Voyager spacecraft attitude control propulsion system post-launch performance requirements changes

Abstract

A test program aimed at the re-qualification of the 0.2-lbf attitude control thruster of the Voyager 2 spacecraft was carried out while the spacecraft was in flight on an interplanetary trajectory to Uranus. The objective of the program was to determine if the 0.2-lbf thruster could be successfully and repeatedly fired at pulse widths of less than the standard minimum pulse width of 10 milliseconds with no degradation. It was demonstrated that the thruster was qualified for short pulse operation at pulse widths of 4 ms or greater. Pulse widths of 4.0 ms provide an impulse bit of approximately 45 percent of the impulse provided by a 10-ms pulse, and the pulse-to-pulse and unit-to-unit variation is approximately plus or minus 10 percent.