Abstract
Actively twisting the entire rotor blade is being investigated as an approach to reduce helicopter vibration and noise. In the present work, an induced shear piezoelectric tube is analytically evaluated as an active blade twist actuator. A finite element model of the induced shear actuator and rotor blade is used to guide the designs of the induced shear tube for small scale and full scale rotor blade applications. The finite element analysis indicates that a 48 inch long tube actuator generates a tip twist of +/-1.1° in a full scale blade and an 18 inch long actuator produces a tip twist of +/-1.40° for a small scale blade. The performance of the induced shear actuator is compared to the state of the art in active twist actuators. The results indicate that the induced shear tube shows promise as an active blade twist actuator.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 1977-1987 |
| Number of pages | 11 |
| Journal | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
| Volume | 3 |
| DOIs | |
| State | Published - 2002 |
| Event | 43rd Structures, Structural Dynamics and Materials Conference - Denver, CO, United States Duration: Apr 22 2002 → Apr 25 2002 |
All Science Journal Classification (ASJC) codes
- Architecture
- General Materials Science
- Aerospace Engineering
- Mechanics of Materials
- Mechanical Engineering