电控旋翼气弹设计参数研究

Aeroelastic Parameter Design for Electrical Controlled Rotor

以有限元旋翼气弹分析程序 LORA0 1为基础 ,建立了电控旋翼的气弹分析模型 ,给出了一种有效的旋翼 /襟翼耦合配平方法。以此为基础 ,选取改造后的 SA3 49旋翼为基准旋翼 ,对电控旋翼的若干设计参数进行了分析研究。这些参数包括 :桨叶预安装角、桨根弹簧扭转刚度、襟翼长度、襟翼中点径向位置、襟翼弦长比以及襟翼移轴补偿率。通过参数分析得到适宜的取值范围 ,可作为电控旋翼设计的理论基础。

A comprehensive rotor finite element aeroelastic code based on LORA01 is used to analyze the electrical controlled rotor (ECR), or is called swashplateless rotor. A new rotor/flap couple trim method is constructed to get the flap control magnitude. Taking the modified SA349 helicopter rotor as the baseline rotor, parametric design study is conducted for the ECR. The parameters are blade pre-pitch angle, blade root spring stiffness, flap length, flap location, flap chord ration, and overhang ration. Results show that moderate blade pre-pitch angle reduces the flap deflections, and keeps reasonable flap hinge moment. Lowering the blade root spring stiffness leads to smaller flap hinge moment. Increasing the flap length and moving the flap towards blade tip improve the flap control effectiveness. Moderate flap chord ration may be used for both control authority and flap hinge moment, 0 25 is recommended. Increasing the flap overhang ration has nearly no effect on flap control effectiveness, but can greatly reduce the flap hinge moment.