应用前行桨叶概念的共轴刚性旋翼高速直升机具有较高的最大飞行速度，但共轴刚性旋翼与推力桨的配合带来了操纵冗余问题，本文以提升高速直升机飞行性能为目标，开展了旋翼/推力桨操纵策略影响分析。首先，建立了一套用于共轴刚性旋翼、推力桨与机身气动力预测的高精度计算流体力学（CFD）方法；其次，提出了CFD-代理模型（SM）-遗传算法（GA）结合的共轴刚性旋翼/推力桨冗余操纵鲁棒配平方法。在此基础上，开展了旋翼/推力桨前向拉力分配、旋翼升力偏置量和机身姿态等操纵策略对高速直升机飞行性能的影响分析，获得了能够有效提升高速直升机最大前飞速度、实用升限的操纵策略。结果表明：固定机身俯仰角前飞时，旋翼分配小部分前向拉力可以提升高速直升机最大平飞速度，最大可提升10.78%；在海平面飞行时，旋翼升力偏置量为0.3，直升机具有最大前飞速度，升力偏置量为0.2，直升机实用升限最大；机身俯仰角为-1°时，高速直升具有最大前飞速度和实用升限，俯仰角过大或过小都会降低前飞性能。

The coaxial rigid rotor high-speed helicopter based on the forward blade concept has a high maximum flight speed， but the cooperation of the coaxial rigid rotor and the propellor brings the problem of handling redundancy. To improve the flight performance of the high-speed helicopter， this paper carries out the analysis of the influence of the rotor/thrust blade control strategy. Firstly， a high-precision Computational Fluid Dynamics （CFD） method for predicting the aerodynamic forces of coaxial rigid rotor， propellor and fuselage is established. Secondly， a robust trim method for redundant control of coaxial rigid rotor/propellor is proposed based on CFD-Surrogate Model （SM）-Genetic Algorithm （GA）. On this basis， the influence of control strategies such as rotor/propellor forward thrust distribution， rotor lift offset and fuselage attitude on the flight performance of high-speed helicopter is analyzed， and the control strategies that can effectively improve the maximum forward flight speed and practical lift limit of high-speed helicopter are obtained. The results show that with fixed fuselage pitch angle， the maximum horizontal flight speed of the high-speed helicopter can be increased by 10.78% when a small part of the forward thrust is distributed by the rotor. When flying at sea level， the helicopter has the maximum forward speed when the lift offset of the rotor is 0.3， and has the maximum service ceiling when the lift offset is 0.2. When the fuselage pitch angle is -1°， the high-speed helicopter has the maximum forward flight speed and service ceiling. If the fuselage pitch angle is too large or too small， the forward flight performance will be reduced.