This paper addresses the whole process of load determination during the development of the TIGER main rotor system. A short description of the helicopter and the main rotor is followed by a brief presentation of theoretical tools used for predictions and simulations during the design phase. Although the aircraft showed the expected flight properties from the very beginning of testing in 1991, load optimisation was necessary to achieve a longer service life of critical parts and to expand the flight envelope. A hub geometry change from a 2.5 deg. blade droop angle to a central 2.5 deg. hub pre-cone angle was performed in order to expand the load factor capability by lowering loads in lead-lag bending and in the control system. The shaft bending moment limit was enhanced in order to safeguard slope landing capability of the aircraft up to 12 deg. nose-up. Furthermore, the main rotor was tuned for low 4/rev vibrations and reduced 4/rev torque amplitudes in the fixed system. All improvement measures are discussed with respect to essential aeromechanical aspects and are reflected by critical evaluations of the flight test results.


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    Title :

    Survey of TIGER main rotor loads from design to flight test


    Additional title:

    Überblick über die Belastung des TIGER-Hauptrotors vom Entwurf bis zum Flugversuch


    Contributors:

    Published in:

    Publication date :

    2002


    Size :

    12 Seiten, 24 Bilder, 3 Tabellen, 15 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





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