Abstract
Instead of using conventional flaps to generate torques, we explore the feasibility of applying micromachined actuators to controlling leading-edge vortices, and, consequently, providing sufficient moments for flight control. We introduce micro balloon actuator, whose working principles, balloon membrane material, dimensions and processing of balloon membrane are described. Micro balloon actuator is 8 mm × 2 mm × (100-150 μm). The principles of flow control are derived. The delta wing leading-edge vortices and principles of generation of controlling torques are proposed. Numerical simulations of delta wing and the effect of positions of micro actuators on rolling moment are carried out. The results show that the control capability of micro actuator is acceptable. Micro balloon actuators can generate an additional moment for the flight control of aircraft.
| Original language | English |
|---|---|
| Pages (from-to) | 487-491 |
| Number of pages | 5 |
| Journal | Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University |
| Volume | 24 |
| Issue number | 4 |
| State | Published - Aug 2006 |
Keywords
- Delta wing
- Leading-edge vortex
- MEMS (Micro-Electro-Mechanical System)
- Micro actuator