基于试飞的直升机悬停状态地面效应

提出了一种基于试飞的直升机悬停状态地面效应研究方法,该方法在建立无量纲形式的直升机悬停需用功率模型的基础上,通过飞行试验实测直升机在不同重量和不同离地高度悬停时的发动机扭矩、大气条件等参数,利用参数辨识的方法确定无量纲形式直升机悬停需用功率模型中的相关空气动力参数及地面效应模型.采用本文所述方法可以方便地进行直升机有、无地效时的悬停性能拓展.

Helicopter Hover Ground Effect Based on Flight Test

A method for identifying the ground effect is proposed by flight tests and a non-dimensional model of helicopter required power suitable for helicopter inground effeet(IGE) is developed. Flight tests are conducted, and the corresponding data are measured and processed for different combinations of the weight, the height and atmospheric conditions. A parameter identification algorithm for the flight test data analysis is discussed and the identified results are obtained. Based on the identified aerodynamic parameters, the ground effect model for helicopter IGE is established. Results show that the method can identify the helicopter ground effect and the aerodynamic parameters of the helicopter in hover.