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不论是现代高机动隐身战斗机的设计需求还是常规布局飞机的飞行动力学分析,深入研究大迎角飞行时的非线性非定常气动力模型都极其重要。基于纵向运动小振幅及大振幅强迫振荡试验数据,分析了常规稳定导数模型的准确性,并从导数模型出发发展了简化涡流和分离流时间迟滞效应的非定常气动力线性模型和非线性模型,最后应用风洞典型机动历程模拟试验验证了模型的有效性。结果表明:对于复杂构型高机动飞机模型,发展并改进的非线性微分方程模型可以准确预测飞机不同机动下的非定常气动力特性,具有较强的工程可行性。
Whether it is the design requirements of modern high mobility stealth fighter or the flight dynamics of conventional layout aircraft, it is very important to study the nonlinear unsteady aerodynamic model in flight at high attack angle. Based on the small amplitude and large amplitude forced oscillation test data of longitudinal motion, the accuracy of the conventional steady derivative model is analyzed. Based on the derivative model, the unsteady aerodynamic linear model and nonlinear model of simplified vortex and separation flow time lag effect are developed. At last, the validity of the model is verified by the simulation experiment of the wind tunnel typical maneuver. The results show that the developed and improved nonlinear differential equation model can accurately predict the unsteady aerodynamic characteristics of aircraft with different maneuvers, and has strong engineering feasibility for complex configurations of high-performance aircraft models.