Magnetic Collective and Cyclic Controls Design

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Description:
In the present forms of such mechanical cyclic and collective controls more or less complexity is unavoidable. Besides the employment of the usual devices such as disengage devices, linkages, metal bars and fittings necessarily introduce numerous difficulties and limitations and add to the cost of production, weight and maintenance of the helicopter.

The objective is to overcome these deficiencies and the complexity of the mechanical transmission from the controls to the swashplate and maintain stability for the helicopter through the agency of a solid-state gyroscopic angular sensor only without the need to use any autopilot/auto-hover systems in a more perfect manner, and by means simpler and more economical than those heretofore utilized.

The main rotor blades will be attached by spherical bearing links to a ring shaped neodymium permanent magnet replacing the conventional swashplate. The mentioned swashplate will be rotating above eight variable electromagnets surrounding the rotor hub four of them will be primary and the other four will be secondary. The blades movement within the range of the pitch angle will be limited by unpowered pneumatic actuators that tends to return the blades to the default position and to control the increased magnetic pull as the swashplate comes closer to the electromagnets to avoid any sudden changes.

Operation:
Collective control is achieved by increasing the voltage evenly in all four primary variable electromagnets. This will increase the magnetic pull thus the swashplate (ring shaped neodymium permanent magnet) will move downward resulting in an increased pitch angle in both blades evenly at the same time. Cyclic control is achieved by increasing the voltage unevenly in the electromagnets located in the direction where you desire to steer the aircraft. This will result in a change in the angle of the swashplate in the desired direction. The swashplate will remain tilted towards the greater magnetic pull during rotation. Auto-hover ability is achieved by synchronizing the electromagnets with a solid-state gyroscope angular sensor to distribute the power to the electromagnets in a manner that adjusts the position of the swashplate by increasing and decreasing the magnetic pull in all directions to keep the helicopter leveled and hovering without any aid from the pilot by keeping his hand on the cyclic stick all the time to apply continues corrections to the position of the aircraft.

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  • ABOUT THE ENTRANT

  • Name:
    Michael Abdelmaseh
  • Type of entry:
    individual
  • Profession:
    Engineer/Designer
  • Number of times previously entering contest:
    never
  • Michael is inspired by:
    As a general strategy, personally I think the 1st priority should always be practicality and reliability, 2nd Performance, 3d reduction of the number of parameters as much as possible (simplicity) -but never sacrificing performance etc for simplicity if it is already practical and reliable (the simpler is not always the best).
  • Patent status:
    none