As a part of Aero-design Challenge a group of seven students from my college designed an unmanned aerial vehicle.
Design Considerations included:
- Wing design: Aspect Ration and Wing loading for deciding the wing span and chord length.
- Wing airfoil selection: based on angle of attack, Cp Vs X-chord, Cl Vs Cd and many other parameters were considered to decide the S1223 as the wing airfoil.
- Fuselage Design: was based mainly on the aim to reduce weight while still accommodating payload and electronics.
- Tail: Conventional tail structure with NACA 0012 was used to ensure stability with greater lift.
- Control Surfaces: were designed after thorough calculations.
Electronics used: LiPo Battery 2200mAh, 11.1V, Transmitter and Reciever: Flysky Fs-iA6B, Servo motors: 9gm, torque: 1.8kg-cm, Electronic Speed Controller: 30A BLDC ESC, Propeller: 2000KV Brushless motor
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