OTHER: Helicopter - Inside - Intermeshing - Electric Motor Located in Rotors

SloMoSynchro (Slow Motor ~ Intermeshing Configuration)

• To locate two ELECTROTOR-SloMo Principal assemblies in a frame that creates an Intermeshing arrangement.
• Initially design and build as a MicroLite craft with the above Intermeshing frame mounted on tripod supports. This will offer the best Payload to Gross weight ratio.

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Bill of Material 1751

The intention is to interlock them electrically and mechanically. ~ DESIGN: Electrotor-SloMo - Rotor - Synchronization - Electrical-Mechanical

• Electrotor ~ SloMo; Radial Flux Permanent Magnet motor.
• With parallel (but isolated) wiring double or triple redundancy can be incorporated in the; batteries, power circuit and motor. .
• The extreme rigidity of the rotor blades and the 6º precone angle allows the rotors to have a reduced axis angle between them.
• Hopefully, [Blade Pitch Control] can also be incorporated.
• Cyclical control by Direct Control, supplemented by Weight Shift
• Collective control by hand grip throttle.
• Yaw: Rudder? Reference Opposed longitudinal cyclic (twist frame about Y-axis) for Interleaving.
• Autorotation by automatic entry, with capacitor assisted flare at landing.
• Powered by a pair of electric motors, which have 1:1 rpm relationship and direct coupling to their counterrotating rotors. ElectrotorSloMo.
• The mechanically separated motors will allow the rotor-motor assembly to be used in any small recreational twin-rotor helicopter. ~ September 18, 2009
• Cyclic Force by the Pilot: For the same effective disk area, the intermeshing may have smaller rotor disk and this may result in a slightly lower pitch-change force by the pilot and a higher roll-change force by the pilot.
• Tripod: For more information see: OTHER: Helicopter - Inside - Interleaving - SloMo on Tripod

Synchronization of Rotors :

• For physical intermeshing backup consider having the two or three blades intermesh at the root instead of large teeth on the OD of the hubs.
• For a possibly better idea see; DESIGN: Electrotor-SloMo - Rotor - Synchronization - Electrical-Mechanical.

• Using the data in the table on DESIGN: Electrotor-SloMo ~ Rotor - Disk - 2 Blades v.s. 3 Blades;
• At the midpoint between the rotors, with an 18" stagger, and airspeed of 60 mph, the tangential velocity will be -37 fps.
• Over the center of the other rotor, with an 18" stagger, and airspeed of 60 mph, the tangential velocity will be +15 fps.
• Over the closest of the stator coils on the other rotor (at 13"R), with an 18" stagger, and airspeed of 60 mph, the tangential velocity will be -12 fps. This means that the coils in close proximity to the other rotor (i.e near to 270º azimuth) will receive little cooling in hover and in forward flight.

1. One heck of a lot of high performance (yet to be developed) batteries. With today's technology the flight time would be logged in minutes.
2. Generator driven by small (yet to be developed) turbine.
3. Ground tether containing electrical cable.
4. Large lightweight Ultracapacitor(s) for flare at the end of autorotation. Could be charged by rotors during autorotation.
5. Capacitors are very light weight. In fact, there is consideration for using the honeycomb core in a composite construction fuselage as a capacitor/battery.
6. Principle Assembly for this craft; Electrotor-SloMo ~ Power Storage Devices

• Have a large coning angle of 6 degrees.

• Principle Assemblies for this craft; Control - Flight, Control - Electric
• Consider using patent US 5,043,641. Have hard copy.

• 4,311,080 US ~ Drive mechanism ~ January 19, 1982 ~~ circular linear induction

• This small (25 employee) Canadian company interesting. http://www.micropilot.com/. There is an article on it in the business section May 30, 2006 Globe and Mail.

• See patent; US 4,968,913. When looking at drawing number 1; Consider a Rotor-Stator-Rotor arraignment. Leave the stator as is and make the second rotor a mirror image of the first; to get opposite rotation between the two rotors. Got to check the validity of preceeding statement.
• I do not think that this will assure synchronized rotation for maintaining fixed blade-crossing azimuths. Perhaps additional electric items might be added.
• What would be the best winding configuration for the stator? - Torus ?
• What would be used to start both rotors in the correct direction? A 3rd small starting phase? Or, a few nylon pinion gears between the two rotors so that both can be pre-spun in a counterrotating direction by the hand of the pilot turning the lower one only?

• See A131.html
• See; Perhaps Relevant Patents

• The resistance of the electric motor to turn (cogging) if no power. Overrunning clutches will overcome this potential problem.
• The efficiency (power to weight) of the axial-flux motor.
• 2P vibration on the absolutely rigid rotor with 2-blades.

• An idea that is intended to assure that the rotors disks have a small gap while not clashing with each other. xx

• Motor power and control to be two or three totally independent systems for redundancy.
• Collective by power change and torque-pitch coupling. OTHER: Miscellaneous - Thoughtless Ideas - Torque/Pitch Collective Rotor Hub
• Principle Assembly for this craft; Electrotor-SloMo ~ Control (flight & power)
• Power Storage:
• Have a battery pack that can be dropped during autorotation so as to reduce the disk loading and therefor the descent rate. Consider having a capacitor pack that stays with the craft to be used during flare.
• Electrotor-SloMo ~ Power Storage Devices

[Source ~ MDD p.20] Discuses Drag and Flapping Pivots

[Source ~ MDD p.122] Figure 12 shows coincidental drag and flapping Pivots.

• OTHER: Helicopter - Inside - Coaxial - Electric Motor Located Between Rotors ~ SloMoCo
• OTHER ~ Flight Dynamics - Rotor Hub - Aerodynamically Active Blade Twist Forget. It looks like this will not work.

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