| Citation: | CHEN Jinhe, SUO Qian, ZHANG Wei, et al. Influence of rigid rotor parameters on longitudinal dynamic stability[J]. Journal of Aerospace Power, 2025, 40（12）：20240847 doi: 10.13224/j.cnki.jasp.20240847
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The longitudinal dynamic stability characteristics of a coaxial rigid rotor helicopter in forward flight are greatly affected by the rotor design parameters. The main design parameters of advancing blade concept rotor were calculated and analyzed. CAMRAD Ⅱ was used to establish XH-59A coaxial high speed helicopter model. The effects of rotor blade flapping frequency, pitch-flapping, blade mass distribution, the position between blade center of gravity-aerodynamic center (CG-AC) and torsional stiffness on the longitudinal long period modes of coaxial helicopter were analyzed. The results showed that: the higher flapping frequency of a rigid blade indicated the stronger rotor angle-of-attack instability and increased with forward flight speed. Positive pitch-flap coupling, large flapping inertia moment and center of gravity (CG) located in front of aerodynamic center (AC) effectively reduced angle of attack instability for rigid rotor and improved the longitudinal dynamic stability of the helicopter; the large torsional stiffness suppressed the blade torsional modes, thus suppressing the influence of the blade CG-AC on the longitudinal long-period modes.
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