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This thesis discusses about modelling and simulation of dynamics system with flapping-wing micro aerial vehicle/ FMAV. Modeling needs to be done in order to know the characteristics of motion of the system. To obtain a mathematical model, performed by the method of approach to a rigid system of mult...
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| 格式: | Final Project |
| 語言: | Indonesia |
| 在線閱讀: | https://digilib.itb.ac.id/gdl/view/15751 |
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| 總結: | This thesis discusses about modelling and simulation of dynamics system with flapping-wing micro aerial vehicle/ FMAV. Modeling needs to be done in order to know the characteristics of motion of the system. To obtain a mathematical model, performed by the method of approach to a rigid system of multiple objects (multiple rigid body) and Newton's Second Law, whereas for the aerodynamic forces approach used quasy-steady state approach. Basically, this method uses a system of equilibrium forces and moments acting on the system FMAV, such as gravity, aerodynamic <br />
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forces and inertial forces. With this method, a mathematical model of the system FMAV has been obtained <br />
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Furthermore, numerical simulations carried out also using MATLAB/SIMULINK. This simulation is reviewing several cases of aircraft, namely: the case of monitoring the flight (hovering) and several variations of equilibrium in the case of flying a vertical direction (against gravity) in the field of different wing. The simulation results showed that the orientation / attitude FMAV translational motion is affected by the condition / initial attitude of the wing movements FMAV. From the research results are expected to provide an overview of the theoretical attitude and dynamic nature of the system FMAV. |
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