Nonlinear Large Amplitude Vibration of Composite Helicopter Rotor Blade at Large Static Deflection
Abstract
The nonlinear, large amplitude free vibration of compo site helicopter blades under large static deflection is investigated analytically. A new model capable of handling large amplitudes as well as large deflections was developed, based on the work in a previous report by Minguet. The model can deal with large displacements and rotations by use of Euler angles and can account for structural couplings such as bending-twist and extension-twist. The reduction of this large deflection model to a commonly used moderate deflection model is also shown. A Newton-Raphson type iterative solution technique based on numerical integration of the basic large deflection equations is seen effective for the present analysis. It is found that both large static deflection and large amplitudes can affect the fore-and-aft and torsion modes significantly, but bending modes are not influenced much by the geometrical nonlinearities. (js)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 25, 1990
- Accession Number
- ADA227933
Entities
People
- John Dugundji
- Taehyoun Kim
Organizations
- Massachusetts Institute of Technology