This report presents the results of a helicopter tiedown test program. The primary purpose of this test was to evaluate a roller gear transmission in an aircraft installation and to conduct a 50-hour tiedown test at a power spectrum equivalent to helicopter military usage. The roller gear transmission transmits 3,000 hp at 203 rpm to a helicopter main rotor head. The transmission is powered by two General Electric axial-flow turboshaft engines, each producing 1,870 hp at 18,966 rpm. A 19.85:1 roller gear unit is the final reduction stage in the transmission.


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    Title :

    3000-HP Roller Gear Transmission Development Program. Volume V. Aircraft Tiedown Testing


    Contributors:
    G. F. Gardner (author) / D. O. Adams (author)

    Publication date :

    1975


    Size :

    150 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English