Helicopter Aerodynamic Parameter Identification via Flight Dynamics

Abstract

A method which can process flight test data by integrating parameter identification and non-dimensional flight dynamic model was proposed to acquire the effective aerodynamic parameters of a helicopter. First of all, a non-dimensional mathematic model considering flight dynamics was deduced for a helicopter in state of level flight, and some important parameters including aerodynamic and correctional were developed. Next, taking helicopter Z-9× for example, the least squares method was adopted to identify these parameters based actual flight test data. Lastly, the identification method was proved valid through feasibility analysis. Results show that this method is a good way to acquire aerodynamic parameters and can shorten flight test periods as well.