Abstract: Spacecraft maneuvers (e.g., orbit transferring, stationkeeping and attitude controlling) of a first spacecraft are realized with conventional force and torque generators (e.g., thrusters and momentum wheels). Spacecraft maneuvers of a second spacecraft are realized through magnetic interaction between the first and second spacecraft using a closed loop control system. In particular, a magnetic moment vector m1 of a magnetic system of the first spacecraft and a magnetic moment vector m2 of a magnetic system of the second spacecraft are adjusted to apply selected force vectors and torque vectors to the first and second spacecraft using a closed loop control system.

Abstract: A satellite assembly 10 is provided, including an RF radiating element 12 including a plurality of RF choke elements 18, each of said plurality of RF choke elements 18 being defined by an RF dimensional set 20 including an RF depth 22 and an RF width 24. The satellite assembly 10 further includes a null aperture field zone 26 created by the plurality of RF choke elements 18, the null aperture field zone 26 created by tuning each of the RF dimensional sets 20. At least one field sensitive component 14 is positioned within said null aperture field zone 26.

Abstract: An electrical ground (10) for use in a spacecraft comprising, a first surface (12) capable of emitting electrons by photoemission, at least one isolated conductive surface (18) and at least one conductive connector (20) in connection with the first surface (12) and the isolated conductive surface (18) such that excess electrical charge developed in the isolated conductive surface (18) is dispersed into the first surface (12).