초록 ▼

Spacecraft vehicles and methods for providing reorbiters capable of moving target objects are provided. More particularly, a reorbiter utilizing electrostatic or Coulomb force for acting on target objects and for moving the target objects into new orbits or altitudes are provided. The reorbiter may

Spacecraft vehicles and methods for providing reorbiters capable of moving target objects are provided. More particularly, a reorbiter utilizing electrostatic or Coulomb force for acting on target objects and for moving the target objects into new orbits or altitudes are provided. The reorbiter may establish an electrostatic force by controlling the electrical potential of the reorbiter through active charge emission. The target object may acquire an electrical potential due to its interaction with the space plasma and photoelectrons or the reorbiter may impart additional charge to the target object. After establishing the electrostatic force, a propulsion system of the reorbiter is operated to provide thrust. Thrust is directed to change the orbit and/or position of the target object that is being moved by the electrostatic force between the reorbiter and the target object.

대표청구항 ▼

1. A reorbiter, comprising: an active charge control system, wherein a desired surface potential of the reorbiter is maintained by the charge control system for at least a first time interval while the reorbiter is in space, wherein the reorbiter potential is held at a non-zero value to create an el

1. A reorbiter, comprising: an active charge control system, wherein a desired surface potential of the reorbiter is maintained by the charge control system for at least a first time interval while the reorbiter is in space, wherein the reorbiter potential is held at a non-zero value to create an electrostatic force to allow a target object to be moved by the reorbiter during the first time interval, and wherein the active charge control system establishes an electrostatic force between the reorbiter and the target object; anda propulsion system, wherein a propulsive thrust is provided while the electrostatic force is established to change a location of the reorbiter and the target object. 2. The reorbiter of claim 1, wherein the active charge control system includes an ion source. 3. The reorbiter of claim 1, wherein the active charge control system includes an electron source. 4. The reorbiter of claim 1, wherein the active charge control system and the propulsion system include a shared ion source. 5. The reorbiter of claim 1, wherein the active charge control system and the propulsion system include a shared electron source. 6. The reorbiter of claim 1, wherein the active charge control system and the propulsion system include a shared ion source and a shared electron source. 7. The reorbiter of claim 1, wherein the active charge control system includes an ion emitter. 8. The reorbiter of claim 1, wherein the propulsion system includes an engine. 9. The reorbiter of claim 1, further comprising: a reorbiter charge sensor, wherein the reorbiter charge sensor is operable to determine a potential of the reorbiter. 10. The reorbiter of claim 1, wherein the location is a formation center of mass of the reorbiter and the target object. 11. A method for changing an altitude of a target spacecraft, comprising: placing a reorbiter into proximity with a target object;controlling an electrical potential of the reorbiter, wherein the electrical potential of the reorbiter is set to a charge polarity to create at least one of an attractive force and a repulsive force between the reorbiter and the target object;after establishing the electrostatic force between the reorbiter and the target object, applying a propulsive force, wherein the propulsive force is applied while the at least one of an attractive force and a repulsive force is established to change an altitude of the target object. 12. The method of claim 11, further comprising: sensing an electrical potential of the reorbiter. 13. The method of claim 11, further comprising: estimating an electrical potential of the target object by determining a relative motion response from a separation distance between the reorbiter and the target object. 14. The method of claim 11, further comprising: changing an absolute electrical potential of the target object by controlling the charge of the target object. 15. The method of claim 11, wherein controlling an electrical potential of the reorbiter includes at least one of: emitting positive ions from the reorbiter;emitting negative electrons from the reorbiter. 16. The method of claim 11, wherein applying a propulsive force includes operating an engine. 17. The method of claim 11, wherein controlling an electrical potential of the reorbiter includes emitting positive ions from an ion emitter provided as part of the reorbiter, and wherein applying a propulsive force includes emitting positive ions from the ion emitter. 18. The method of claim 11, wherein the altitude of the reorbiter and the target object is changed to a higher altitude over a plurality of orbital periods about the Earth. 19. The method of claim 11, wherein controlling the electrical potential of the reorbiter includes: sensing a potential of the reorbiter;activating a charge emitter to alter the electrical potential of the reorbiter. 20. A reorbiting system, comprising: a reorbiter, the reorbiter including: an active charge control system;a propulsion system;a target object, wherein the active charge control system of the reorbiter is operated to establish an electrostatic force between the reorbiter and the target object, and wherein the propulsion system of the reorbiter is operable while the active charge control system is established to move the reorbiter and the target object. 21. The system of claim 20, wherein the propulsion system includes an engine.