Application of H∞ control to pitch autopilot ofmissiles

Yang S.M.; Huang N.H.

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Application of H∞ control to pitch autopilot ofmissiles

机译：H∞控制在导弹俯仰自动驾驶仪中的应用

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The pitch rate control of a missile is analyzed by an H∞ controller. The system dynamics governing the aerodynamic stability derivatives and airframe structure vibration is formulated in a generalized state space realization form. This formulation facilitates the γ-iteration method in solving the associated Ricatti equation of the 4-block H∞ control problem. It is shown that the H∞ controller, because of its loop shaping capabilities, can provide improved tracking performance and stability robustness compared with H2 (linear-quadratic-Gaussian (LQG)) and classical proportional-integral-derivative (PID) controller in the rigid airframe model. When airframe flexibility effect is considered, the H∞ controller is also shown to be robust under structure natural frequency variations

机译：用H∞控制器分析导弹的俯仰率控制。以广义状态空间实现形式来表述控制空气动力学稳定性导数和机身结构振动的系统动力学。该公式有助于γ迭代法求解4块H∞控制问题的相关Ricatti方程。结果表明，与H2（线性二次高斯（LQG））和经典比例积分微分（PID）控制器相比，H∞控制器具有环路整形功能，因此可以提供改进的跟踪性能和稳定性。刚性机身模型。考虑机身柔性效应时，H∞控制器在结构固有频率变化下也表现出较强的鲁棒性

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来源
《IEEE Transactions on Aerospace and Electronic Systems》 |1996年第1期|p.426-433|共8页
作者
Yang S.M.; Huang N.H.;
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原文格式 PDF
正文语种 eng
中图分类航空;
关键词
H∞ control; Riccati equations; attitude control; boundary-value problems; closed loop systems; control system synthesis; flexible structures; missile control; multivariable control systems; robust control; state feedback; state-space methods; γ-iteratio;

机译：H∞控制;Riccati方程;姿态控制;边值问题;闭环系统;控制系统综合;柔性结构;导弹控制;多变量控制系统;鲁棒控制;状态反馈;状态空间方法;γ迭代;

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专利

1. Application of H/sup /spl infin// control to pitch autopilot of missiles [J] . Yang S.M., Huang N.H. IEEE Transactions on Aerospace and Electronic Systems . 1996,第1期

机译：H / sup / spl infin //控制在导弹俯仰自动驾驶仪中的应用
2. Roll-pitch-yaw autopilot design for nonlinear time-varying missile using partial state observer based global fast terminal sliding mode control [J] . Ahmed Awad, Wang Haoping 中国航空学报（英文版） . 2016,第005期

机译：基于局部状态观测器的全局快速终端滑模控制的非线性时变导弹横滚偏航自动驾驶仪设计
3. An indirect adaptive predictive control for the pitch channel autopilot of a flight system [J] . Salahshoor Karim, Khaki-Sedigh Ali, Sarhadi Pouria Aerospace science and technology . 2015,第SEPa期

机译：飞行系统俯仰通道自动驾驶仪的间接自适应预测控制
4. Gain-scheduling control design in the presence of hidden coupling terms via eigenstructure assignment: Application to a pitch-axis missile autopilot [C] . H. Lhachemi, D. Saussié, G. Zhu American Control Conference . 2016

机译：通过本征结构分配在存在隐含耦合项的情况下进行增益调度控制设计：应用于俯仰轴导弹自动驾驶仪
5. Adaptive control of linear time-varying systems with applications to missile autopilots. [D] . Song, Chanho. 1989

机译：线性时变系统的自适应控制及其在导弹自动驾驶仪上的应用。
6. Application programming in C# environment with recorded user software interactions and its application in autopilot of VMAT/IMRT treatment planning [O] . Henry Wang, Lei Xing 2016

机译：具有记录的用户软件交互的C＃环境中的应用程序编程及其在VMAT / IMRT治疗计划自动驾驶中的应用
7. Roll-pitch-yaw autopilot design for nonlinear time-varying missile using partial state observer based global fast terminal sliding mode control [O] . Awad Ahmed, Wang Haoping 2016

机译：基于局部状态观测器的全局快速终端滑模控制的非线性时变导弹横滚偏航自动驾驶仪设计
8. Analysis of Two Nonlinear Flight Control Systems. Part I. Liapounov-Lurje Approach to a Simplified Pitch Rate Autopilot. Part II. Analysis of a High-Gain Adaptive Pitch Rate Autopilot [R] . Alex, T. R. 1964

机译：两种非线性飞行控制系统的分析。第一部分.Liapounov-Lurje简化俯仰率自动驾驶仪的方法。第二部分。高增益自适应变桨速率自动驾驶仪的分析

Application of H∞ control to pitch autopilot ofmissiles

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