The invention relates to a method for deflecting space debris comprising steps of: launching (E2) a thruster (2) by means of a sounding rocket (1) at a target altitude close to that of the one or more debris to be deflected. generating (E3) by the thruster a gas cloud (G) above the sounding rocket.

A solar generator comprises a flexible support, an array of solar cells, electrical transfer conductors, blocking diodes, the solar cells being formed along different transverse strings, the solar cells situated in a same string being electrically connected in series, each string comprising two opposite ends, respectively of positive polarity and of negative polarity. The positive polarity end of each string of solar cells is individually connected to a respective blocking diode via an electrical transfer conductor dedicated to the string, the electrical transfer conductors dedicated to the different strings being independent of one another, the blocking diodes being located at the proximal end of the solar generator, outside of the array of solar cells.

A solar generator comprises a flexible support, an array of solar cells, electrical transfer conductors, blocking diodes, the solar cells being formed along different transverse strings, the solar cells situated in a same string being electrically connected in series, each string comprising two opposite ends, respectively of positive polarity and of negative polarity. The positive polarity end of each string of solar cells is individually connected to a respective blocking diode via an electrical transfer conductor dedicated to the string, the electrical transfer conductors dedicated to the different strings being independent of one another, the blocking diodes being located at the proximal end of the solar generator, outside of the array of solar cells.

In a space traffic management system, space traffic management devices individually mounted in a plurality of mega-constellation business devices and in a debris removal business device are connected to each other via a communication line. The debris removal device performs Active Debris Removal (ADR) against debris formed by a satellite managed by a first mega-constellation business operator. The debris removal device acquires real-time high-accuracy orbital information of a satellite group of a second mega-constellation business operator in a timeframe in which a debris removal satellite, during orbital descent, passes through an orbital altitude region where the satellite group of the second mega-constellation flies, the debris removal satellite passing through the satellite group while ensuring flight safety.

A method and satellite for capture-less management of orbital debris objects, include controlling a satellite having opposing thrusters to be maintained at a predetermined distance from an orbital debris object to be managed, i.e., paired with the orbital debris object. Management may include fine tracking of the orbital debris object and/or operating the opposing thrusters to apply force to the orbital debris object to generate a model of the orbital debris object, to change the attitude of the orbital debris object, to deorbit the orbital debris object, and/or breakup the orbital debris object.

A method and satellite for capture-less management of orbital debris objects, include controlling a satellite having opposing thrusters to be maintained at a predetermined distance from an orbital debris object to be managed, i.e., paired with the orbital debris object. Management may include fine tracking of the orbital debris object and/or operating the opposing thrusters to apply force to the orbital debris object to generate a model of the orbital debris object, to change the attitude of the orbital debris object, to deorbit the orbital debris object, and/or breakup the orbital debris object.

Provided is a system, method and device for electrodynamic dust shielding. The system includes an electrodynamic dust shield device external to an object having lunar dust. The electrodynamic dust shield device electrodynamically removes unwanted material from the object. The method includes positioning an electrodynamic dust shield device near an object to be cleaned from dust, and providing an electric field with the electrodynamic dust shield to remove dust from the object to be cleaned.

Provided is a system, method and device for electrodynamic dust shielding. The system includes an electrodynamic dust shield device external to an object having lunar dust. The electrodynamic dust shield device electrodynamically removes unwanted material from the object. The method includes positioning an electrodynamic dust shield device near an object to be cleaned from dust, and providing an electric field with the electrodynamic dust shield to remove dust from the object to be cleaned.

Disclosed is a micrometeoroid and debris protection system (MDPS) for a thermal control system on a spacecraft. The MDPS comprises a radiator face-sheet, a truss attached to the radiator face-sheet, and a thermally transparent bumper disposed on the truss. The thermally transparent bumper shields the radiator face-sheet from micrometeoroids and debris and enables thermal transfer from the radiator face-sheet through the thermally transparent bumper.

Disclosed is a micrometeoroid and debris protection system (MDPS) for a thermal control system on a spacecraft. The MDPS comprises a radiator face-sheet, a truss attached to the radiator face-sheet, and a thermally transparent bumper disposed on the truss. The thermally transparent bumper shields the radiator face-sheet from micrometeoroids and debris and enables thermal transfer from the radiator face-sheet through the thermally transparent bumper.