Fiber optic rotation sensor for space missionsThe 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.
Document ID
19890022982
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
De Paula, R. P. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Bartman, R. K. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Youmans, B. R. (California Institute of Technology Jet Propulsion Laboratory, Pasadena, United States)
Bogert, G. A. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Minford, W. J. (AT&T Bell Laboratories Allentown, PA, United States)