The current status of a program to develop the fiberoptic rotation Sensor (FORS) as an alternative to spinning mass gyros for space applications is briefly reviewed. In particular, the FORS being developed now for use in the inertial reference units of the Mariner Mark II series of planetary exploration spacecraft is described. The requirements for a FORS-based inertial reference unit appropriate to the Comet Rendezvous/Asteroid Fly-by missions are examined, and the general design of the instrument is discussed. Some results of preliminary tests are presented.
Fiber optic rotation sensor for space missions
Fiber Optic and Laser Sensors V ; 1987 ; San Diego, CA, United States
01.01.1988
Aufsatz (Konferenz)
Keine Angabe
Englisch
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