| 飞机结构模态耦合现象的抑制方法 |
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| 引用本文： | 顾计刚,王大勇,马国锋. 飞机结构模态耦合现象的抑制方法[J]. 飞机设计, 2013, 0(6): 53-55,63 |
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| 作者姓名： | 顾计刚 王大勇 马国锋 |
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| 作者单位： | [1]中国人民解放军驻沈阳飞机工业集团有限公司军事代表室,辽宁沈阳110034 [2]沈阳飞机设计研究所,辽宁沈阳110035 |
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| 摘 要： | 某型飞机试飞中出现了高频振荡现象，该振荡属于伺服弹性振荡，产生该振荡的原因是飞控系统对传感器测量的结构弹性频率段的振动信号衰减程度不足。为了抑制该振荡的发生，对主控系统的纵向通道控制律进行了适当的调整，并对调整前后控制系统的频域特性进行仿真对比。在此基础上，进行试飞现象重现并验证控制律更改的有效性，这些仿真表明，控制律更改可以实现对伺服弹性振荡的抑制。
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| 关 键 词： | 伺服弹性振荡 结构滤波器 控制律 参数辨识 |
Preventing Methods of Airplane Structural Mode Coupling |
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| GU Ji-gang,WANG Da-yong,MA Guo-feng. Preventing Methods of Airplane Structural Mode Coupling[J]. Aircraft Design, 2013, 0(6): 53-55,63 |
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| Authors: | GU Ji-gang WANG Da-yong MA Guo-feng |
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| Affiliation: | 1. PLA Military Representative Office in Shenyang Aircraft Industries(group)Co.Ltd., Shenyang 110034, China) (2.Shenyang Aircraft Design ＆ Research Institute, Shenyang 110035, China) |
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| Abstract: | High-frequency oscillation occurred during the flight test of some airplane, this oscillation was servo-elastic oscillation. The cause was that the flight control system hadn＇t attenuated enough the oscillation signal in the structural elastic frequency range. To avoid this oscillation, the longitudinal control law of primary control system and was adequately adjusted. Frequency characteristic of control system was compared between before and after modification. Then, the phenomenon during flight test was repeated and the modification of control law was validated. The simulation indicated that the new control law was able to prevent servo-elastic oscillation. |
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| Keywords: | servo-elastic oscillation structural filter control law parameter identification |
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