An iterative computation method for nonlinear forced vibration equation on helicopter blade aerodynamic load is given.
介绍用迭代方法求解直升机桨叶气动载荷中的非线性强迫振动方程。
Based on the nonlinear information fusion theorem, an iterative fusion estimation method with small computation cost was derived.
基于非线性信息融合估计定理，推导出一种计算简单的迭代型非线性滤波方法。
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