Abstract
The previous study on modelling of the flapping wing micro air vehicle used to concentrate on thecomplicated aerodynamic computation and the research on the dynamic simulation is often constrained to frequently use the oversimplified 6-degree of freedom (DOF) rigid body equations. However, the motion of the wing is seriously interfered with the body's motion. The aforementioned 6-DOF single rigid body equations do not take the inertial coupling effects into account during the whole flight. For this sake, the article established an available simulation model in the form of multi-body dynamic equation. First, by applying Newton's laws and angular momentum theorem to the vehicle, the multi-body dynamic equation can be deduced. Then, a dynamic model is built under the circumstance of Matlab/Simulink. Finally, the modelling is verified against the data of the wind tunnel tests from the laboratory and the feedback of the real flight tests.
| Original language | English |
|---|---|
| Pages (from-to) | 885-890 |
| Number of pages | 6 |
| Journal | Procedia Engineering |
| Volume | 99 |
| DOIs | |
| State | Published - 2015 |
| Event | Asia-Pacific International Symposium on Aerospace Technology, APISAT 2014 - Shanghai, China Duration: 24 Sep 2014 → 26 Sep 2014 |
Keywords
- flapping wing
- flight dynamics
- multi-body dynamic
- simulation