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박욱제,황명신,송용규 한국항공대학교 1998 論文集 Vol.36 No.-
To obtain aircraft dynamic parameters, various estimation methods such as Maximum Likelihood, Linear Regression are applied. In this paper we adopt the extended Kalman filter(EKF) to estimate the stability and control derivatives in aircraft dynamic models from flight test data. The extended Kalman filter is applied to nonlinear augmented system assuming that unknown parameters are additional states. In this work, the results of the extended Kalman filter are compared with those of the wind tunnel test and Modified Maximum Likelihood Estimation(MMLE) using ChangGong-91 aircraft flight test data.