초록 ▼

Systems, apparatuses, and methods for removal of orbital debris are provided. In one embodiment, an apparatus includes a spacecraft control unit configured to guide and navigate the apparatus to a target. The apparatus also includes a dynamic object characterization unit configured to characterize m

Systems, apparatuses, and methods for removal of orbital debris are provided. In one embodiment, an apparatus includes a spacecraft control unit configured to guide and navigate the apparatus to a target. The apparatus also includes a dynamic object characterization unit configured to characterize movement, and a capture feature, of the target. The apparatus further includes a capture and release unit configured to capture a target and deorbit or release the target. The collection of these apparatuses is then employed as multiple, independent and individually operated vehicles launched from a single launch vehicle for the purpose of disposing of multiple debris objects.

대표청구항 ▼

1. A system for removing debris, comprising: a plurality of active debris removal (ADR) vehicles for removing a rocket body, each of the plurality of ADR vehicles are delivered to space by a single launch vehicle and comprise a cowcatcher attached to a front of each of the plurality of ADR vehicles,

1. A system for removing debris, comprising: a plurality of active debris removal (ADR) vehicles for removing a rocket body, each of the plurality of ADR vehicles are delivered to space by a single launch vehicle and comprise a cowcatcher attached to a front of each of the plurality of ADR vehicles, and the cowcatcher configured to protect instruments and mechanisms on each of the plurality of ADr vehicles when entering a nozzle of the rocket body, whereinthe single launch vehicle comprises a payload, the payload comprising the plurality of ADR vehicles,each of the plurality of ADR vehicles is oriented upside down on the payload with respect to the single launch vehicle, andthe cowcatcher for each of the plurality of ADR vehicles is oriented towards a base of the single launch vehicle to transmit launch loads from the single launch vehicle to each of the plurality of ADR vehicles. 2. The system of claim 1, wherein the launch vehicle releases each of the plurality of ADR vehicles in succession. 3. The system of claim 1, wherein each of the plurality of ADR vehicles loiters in orbit until a target plane assigned to the respective vehicle is near the respective vehicle plane. 4. The system of claim 1, wherein each of the plurality of ADR vehicles is further configured to rendezvous with an assigned target. 5. The system of claim 1, wherein each of the plurality of ADR vehicles is further configured to analyze an assigned target prior to capturing the assigned target. 6. The system of claim 5, wherein each of the plurality of ADR vehicles is further configured to capture the assigned target. 7. The system of claim 5, wherein each of the plurality of ADR vehicles is further configured to capture another pre-assigned target when the assigned target is not capturable. 8. The system of claim 1, wherein each of the plurality of ADR vehicles is further configured to deorbit an assigned captured target. 9. The system of claim 1, wherein each of the plurality of ADR vehicles is further configured to deorbit itself when failure to capture the target occurs. 10. The system of claim 1, further comprising: a ground support and operations unit configured to simultaneously plan, navigate and perform operations on each of the plurality of ADR vehicles to capture and deorbit a plurality of targets. 11. The system of claim 1, wherein each of the plurality of ADR vehicles are clustered on the payload, and are independently targeted and independently operated. 12. The system of claim 1, wherein the cowcatcher comprises a gridded frame to protect a corresponding one of the plurality of ADR vehicles when entering the nozzle of the rocket body, andthe gridded frame comprises an outer ring and an inner ring, the outer ring being larger than the inner ring, forming a shape of an internal nozzle of the rocket body.