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. After establishing helicopter flight control state equations, the calculations of effective derivatives, the performance analysis and step response simulation for SAS were carried out. Through the design of SAS, the helicopter dynamic stability can be improved, and the stability augmentation performance can meet the requirements of the first level qualities of the design specifications.
| Original language | English |
|---|---|
| Pages (from-to) | 636-639 |
| Number of pages | 4 |
| Journal | Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics |
| Volume | 28 |
| Issue number | 6 |
| State | Published - Dec 2002 |
Keywords
- Control law
- Dynamics
- Helicopter
- Stability augmentation system
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