In this paper, the mathematical model of compatibility check of flight test date is set up based on the kinematic equations with six freedom of aircraft.
本文采用飞行器六自由度运动方程组，建立了飞行试验数据相容性检验的数学模型。
ARMAX model method and subspace-based state space method were used to process the flight flutter test data, and identify the flutter modal parameters of aircraft.
论文使用了现代参数辨识技术的ARMAX模型递推法和状态子空间辨识法，对飞行颤振试验数据进行处理，辨识飞机的颤振模态参数。
The engine model identification using flight test signals is introduced.
利用飞行试验信号对发动机模型辨识进行了研究。
Flight test shows that the confidence of this model is higher.
飞行试验表明此模型具有较高的置信度。
Large amplitude test, Unsteady aerodynamic, Wall influence, dynamic derivative simulating, Mathematic model, Fuzzy logic, Aerodynamicmodeling, Flight simulating.
大振幅试验，非定常空气动力，空气动力模型，洞壁干扰，动导数仿真，数学模型，模糊逻辑，飞行仿真。
This paper presents the methods of free flight spin test and rotation balance test in vertical wind tunnel, the design of test model is briefly expounded.
介绍了立式风洞自由飞尾旋试验和旋转天平试验的方法，简述了试验模型的设计。
According to the generic structural model, specific parameterized models in hover and forward flight are obtained by using the flight test data.
然后依据通用结构模型，利用飞行实测数据，得到悬停和前飞状态下的辨识模型。
The flight test data of some a reentry capsule are analyzed. The results validate the developed mathematical model and algorithm of trajectory reconstruction.
对某飞船返回舱的飞行试验数据进行了计算和分析，结果证实了弹道重建数学模型的正确性和算法的可行性。
It incorporates organically the flight test data and the flutter theory model by the structured singular value theories, to process the flutter boundary estimate.
利用结构奇异值理论将颤振理论模型和试飞数据有机结合起来，进行了颤振边界预测。
Pass to incorporate organically the flight test data and the system model, make use of the structured singular value theories proceed the flutter boundary estimate.
一种新的颤振分析方法——鲁棒颤振裕度法被介绍，它利用结构奇异值理论将系统模型和试飞数据有机结合起来进行颤振边界预测。
Pass to incorporate organically the flight test data and the system model, make use of the structured singular value theories proceed the flutter boundary estimate.
一种新的颤振分析方法——鲁棒颤振裕度法被介绍，它利用结构奇异值理论将系统模型和试飞数据有机结合起来进行颤振边界预测。
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