04825646 is referenced by 46 patents and cites 10 patents.

An axial electrostatic ion thruster for use on a dual-spin stabilized spacecraft is disclosed. The thruster is mounted on the spun portion of the spacecraft and continuously fired for an integral number of spin periods to provide north-south velocity and attitude control. To achieve zero attitude precession with a statically imbalanced despun platform, or an intentional attitude precession generally, the ion thrust is spin-synchronously varied between two non-zero levels to achieve a prescribed Fourier component amplitude and phase at the spin frequency. Modulation of the thrust is achieved with constant ion beam current by complementary modulation of the beam voltage, V.sub.B, and accel voltage, V.sub.A by varying the ion extraction system grid voltages. This varies the thrust while maintaining a constant total accelerating voltage V.sub.TOT =V.sub.B +.vertline.V.sub.A .vertline..

Title
Spacecraft with modulated thrust electrostatic ion thruster and associated method
Application Number
7/41564
Publication Number
4825646
Application Date
April 23, 1987
Publication Date
May 2, 1989
Inventor
Robert L Poeschel
Thousand Oak
CA, US
A Dorian Challoner
Manhattan Beach
CA, US
Agent
A W Karambelas
Mark J Meltzer
Steven M Mitchell
Assignee
Hughes Aircraft Company
CA, US
IPC
H05H 1/16
F03H 1/00
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