Stability margin-based PD attitude control tuning for unstable flight vehicle
Stability margin-based PD attitude control tuning for unstable flight vehicle
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DOI：
10.1080/00207721.2011.600471
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发表时间：
2013-02
影响因子：
4.3
通讯作者：
Chen, Zengqiang
中科院分区：
文献类型：
--
作者：
Sun, Mingwei;Yang, Ruiguang;Wang, Zenghui;Chen, Zengqiang
比例导数（PD）姿态控制在飞行器尤其是助推段的控制中有着广泛的应用。一些飞行动力学是开环不稳定的，这往往限制了可实现的闭环性能。根据小摄动理论得到的线性模型的固有特性，推导出满足增益和相位裕度要求的简单PD姿态控制数值解析整定公式。根据Routh稳定性判据，利用所建立的调谐规则对低频延时进行逼近，得到增益的递减余量。采用一些数值多项式求解方法寻求可行的稳定裕度区域，并在二维平面上显式绘制。考虑到工程实际，还施加了最大增益约束。最后，通过数值算例验证了分析结果。
Proportional-derivative (PD) attitude control is widely used for the flight vehicles, especially in boost phase. Some of the flight dynamics are open-loop unstable, which often limits the achievable closed-loop performance. Based on the intrinsic characteristics of the linear model obtained from the small perturbation theory, simple numerical analytical tuning formulae of PD attitude control are derived to meet the gain and phase margin specifications. According to Routh stability criterion, the decreasing gain margin is obtained by using the approximation of delay amid low frequency with the established tuning rule. Some numerical polynomial solving approaches are employed to seek the feasible stability margin region, which is explicitly plotted in the 2-D plane. Taking engineering practice into account, the maximum gain constraint is also imposed. Finally, several numerical examples are presented to validate the analysis result.
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影响因子：
4.8
作者：
P. Paraskevopoulos;G. Pasgianos;K. Arvanitis
通讯作者：
P. Paraskevopoulos;G. Pasgianos;K. Arvanitis
影响因子：
2.6
作者：
K.W.Han;C.-H. Chang
通讯作者：
K.W.Han;C.-H. Chang
DOI：
10.1049/ip-cta:19982243
发表时间：
1998-09
期刊：
--
影响因子：
--
作者：
W. Ho;W. Xu
通讯作者：
W. Ho;W. Xu
影响因子：
4.3
作者：
A. Rad;W. Lo
通讯作者：
A. Rad;W. Lo
影响因子：
4.3
作者：
N. Tan;D. Atherton
通讯作者：
N. Tan;D. Atherton