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以战斗机俯仰机动为例,建立了飞机大迎角非定常气动力模型,包括非线性代数模型、Fourier函数分析模型、状态空间模型、差分方程模型以及模糊逻辑模型。并用SDM标模大振幅俯仰振荡非定常气动力风洞试验数据对模型参数进行了辨识,验证了模型的有效性。从模型物理意义、参数辨识难易程度及模型通用性和精确度等方面对几种非定常气动力模型进行了比较研究。
Taking fighter pitching maneuver as an example, the unsteady aerodynamic model of aircraft at high angle of attack is established, including nonlinear algebraic model, Fourier function analysis model, state space model, difference equation model and fuzzy logic model. The parameters of the model are identified by using SDM-scale large-amplitude Pseudo-Pneumatic unsteady aerodynamic wind tunnel test data to verify the validity of the model. Several kinds of unsteady aerodynamic models are compared in terms of the physical meaning of the model, the difficulty of parameter identification and the universality and accuracy of the model.