科研之友
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摘要
A comprehensive analysis for evaluating performance and vibratory loads of a coaxial helicopter rotor is developed and validated against existing experimental data. The model is extended from the baseline University of Maryland Advanced Rotor Code to include interactional rotor wake between the coaxial rotors, modeling of relative phase between rotors, and trim strategies for a coaxial helicopter. The simulation is used to define a flight envelope for an experimental rotor being developed for testing in the Glenn L. Martin Wind Tunnel. Areas of interest are rotor performance and blade flap bending moments, particularly with variation in lift offset. Control methods and the impact of rotor phase on resulting hub loads are explored. Clearance between the tips of the upper and lower rotor is a limiting factor in testing a lift offset rotor; the impact of blade structural properties on tip clearance are examined. Tip clearance depends on lift offset and thrust but not on advance ratio. It is found that the use of moderate lift offset can improve performance and vibratory loads at the cost of increased blade loads.
- 出版日期2017-7
