The Viking Mission included the insertion of two unmanned spacecraft into orbit about Mars and the deployment of a soft-lander from each. A description is presented of the adaptive design and implementation of the spacecraft propulsive maneuvers as these flights progressed, taking into account also the inflight results for the orbital phase of the primary Viking mission. The design process included the selection of target parameters and the minimization of both propellant usage and the effects of execution errors, while complying with mission and operational constraints. All maneuvers performed to trim the spacecraft orbits are considered. Attention is given to navigation requirements, geometry definitions and terminology, maneuver mechanization and constraints, and maneuver capability.


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    Title :

    Orbit trim maneuver design and implementation for the 1975 Mars Viking Mission


    Contributors:

    Conference:

    Astrodynamics Conference ; 1978 ; Palo Alto, CA, US


    Publication date :

    1978-08-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :






    Navigation of 1975 Mars Viking mission.

    Kohlhase, C. E. / Grogan, M. M. / Rudd, R. P. | NTRS | 1972