现代军机大迎角区域性能对空中作战优势的建立有着重要影响，针对大迎角区域建立合适的数学模型对于飞行仿真、稳定性分析和控制律设计都有着重要作用，并且对于解决飞行安全问题和研究飞机失速和尾旋问题具有重要意义。针对小展弦比飞翼标模的迟滞特性，对状态空间模型进行改进，应用大振幅强迫振荡试验数据建立了非定常气动力模型，采用风洞典型机动模拟试验验证状态空间模型的有效性和适用性。结果表明：本文发展并改进的状态空间模型能够准确预测小展弦比飞翼标模不同机动下的非定常气动力特性，具有较强的工程实用性。
The performance of modern military aircraft in areas of high angles of attack has an important influence on the establishment of air combat advantage. The establishment of suitable mathematical models for the high angle of attack area plays an important role in flight simulation, stability analysis and control law design. The state space model is modified to address the hysteresis characteristic of the low aspect ratio flying wing model. The unsteady aerodynamic model is established using the large-amplitude forced oscillation test data. The results show that the state space model developed and improved in this paper can accurately predict the unsteady aerodynamic characteristics of aircraft under different maneuvers and has high engineering practicability.
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