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Cyclogyro Aircraft / Cycloidal Propellers

Device: Cyclogyro
Folder: cyclogyro
Original: Open article
Confidence
0.90
Practicability
0.60
Evidence
0.50
Fringe Score
0.20
Risk
0.20
TRL
5

Goal

Provide vertical lift and thrust with omnidirectional control for small UAVs, improving maneuverability and efficiency over conventional helicopters.

Problem

Helicopter blade speed dead-space, limited lateral thrust control, and inefficiency at small scales.

Concept Summary

A cyclogyro uses a rotating cylindrical hub with multiple airfoil blades (cycloidal propellers). Each blade's pitch is varied cyclically, generating lift and thrust in any direction as the hub rotates. By synchronising pairs of rotors, the craft can hover, ascend/descend, and move laterally without tilting the whole vehicle.

Principles

  • Aerodynamic lift from rotating airfoils
  • Variable pitch control of individual blades
  • Thrust vectoring through cyclic pitch modulation
  • Cycloidal rotor kinematics

Scientific Domains

Aeronautics Mechanical Engineering Fluid Dynamics

Materials

  • lightweight composite
  • plastic
  • carbon-fiber reinforced polymer

Mechanisms of Action

  • Rotating airfoil blades generate lift and thrust
  • Blade pitch is adjusted continuously to control force direction
  • Differential thrust between left/right rotors provides yaw control

Energy Sources

electric motor battery

Applications

  • Small UAVs
  • VTOL drones
  • Micro air vehicles

Claimed Performance

More efficient and maneuverable than helicopters at small scales; tethered prototype demonstrated vertical and horizontal flight.

Experimental Evidence

Tethered flight of a cyclogyro prototype by the National University of Singapore (2007); micro cyclocopter free flight by University of Maryland (2011); several other university teams have built tethered or short-duration free-flight models.

Replication Status

Prototype tethered flight achieved; limited free-flight demonstrations; no large-scale commercial deployment.

Limitations

  • Only tethered flight demonstrated for most prototypes
  • Power loading (lift per power) not better than helicopters
  • Blade bending due to centrifugal forces
  • Scale limitation - impractical above ~0.5 m rotor diameter

Red Flags

  • Lack of independent, peer-reviewed performance data
  • No quantitative thrust or efficiency figures provided
  • Claims of superiority without rigorous testing

Keywords

cycloidal rotor VTOL UAV tilt-rotor aerodynamic control

Related Technologies

helicopter tilt-rotor aircraft drone multirotor

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