Development of UAV, Cyclocopter I (2003.03 ~ 2004.12)

Specifications

 

 Two Rotor System

 Number of Blades

 4

 Rotor Radius

 0.7 m

 Airfoil

 NACA0012

 Blade Span Length

 1.0 m

 Max. Pitch Angle

 30 deg.

 Blade Chord Length

 0.15 m

 Power

 16HP Engine

 Rotating Speed

 550 RPM

 Accomplishments

 - Development of Unmanned VTOL vehicle, cyclocopter
 - Structural analysis by NASTRAN
 - CFD analysis by STAR-CD
 - Parametric study for optimal rotor design

 Movie Clip

 Unmanned VTOL aircraft, Cyclocopter

 - Investigated in numerical and experimantal manner to verify the chracteristics and the performance.
 - Focused on the hovering and the low speed forward flight of the vehicle.

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Cycloidal Blade System

Developed Cyclocopter

 Design

 - Two rotors with dame rotation direction
 - Rotors are supported at both ends of the fuselage : overcome centrifugal force and reduce vibration

Parameter

Value

Rotating speed

550 RPM

Rotor radius

0.7 m

Lateral length

2.7 m

Longitudinal length

1.65 m

Number of blades

4

Conceptual design

Total weight

46 kg

 Analysis

 - Rotor

 - Airframe

 - Thrust and power

     ¢Ñ Thrust : 50 kgf ( 550 RPM & ¥èa =26°)
         Corresponding power : 13 HP
         Total weight : 46 kgf
         Engine Max. power : 16 HP

 Manufacturing

 - Blade

 - Control

 - Transmission

 

 Experiment

 - Data acquisition system

 - Results of experiment

Thrust with repect to blade pitch angle

Vertical thrust with repect to phase angle

 - Center of thrust