This report describes a helicopter vibration analysis method. In the method the rotor forcing for a single main rotor is calculated by integrating the forces and moments at the rotor center, and then applying them to a rigid helicopter airframe. The vibrations (any place in the airframe) are calculated as the to the applied hub center forces and moments. The method of analysis allows for dissimilar blades in the main rotor to simulate various type of blade damage and the resulting increase vibrations transmitted into the airframe. The analysis method is generic and can be used to analyze any single main rotor helicopter. An application is made for the UH-60A helicopter, resulting from the loss of outboard sections of one blade of the rotor, and the resulting vibrations in the cockpit are calculated.... Rotor blades, aerodynamic forces, Vibrations, Helicopters, Vibration analysis.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Helicopter Forced Response Vibration Analysis Method RTVIB20


    Contributors:
    J. Fries (author)

    Publication date :

    1993


    Size :

    36 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Forced landing by helicopter

    Brie, R. | Engineering Index Backfile | 1946



    Helicopter vibration

    Prouty, W.R. | Tema Archive | 1988


    Unmanned helicopter forced landing emergency parachute

    CHEN LUODAN | European Patent Office | 2021

    Free access

    Helicopter Vibration Isolation

    KELLEY, BARTRAM | SAE Technical Papers | 1948