Study shows that for reasonable values of initial-condition errors and equipment biases, resultant position indication errors will not become excessive unless re-entry maneuver time is greater than 45 to 60 min; position indication error caused by accelerometer uncertainties can be reduced by leaving accelerometers off until their output becomes significantly greater than their uncertainty.


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    Title :

    Investigation of errors of inertial guidance system during satellite re-entry


    Additional title:

    NASA -- Tech Note


    Contributors:
    White, J.S. (author)


    Publication date :

    1960


    Size :

    42 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :