Terminator tape satellite deorbit module

1. A deorbit device comprising:

a foldable passive-electrodynamic conductive tape that ranges in length from ten to several hundred meters; and

a flat box that is wide enough to accommodate said conductive tape's width so that said foldable passive-electrodynamic conductive tape can be folded to be stowed within said flat box; and

wherein said foldable passive-electrodynamic conductive tape is connected at one end to a spacecraft.

2. The deorbit device of claim 1 further comprising an ejection spring configured to apply force to assist in deployment of said conductive tape.

3. The deorbit device of claim 1 wherein said conductive tape comprises multi-layer insulation (MLI) during the satellite's operation, and then is allowed to deploy or actuated to deploy to serve as a drag device.

4. The deorbit device claim 1 wherein deployment of said conductive tape is accomplished by charging the tape to a high voltage to induce electrostatic repulsion forces that unfold the tape.

5. The deorbit device of claim 1 wherein said conductive tape is perforated.

6. The deorbit device of claim 1 wherein said conductive tape comprises elastic materials that cause said conductive tape to exert force against being folded and facilitate unfolding said conductive tape.

7. The deorbit device of claim 1 wherein said foldable passive-electrodynamic conductive tape is connected at its other end to an endmass.

8. The deorbit device of claim 7 wherein said endmass comprises a cover plate.

9. The deorbit device of claim 1 further comprising a release mechanism.

10. The deorbit device of claim 9 wherein said release mechanism comprises an avionics board.

11. The deorbit device of claim 10 wherein said release mechanism further comprises a polymeric restraint line and a burn-wire that cuts said polymeric restraint line.

12. The deorbit device of claim 10 wherein said release mechanism further comprises a non-explosive actuator pin-puller.

13. The deorbit device of claim 10 wherein said release mechanism further comprises a pyro actuator.

14. The deorbit device of claim 10 wherein said release mechanism further comprises a wax-pellet actuator.

15. The deorbit device of claim 10 wherein said release mechanism further comprises a pneumatic device.

16. The deorbit device of claim 10 wherein said release mechanism further comprises an electric motor.

17. A deorbit device comprising: a foldable active-electrodynamic conductive tape connected at one end to a space craft, wherein said conductive tape further comprises an electron emission device, wherein said foldable active-electrodynamic conductive tape can be folded to fit within a relatively flat box; and

said conductive tape ranges in length from ten to several hundred meters.