An air data computer senses acceleration and rotational rate of an aircraft with an inertial sensor assembly of the air data computer. The air data computer determines first attitude information of the aircraft based on the acceleration and rotational rate sensed with the inertial sensor assembly. The air data computer receives second attitude information of the aircraft from a source external to the air data computer, and determines attitude correction values based on the first attitude information and the second attitude information. The air data computer applies the attitude correction values to the first attitude information to produce error-corrected attitude information that is output from the air data computer.


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    Title :

    AIR DATA ATTITUDE REFERENCE SYSTEM


    Contributors:

    Publication date :

    2018-10-18


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    G01C Messen von Entfernungen, Höhen, Neigungen oder Richtungen , MEASURING DISTANCES, LEVELS OR BEARINGS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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