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在准定常假设下,飞机在大迎角或大幅机动飞行时,其气动特性呈现非线性特点.常用基于配平状态下小幅机动飞行辨识所得的线性气动模型已不再适用.为解决这一问题,提出一种飞行数据多重分区方法,通过各区间的局部线性化以表征气动特性的全局非线性.各区间中,针对气动力和力矩系数的静态项、动导数项及控制导数项进行泰勒级数展开,提出一种通用气动模型,并利用最小二乘类方法辨识各项气动参数.根据某现代战斗机仿真飞行试验数据,辨识相关气动参数并与真实值进行比较,结果表明两者吻合较好.试验结果验证了所述飞行数据多重分区方法和通用气动模型的有效性.
Under the quasi-stationary assumption, the aerodynamic characteristics of the aircraft are non-linear at high angles of attack or maneuvering. The linear aerodynamic model commonly used based on small maneuver flight in trim state is no longer applicable. To solve this problem, A multi-partitioning method of flight data is proposed, in which the global nonlinearity of the aerodynamic characteristics is characterized by the local linearization of each interval. In each interval, the static term, the dynamic derivative term and the control derivative term for the aerodynamic forces and moment coefficients are subjected to Taylor series A universal aerodynamic model is proposed and the aerodynamic parameters are identified by the least squares method.According to the data of a modern flight simulator flight test, the relevant aerodynamic parameters are identified and compared with the real values, the results show that the two agree well with each other. The test results validate the effectiveness of the multiple data partitioning method and the general aerodynamic model.