A120

DESIGN: Electrotor-SloMo ~ Tasks, Concerns, Objectives & Miscellaneous

Tasks (to do): for OTHER: Helicopter - Inside - Intermeshing - Electrotor-SloMo - Development

1/ Blade is the essence of the craft.

De Bothezat characteristics?

2/ Motor:

To closely match the maximum efficiencies of the rotor and the motor at the same RPM.

Megaflux inrunner or F & P outrunner or Joby?

3/ Rotorhub:

Torque-Twist(at root)

Synchronization:

Yaw: DESIGN ~ Electrotor-SloMo ~ Control Flight - Weight-Shift - Yaw

Autorotation: 2107.html, 2070.html

4/ Controller:

5/ Frame:

________________________________________

Was

Frame:

DESIGN: Electrotor-SloMo ~ Frame - Intermeshing - H-tube - General

Test Stand: Only required for F & P

To support the above frame. DESIGN: Electrotor-SloMo ~ Fuselage - Test Stand

Motor:

Electrotor-SloMo ~ Motor

Develop, test and record up to limits of basic F&P. Variables Voltage, Wiring gauge, serial x parallel coils,

Develop to 10KW at 750 RRPM???. Cooling

Blade: for development only.

IVO: Buy

8H12 - Aluminum This will be closer to the final design. SynchroLite ~ Rotor - Blade - 8-H-12 - Aluminum

RotorHub:

DESIGN: Electrotor-SloMo ~ Rotorhead - Hub-C - Overview and Layout

IVO: Electrotor-SloMo ~ Rotorhead - Hub - IVO

See 1955.htm and 1955.dc Hub details: See 1900.dc Composite rotorhub construction.

Synchronization: Electrotor-SloMo ~ Rotorhead - Synchronization

Torque-Pitch Thrust Control: To development the Torque-Pitch mechanism.

Electrotor-SloMo - Control Flight - Auto-Collective by Torque-Pitch

Electronic Controller: Description of operation etc.

Electrotor-SloMo ~ Control - Electric

Concerns:

Primary Ones:

Can the rotor-rotor elastomeric bearing maintain a constant airgap in the motor?

Will threre be excessive 2P vibration if slow turning 6'-3" radius rotors are used?

Will there be stiction in the pitch-change mechanism?

What is the best method(s) for maintaining synchronization?

Can it be assured that a loose magnet will not stop or destroy a motor?

Foreign object entering motor, particularly a ferromagnetic object.

Will it be possible to have a near optimal motor speed and a near optimal rotor speed?

Can the F&P motor produce 10KW?

Can an effective, redundant and safe control system be developed?

Will thermal expansion of composite aero-hub and steel motor-rotor create a problem? Should motor-rotor be independently mounted to the 'mast'?

Non-autorotation & Vortex Ring State

Can the craft be made Darwinian proof?

Minor Ones:

See red type on specific pages.

The below to be relocated;

Galvanic compatibility of metal fasteners in carbon composite; http://www.eng-tips.com/viewthread.cfm?qid=157981

Titanium fasteners are the default choice when joining to carbon composite structures. Galling can be managed (somewhat) by use of lubricants/coatings. I recommend contacting Steve Buzolits at SPS to discuss their Aerlite Ti fasteners and options for reducing/minimizing galling. Use the following link for more information:

Objectives:

IF the electrical system never totally fails;

If the electrical system never totally fails, then the rotors can have smaller diameters.

If the rotor diameters are smaller, then the weight-shift control will be easier.

If the rotor diameters are smaller, then the power requirement will be greater.

If the rotor diameters are smaller, then the empty weight will be slightly less.

If the weight is less, then the power requirement will be less.

If the weight of the principal assembly is less, then the weight-shift control will be easier.

If the electrical system never totally fails, then synchronization of the rotors can be by motor control.

Efficiency (i.e. long flight time) is a primary objective. The motor, the rotor, and the configuration must be optimized for greatest thrust, while the whole craft must be optimized for lowest weight.

See Electrotor ~ Objectives

Outside Engineering Assistance Required:

Electronic Controller.

Motor.

Composites. For blade, rotorhub, and motorhub etc.

Future Considerations:

Consider an unmanned hybrid for much of the flight-testing.

A Progression of the ELECTROTOR into larger and more advanced craft.

Backpack helicopter. 2 x 10 = >20 HP

Seat & skids. 2 x 12.5 = >25 HP

Ultralight (SynchroLite fuselage). Extra 40-50 lbs GW. 2 x 15 = >30 HP

Light UniCopter (Interleaving?) electric (w/ pusher). 2 x 40 + 1 x 40 = 120 HP

AeroVantage. 2 x 50 =100 HP or 4 x 40 = 160 HP

Same Page Different Craft: ~ Electrotor-Simplex ~ Electrotor-MicroLite ~ Electrotor-Plus ~ SynchroLite ~ UniCopter

Last Revised: December 30, 2011