Abstract
This paper gives a detailed insight into the peculiar problems that the designer of a planetary lander inertial reference unit (IRU) requiring heat sterlization will confront. Solutions for such unanticipated deficiencies as gyro flexlead soldering processes, endstone design, and preconditioning processes, as developed for the Viking (Mars) Lander IRU, are presented. The Viking Lander IRU redundancy implementation is discussed with emphasis placed on the advantages and disadvantages of the scheme used and a description of the electronics mechanization. The Viking Lander IRU realized performance for both Viking Landers is discussed with emphasis given to measurable coefficient stabilities from IRU acceptance through Mars landing.
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