Capture system adapted to capture space objects, in particular for recovery or deorbiting purposes

A capture system adapted to capture a target space object, comprising a plurality of articulated arms configured to be deployable from a stowed configuration to a deployed configuration to perform capture of the target space object,

• wherein each articulated arm includes a plurality of articulated arm segments including a first articulated arm segment coupled at a first proximal end to a spacecraft or to a platform deployable from said spacecraft, the first articulated arm segment being coupled at the first proximal end via a first pivoting joint,
• wherein the plurality of articulated arm segments further includes at least a second articulated arm segment coupled at a second proximal end to a first distal end of the first articulated arm segment via a second pivoting joint,
• and wherein the plurality of articulated arm segments are nestable one within the other, in the stowed configuration, such that the first and second articulated arm segments are intertwined.

A capture system adapted to capture a target space object, comprising a plurality of articulated arms configured to be deployable from a stowed configuration to a deployed configuration to perform capture of the target space object,

• wherein each articulated arm includes a plurality of articulated arm segments including a first articulated arm segment coupled at a first proximal end to a spacecraft via a first pivoting joint,
• wherein the plurality of articulated arm segments further includes at least a second articulated arm segment coupled at a second proximal end to a first distal end of the first articulated arm segment via a second pivoting joint,
• and wherein, in the stowed configuration, each of the articulated arm segments is aligned longitudinally alongside lateral sides of the spacecraft.

A capture system adapted to capture a target space object, comprising a plurality of articulated arms configured to be deployable from a stowed configuration to a deployed configuration to perform capture of the target space object,

• wherein each articulated arm includes a plurality of articulated arm segments including a first articulated arm segment coupled at a first proximal end to a spacecraft via a first pivoting joint,
• wherein the plurality of articulated arm segments further includes at least a second articulated arm segment coupled at a second proximal end to a first distal end of the first articulated arm segment via a second pivoting joint,
• and wherein, in the stowed configuration, the articulated arm segments are folded one onto the other into a compact folded configuration.

A capture system adapted to capture a target space object, comprising a plurality of articulated arms configured to be deployable from a stowed configuration to a deployed configuration to perform capture of the target space object,

• wherein each articulated arm includes a plurality of articulated arm segments including a first articulated arm segment coupled at a first proximal end to a spacecraft or to a platform deployable from said spacecraft, the first articulated arm segment being coupled at the first proximal end via a first pivoting joint,
• wherein the plurality of articulated arm segments further includes at least a second articulated arm segment coupled at a second proximal end to a first distal end of the first articulated arm segment via a second pivoting joint,
• and wherein at least one of the articulated arm segments is provided with a shock-absorbing element configured to come in contact with the space object to be captured.

A capture system adapted to capture a target space object, comprising a plurality of articulated arms configured to be deployable from a stowed configuration to a deployed configuration to perform capture of the target space object,

• wherein each articulated arm includes a plurality of articulated arm segments including a first articulated arm segment coupled at a first proximal end to a spacecraft or to a platform deployable from said spacecraft, the first articulated arm segment being coupled at the first proximal end via a first pivoting joint,
• wherein the plurality of articulated arm segments further includes at least a second articulated arm segment coupled at a second proximal end to a first distal end of the first articulated arm segment via a second pivoting joint,
• and wherein each articulated arm further includes a third articulated arm segment coupled at a third proximal end to a second distal end of the second articulated arm segment via a third pivoting joint.