Abstract
The segment control of active twist rotor is investigated to evaluate the effectiveness in rotor power reduction. A numerical model for predicting the isolated rotor power and loads in steady level flights is deployed and validated. A parametric sweep of the amplitude and phase angle for uniform single-harmonic active twist control is conducted to demonstrate the mechanism of active twist control in rotor power reduction. The optimal control schedules and segment layouts of the segment twist control for power reduction while considering saturation limits are obtained using an optimization framework based on genetic algorithm. Up to 5-seg configuration is considered. The results indicate that the segment twist control reduces the rotor power more than the uniform twist control by applying divergent control schedules to each segment. The load distribution of the rotor disk is harmonized in both circumferential and spanwise directions. The 2-seg and 3-seg control configurations are appropriate, while the configurations with more segments yield limited benefits and they may be penalized with an increase in system complexity.
Highlights
In the last decades, the demand for helicopter performance indicators, such as lower required power, greater cargo capacity, lower vibration, higher speed, and lower noise, has been increasing
The results from uniform twist control and segment twist control studies are presented
The results for optimal segment twist control are discussed and compared with those that were obtained for uniform twist control
Summary
The demand for helicopter performance indicators, such as lower required power, greater cargo capacity, lower vibration, higher speed, and lower noise, has been increasing. As an improved form of HHC, the Individual Blade Control (IBC) showed significant potential in rotor performance improvement [12,13]. With the development of active materials and structures, ATR has been studied as an emerging approach for enhancing the helicopter performance and reducing vibration and noise. Sci. 2021, 11, x FOR PEER REVIEtWhe lift force and drag force of the blade section in frame B, C( ) is the coefficient, r4isoft2h5e dimensionless spanwise location of the blade section, R is the radius of the rotor, and the δ is the induced angle of the blade section. The load integral of all blades is performed in order to obtain the forces and moments of the hub transferred by the hinges.
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