| 飞机俯仰速率信号重构方法研究 |
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| 引用本文： | 李卫琪,陈宗基.飞机俯仰速率信号重构方法研究[J].飞行力学,2004,22(2):26-29. |
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| 作者姓名： | 李卫琪 陈宗基 |
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| 作者单位： | 北京航空航天大学,自动化科学与电气工程学院,北京,100083 |
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| 基金项目： | 国家自然科学基金资助项目(90205011) |
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| 摘 要： | 研究了六自由度非线性方程描述的飞机在俯仰速率传感器故障情况下的信号重构方法。给出了两种重构方法，一种是通过建立等效的线性模型，设计线性状态观测器重构状态信号，另一种是使用非线性跟踪微分器方法．通过跟踪俯仰角的微分信号来计算俯仰速率信号。仿真结果表明，两种方法都具有一定的可行性。
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| 关 键 词： | 状态观测器 跟踪微分器 信号重构 |
| 文章编号： | 1002-0853(2004)02-0026-04 |
| 修稿时间： | 2003年5月15日 |
Signal Reconfiguration Method for Aircraft's Pitch Angular Rate |
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| LI Wei-qi,CHEN Zong-ji.Signal Reconfiguration Method for Aircraft''''s Pitch Angular Rate[J].Flight Dynamics,2004,22(2):26-29. |
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| Authors: | LI Wei-qi CHEN Zong-ji |
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| Abstract: | The signal reconfiguration of pitch angular rate in the 6 degrees of freedom aircraft model is introduced. Two methods are presented.In the first method, by building an equivalent linear model of the aircraft, the linear state observer could be designed to estimate the states. In the second method, the nonlinear tracking differentiator is applied to producing the differential signal of the pitch angle, which is used to calculate the pitch angular rate. Simulation results were presented to indicate the feasibility of two algorithms. |
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| Keywords: | state observer tracking differentiator signal reconfiguration |
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