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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Fiber optic rotation sensor for space missions


    Contributors:

    Conference:

    Fiber Optic and Laser Sensors V ; 1987 ; San Diego, CA, United States


    Publication date :

    1988-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Fiber Optic Rotation Sensor For Space Missions

    De Paula, R . P. / Minford, W. J. / Bartman, R. K. et al. | SPIE | 1988


    Fiber optic rotation sensor for long lifetime space missions

    Dorsky, L. / Bartman, R. / Lehman, D. et al. | NTRS | 1992


    Fiber optic rotation sensor for long lifetime space missions

    Dorsky, Leonard I. / Bartman, Randall K. / Lehman, David H. et al. | SPIE | 1992


    Fiber optic rotation sensor for long lifetime space missions

    Dorsky, L. / Bartman, R. / Lehman, D. et al. | Tema Archive | 1992


    Fiber optic sensors for space missions

    Benussi, L. / Berardis, S. / Bertani, M. et al. | IEEE | 2003