飞机结冰后非线性气动力建模及动态响应特性研究

摘要

当前结冰后的动力学仿真主要基于线性气动力模型及结冰影响模型进行,对于结冰后非线性气动力模型的研究较少,然而这对于飞机结冰后在大迎角等非线性区域的动力学分析极为重要.研究了飞机结冰后的非线性气动力模型,将结冰后线性气动力模型的估算方法扩展到非线性气动力模型上,并在结冰后大迎角区域风洞试验数据的基础之上,对失速及过失速区的气动参数变化进行修正.研究了飞机在不同升降舵脉冲信号作用下的动态响应.仿真结果表明,计算结果能够较好地反映飞机在结冰状态下的动力学特性,提出的非线性结冰影响模型能够为结冰条件下研究飞机失速及过失速区域的动力学特性提供理论支撑.%Current flight dynamic researches are commonly based on linear aerodynamics and icing effect model. Researches on nonlinear aerodynamics modeling in icing conditions are relatively rare,however,nonlinear model is of great importance in flight dynamics analysis especially in high angle of attack regions.The paper proposes the linear aerodynamics model to a nonlinear aerodynamics model considering the icing effect in icing conditions.Corrections are presented to modify the aerodynamics parameters of stall and post-stall region based on the wind tunnel test results in a wide range of angles of attack.Dynamic response of different elevator impulse is investigated.Simulation results show that the proposed model can reflect the flight characteristics of the aircraft in icing conditions,and provides a theoretical support for nonlinear flight dynamic research in stall and post-stall region.