直升机旋翼功率传递系数确定方法

Identification of Helicopter Rotor Power Transfer Coefficient

提出了一种确定直升机平直飞行时旋翼功率传递系数的方法;首先,通过飞行力学中的配平计算得到直升机在不同飞行速度下旋翼和尾桨的需用功率;然后,用试飞实测方法确定除旋翼和尾桨外的功率损耗;最终,得到直升机在不同飞行速度下的旋翼功率传递系数。结果表明：由于旋翼、尾桨的需用功率由飞行力学的配平方法得到,能合理地反映飞行状态和直升机尾部构型等影响因素,加上除旋翼和尾桨外的功率由试飞实测得到,因而文中所述的直升机旋翼功率传递系数能更准确地反映直升机的功率传递关系。

A method of helicopter rotor power transfer coefficient determination was presented. Firstly, the trim calculation was conducted at various forward speeds to determine the main rotor and tail rotor powers. Then the additional power consumed by accessories other than main and tail rotors was identified by flight test. The variation of rotor power transfer coefficient with forward speed was obtained according to the powers in corresponding forward speed. The result was improved since the rotor transfer coefficient was determined based on the powers in flight. In Addition, the method described in this paper can consider the effect of vertical empennage and different tail rotor type such as ducted tail rotor.