旋翼非定常气动载荷及瞬态气动响应计算  

Computation of Rotor Unsteady Aerodynamic Loads and Transient Aerodynamic Response

作　　者：吕维梁[1] 史勇杰[1] 魏鹏[1] 徐国华[1] 

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室,南京210016

出　　处：《南京航空航天大学学报》2013年第1期21-27,共7页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家自然科学基金(10872094)资助项目

摘　　要：建立了一个用于定常和机动飞行状态下旋翼非定常气动特性计算的数值方法。该方法在时间步进自由尾迹方法的基础上,采用4阶精度的Adams-Bashforth-Moulton预测校正多步法对离散的旋翼尾迹进行求解,耦合了桨叶挥舞运动模型、旋翼配平模型,并采用Beddoes非定常气动模型来模拟桨叶的压缩、气流分离效应。应用该方法,开展了不同状态下旋翼非定常载荷及总距突增时的旋翼瞬态气动响应的计算,并结合试验结果进行了对比分析。结果表明,本文建立的方法不仅可以准确地求解定常飞行时旋翼的非定常气动载荷,捕捉其沿方位角的变化特征,并且也可以准确模拟总距突增时,旋翼的过冲、迟滞等瞬态气动响应过程。A numerical method for calculating the rotor aerodynamic characteristics in steady and manoeuvring flight is established. On the basis of time-marching free wake analysis, this method applies the 4th-order accurate Adams-Bashforth-Moulton predictor-corrector multistep algorithm to calculating the discreted rotor wake. Furthermore, the method also combines the flapping, trim models and the Beddoes unsteady aerodynamic model, which can simulate the compression and separating effect on blades. By the method, for a sample rotor, the unsteady aerodynamic loads in variational flight conditions and the transient aerodynamic response under ramp increase in collective pitch are calculated and analyzed ac- cording to the experimental data. It is shown by the results that the method not only can accurately pre- dict the unsteady aerodynamic rotor loads in steady flight by capturing its variational characteristics along blade azimuthal locations, but also is capable of precisely simulating the transient aerodynamic response such as overshoot and delay phenomenons under ramp increase in collective pitch.

关 键 词：旋翼 自由尾迹 非定常 气动载荷 气动响应 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]