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The air resonance aeroelastic stability boundaries of a soft‐ in‐plane, hingeless‐rotor helicopter were explored using both an 18‐degree‐of‐freedom analysis and a Froude‐scaled, 28‐in. diameter rotor model. Correlation between
analytical results and test data was excellent in terms of stability boundaries, mode shapes, and frequencies, thus lending credibility to both. Some physical insights of the air resonance phenomenon were gained with both the analysis and the test. Sensitivity of the air resonance stability
to some pertinent design considerations such as the precone of the feathering axis, control system flexibility, and blade in‐plane damping was investigated. Again, the analytical trends agreed well with the test findings. Based on these sensitivities and the insight into the nature
of the air resonance mode, some important design recommendations are made.
The Boeing Company, Vertol Division, Philadelphia, Pennsylvania
Publication date: October 1, 1972
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