Abstract
The armament layout of every military helicopter is decided by the aviation department based on a variety of factors. Amidst a variety of other constraints, the structural behavior plays a vital role in deciding the layout on the helicopter boom. It is necessary to avoid interaction of the rotor blade frequency with that of the natural frequency of the weapon system layout. Vibration analysis was carried out for various configurations, to determine the natural frequencies which are close to that of the rotor blade and therefore avoid them during flight. The finite element analysis followed by impact hammer tests was carried out to confirm the configurations. A passive damping technique is suggested to be adopted for attenuation of the vibrations due to resonance, if any.
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Gopikrishna, R., Kishore Kumar, K., Janarthanan, Y.R. (2022). Dynamic Analysis of Helicopter Boom with Different Payload Configurations. In: Kumar, R., Chauhan, V.S., Talha, M., Pathak, H. (eds) Machines, Mechanism and Robotics. Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-16-0550-5_71
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DOI: https://doi.org/10.1007/978-981-16-0550-5_71
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