초록 ▼

For capturing satellites and other orbital objects, one or more independent capturing units are releasably arranged on a spacecraft serving as a steerable carrier vehicle. Each capturing unit has a propellant charge and at least one braking thrust nozzle of its own, and a closeable capture net relea

For capturing satellites and other orbital objects, one or more independent capturing units are releasably arranged on a spacecraft serving as a steerable carrier vehicle. Each capturing unit has a propellant charge and at least one braking thrust nozzle of its own, and a closeable capture net releasably connected to the capturing unit via a tether line. The net is deployed from the capturing unit to capture the orbital object. Position or attitude control engines of the carrier vehicle are operated for orienting the combination including the capturing unit and the orbital object captured in the net. The capturing unit is then released from the carrier vehicle, and applies a braking thrust to the captured object so as to deorbit the captured object together with the capturing unit.

대표청구항 ▼

1. A recovery and braking device for capturing orbital objects flying freely in space, comprising a spacecraft serving as a steerable carrier vehicle, andat least one capturing unit releasably mounted on and releasable from the carrier vehicle,wherein:the carrier vehicle is equipped with at least on

1. A recovery and braking device for capturing orbital objects flying freely in space, comprising a spacecraft serving as a steerable carrier vehicle, andat least one capturing unit releasably mounted on and releasable from the carrier vehicle,wherein:the carrier vehicle is equipped with at least one position or attitude controlling engine,each said capturing unit is respectively equipped with at least one propellant charge and a closeable capture net,each said capturing unit is respectively releasably connected via a single tether line to a closed central apex of the capture net, wherein a respective single one of said capture net is connected by said single tether line to only a single said capturing unit, andthe propellant charge is equipped with at least one thrust nozzle effective as a braking device. 2. The recovery and braking device according to claim 1, wherein four of said capturing units are mounted on the carrier vehicle. 3. The recovery and braking device according to claim 2, wherein a plurality of said capturing units are combined in a series or parallel connection with one another. 4. A system for capturing and deorbiting an orbital object, comprising: a carrier vehicle equipped with at least one engine and at least one engine nozzle configured and arranged for at least one of position control and attitude control; andat least one capturing unit releasably mounted on said carrier vehicle, wherein each said capturing unit respectively is equipped with at least one braking thrust nozzle, a propellant charge communicating with said at least one braking thrust nozzle, and a capture net that is deployable from said capturing unit and is releasably connected to said capturing unit by a single tether line that is connected to a closed central apex of said capture net, wherein a respective single one of said capture net is connected by said single tether line to only a single said capturing unit. 5. The system according to claim 4, wherein said at least one capturing unit comprises a plurality of said capturing units independently releasably mounted on said carrier vehicle. 6. The system according to claim 4, wherein said carrier vehicle is further equipped with releasable connection clamps that releasably mount said at least one capturing unit on said carrier vehicle. 7. The system according to claim 4, wherein at least a selected one said capturing unit is transportable along said carrier vehicle so that said selected capturing unit can be transported from an initial position to a forward position at a front edge of said carrier vehicle where said capture net can then be deployed from said selected capturing unit. 8. The system according to claim 4, wherein each single said capturing unit respectively is releasably connected by said single tether line thereof to said single capture net thereof. 9. The system according to claim 4, wherein each said capturing unit respectively is further equipped with a cable severing device arranged and adapted to sever said tether line so as to release said capturing unit from said capture net. 10. The system according to claim 4, wherein said carrier vehicle is further equipped with a first radio, each said capturing unit respectively is further equipped with a second radio, and said first and second radios establish a radio communication link between said carrier vehicle and said respective capturing unit. 11. The system according to claim 10, wherein said carrier vehicle further has a direct radio communication link with a ground control station, and each said capturing unit respectively has only said radio communication link with said carrier vehicle and no direct radio communication link with said ground control station. 12. The system according to claim 4, wherein said at least one braking thrust nozzle is arranged and oriented to produce a thrust vector, upon ignition of said propellant charge, wherein said thrust vector is oriented in a direction opposite said tether line and said capture net and opposite an open end of said capture net. 13. The system according to claim 4, wherein each said capturing unit respectively has no navigation facility and no control system and no controllable thruster for active position and attitude control. 14. The system according to claim 4, wherein said carrier vehicle is further equipped with a navigation unit. 15. A method of capturing and deorbiting an orbital object using the system according to claim 4, comprising steps: a) operating said at least one engine of said carrier vehicle to position said carrier vehicle at a capturing range and a capturing position relative to said orbital object;b) deploying said capture net from a first said capturing unit and capturing said orbital object in said capture net;c) operating said at least one engine of said carrier vehicle to apply tension to said tether line connected to said capture net in which said orbital object is captured, so as to properly orient and stabilize a connected combination including said first capturing unit and said orbital object captured in said net;d) releasing said first capturing unit from said carrier vehicle so that no mechanical connection remains between said first capturing unit and said carrier vehicle; ande) igniting said propellant charge of said first capturing unit so as to produce a braking thrust from said at least one braking thrust nozzle of said first capturing unit, whereby said orbital object captured in said capture net is decelerated in its orbit and deorbited. 16. The method according to claim 15, further comprising, after said step b), deploying said capture net from a second said capturing unit and capturing said orbital object in said capture net of said second capturing unit, in addition to having captured said orbital object in said capture net of said first capturing unit. 17. The method according to claim 16, further comprising releasing said second capturing unit from said carrier vehicle, and combining said first and second capturing units in a series connection. 18. The method according to claim 16, further comprising releasing said second capturing unit from said carrier vehicle, and combining said first and second capturing units in a parallel connection.