Dynamic Stability Analysis and Control Law Design of Stability Augmentation System for Helicopter
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摘要: 研究了无铰直升机动稳定性、操纵性和控制问题.在动稳定性计算分析的基础上,认识到定常飞行中的非稳定模态和增稳系统设计的必要性.在完成直升机非线性动力学建模之后,经小扰动线化得到直升机飞行控制状态方程,进行了直升机增稳系统等效导数的计算,性能分析和系统阶跃响应仿真.通过稳定性(增稳系统)设计,改善了直升机动稳定性, 其增稳性能满足设计规范中一级动态品质要求.Abstract: Dynamic stability and control laws of a hingeless rotor helicopter were studied. Based on dynamic stability analysis of the helicopter, the unstable mode and the necessity of installation of Stability Augmentation System (SAS) were cognized. The control laws of SAS for helicopter pitching, rolling and yawing motions were presented. Following establishing helicopter flight control state equations, the calculations of effective derivatives, the performance analysis and step response simulation for helicopter SAS were carried out. Through the design of SAS, the helicopter dynamic stability can be improved, the stability augmentation performance can meet the requirements of the first level qualities of the design specifications.
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Key words:
- helicopters /
- stability augmentation systems /
- control law /
- dynamics
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