The solution of nonlinear algebraic equations is usually met in the study of flight dynamics.
飞行动力学研究中常遇到求解非线性代数方程组的问题。
According to the demand of flight control system, a nonlinear dynamics model with considerable aerodynamic forces and moments for a large maneuver re entry missile head is built.
根据飞行控制要求，考虑了影响较大的气动力和气动力矩因素，建立了一个完全表征大机动情况下弹头运动的非线性动力学模型。
Based on 12-state nonlinear aircraft dynamic model, a nonlinear flight control law is designed by using nonlinear inverse dynamics and modern optimal control theory.
针对12维非线性飞机动力学模型，利用非线性逆系统理论和现代最优控制理论设计了一组非线性飞行控制规律。
Based on 12-state nonlinear aircraft dynamic model, a nonlinear flight control law is designed by using nonlinear inverse dynamics and modern optimal control theory.
针对12维非线性飞机动力学模型，利用非线性逆系统理论和现代最优控制理论设计了一组非线性飞行控制规律。
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