collision process with each of the one or more space objects, wherein one or more of the first layer of material, the second layer of material and the at least one material that is disposed within the interior portion are configured to capture and alter orbit of the satellite and the one or more space objects captured thereby after collision with the satellite,
• wherein the first side further comprises a first thin film structure comprising a thin film antenna, and
• wherein the second side further comprises a second thin film structure opposite the first thin film structure and a plurality of thin film solar cells, and
• wherein the first side or the second side further comprises a thin film battery.