An analytical study, which is based on calculations from a rotorcraft comprehensive analysis of a notional coaxial rotor system in isolation, is presented to improve understanding of the aeromechanics of lift-offset coaxial rotors. The calculations include a trim analysis that enforces a fixed value for coaxial system lift in order to isolate the effect of lift offset. The quantities examined here are the blade pitch controls, coaxial system performance, blade airloads, blade structural loads, and coaxial system hub loads. Operating conditions examined form airspeed sweeps for four different values of lift offset. The maximum airspeed that the rotor may achieve trim is increased by increasing lift offset. For a given airspeed, increasing lift offset generally increases the coaxial system lift-to-effective-drag ratio as a result of a decrease in shaft power (despite an increase in drag power). Increasing lift offset decreases half peak-to-peak values of pitch link force, torsion moment, and in many cases, chord bending moment. While increasing lift offset increases half peak-to-peak flap bending moment for sufficiently low airspeeds, it may decrease this quantity for higher airspeeds. Lastly, increasing lift offset generally decreases the fixed-frame, vibratory, system hub longitudinal force and pitch moment.

提出了一项分析研究，该研究基于旋翼航空器对孤立的概念同轴转子系统进行的全面分析而得出的计算结果，目的是增进对偏置偏置同轴转子的空气力学的理解。这些计算包括调整分析，该分析对同轴系统的升程强制采用固定值，以隔离升程偏移的影响。此处检查的数量是叶片桨距控制，同轴系统性能，叶片空气载荷，叶片结构载荷和同轴系统轮毂载荷。从空速扫描中检查了四种不同升程偏移值的运行条件。转子可达到的最大空速可通过增加升程偏移量来增加。对于给定的空速，由于轴功率的减小（尽管阻力增大），增大升程偏移量通常会提高同轴系统的升力对有效阻力比。升力偏移量的增加会减小变桨连杆力，扭转力矩以及许多情况下的弦弯矩的峰峰值的一半。对于足够低的空速，增加升程偏移会增加峰到峰襟翼弯曲力矩的一半，而对于较高的空速，它可能会减少此量。最后，增加升程偏移通常会减小固定框架，振动，系统轮毂的纵向力和俯仰力矩。对于足够低的空速，增加升程偏移会增加峰到峰襟翼弯曲力矩的一半，而对于较高的空速，它可能会减少此量。最后，增加升程偏移通常会减小固定框架，振动，系统轮毂的纵向力和俯仰力矩。对于足够低的空速，增加升程偏移会增加峰到峰襟翼弯曲力矩的一半，而对于较高的空速，它可能会减少此量。最后，增加升程偏移通常会减小固定框架，振动，系统轮毂的纵向力和俯仰力矩。