Computation of Guidance Gains for Nonlinear Flight Trajectory Tracking Control System.
Computation of Guidance Gains for Nonlinear Flight Trajectory Tracking Control System.
复制标题
非线性飞行轨迹跟踪控制系统制导增益的计算。
DOI：
10.2322/jjsass.47.449
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发表时间：
1999
期刊：
影响因子：
--
通讯作者：
H. Takano
中科院分区：
文献类型：
--
作者：
Y. Baba;H. Takano
引导飞行器沿所需轨迹飞行的引导力由两部分组成。一个是编程运动所需的力，另一个是消除制导误差的力，这在很大程度上取决于制导误差校正增益的大小，即制导增益。本文利用小扰动理论，计算了自动驾驶仪的增益随动力学参数的变化关系。最后通过仿真验证了本文所计算的制导增益的有效性。
The guidance force, which guides an aircraft on the desired trajectory, consists of two parts. One is the force necessary for programming motion and the other is the force to eliminate the guidance errors, which depends significantly on the magnitude of the guidance error correction gains, that is, guidance gains. In this paper, using small perturbation theory, the gains are computed as the functions of the parameters of the dynamics for the autopilot. Finally the simulation results show the effectiveness of the guidance gains computed in this paper.