Advanced Control Techniques for Control of Rotorcraft Vibration
Abstract
The goal of this project is to develop vibration and control approaches and software suitable for use in the flight tests of the MD-900 helicopter, and to assist Boeing in the preparations for flight test, to enable them to use our advanced control approaches. During this effort, we have studied the feasibility of improving the robustness of X-frame actuator systems using feedback control approaches. We have investigated various feedback control design techniques to find out whether it is feasible to make the actuator robust without sacrificing its performance, and concluded that the flap position control may not be required, and even more, may be counter-productive. We have also improved the system identification methodology to investigate periodic effects, and applied it to the flight test data at Langley. Our analysis of the Langley data shows that periodic effects are negligible, so that periodic control methods are probably not required for vibration control of active rotors. Finally, we have evaluated our advanced continuous-time control system approach to reduce the helicopter vibration using wind tunnel test data at Langley, and found that our approach yields more than 20 dB of vibration reduction at the frequency components of interest.
Document Details
- Document Type
- Technical Report
- Publication Date
- Sep 29, 2003
- Accession Number
- ADA424410
Entities
People
- Steven R. Hall
Organizations
- Massachusetts Institute of Technology