OTHER: Electrotor-MicroLite ~ Concerns & Tasks

The power wires to the motor must disconnect from the battery pack (and rear leg?)

The wiring to the pilot, such as throttle, emergency power switch and instruments, etc. must disconnect between the principle assembly and the two front legs. Consider swing the legs up to the blades; if the legs do not extend beyond the blades and the weight can be carried by one man.

Reduce weight while simplifying

Is there a reason to seal and lubricate bevel gears?

Work on means of providing 2-position blade pitch (auto-collective) This cannot be done well by blade twist since the pitch change will increase at greater span distances The complete blade must rotate on the pitch axis, perhaps in a bushing.

Try and consider all things that could go wrong.

• Can the teeth in the ring gear be hardened and/or should there width be increased, if this is possible.
• Add seals.
• Add oil filler hole.

• Autorotation: The requirement for autorotation may never exist. The normal deterioration of the electrical power, perhaps supplemented by a feature in the controller, will created deterioration of the electrical power going to the motors might be used to force the craft to descend. Then the short-term power supply (Ultra capacitor) would be used for the actual landing.
• Concern: As the power is reduced the rotor will probably experience a reduction in its RRPM and a reduction in the induced velocity through the disk. Will this result in an angle of attack across the surface of the disk that will result in a stalled rotor? Where is the NACA article by Robert Pegg? Note that the Intermeshing blade (6 blades) at hover has a maximum AoA of 1.01º, which is at the .4R segment
• The Ultrasport 254 has a disk loading of 1.52 lb/ft². It is claimed that it can autorotate to the ground, lift off and return to the ground on the stored inertia in the rotor. If the eventual Microlite had 5'-6" blades and was Side-by-Side it's disk loading would be 1.58 1.52 lb/ft², however it will not have the same rotational inertial.
• See; Rotary Wing thread; The Demise of Autorotation
• Reliability:
• Xx
• Perturbations:
• xx
• 2-position Pitch Control:
• The change in the pitch of the two rotors will not be synchronized. This means that in the time between the transition of each; the coaxial configuration will be subject to yaw, while the Interleaving and the Side-by-Side will be subjected to roll. This may not be a problem if the transition between torque and no torque involves a specific power setting for the minimum current and this could be activated by the 'ON' switch, before the 'rheostat' throttle was used.
• This problem will be much more detrimental on the proposed subsequent variable pitch rotors, since the blades on the two rotors may never have identical pitches, except when they are at the two end-stops of travel.
• More (less complicated):
• Cooling of motor:
• xx
• Landing Safety:
• Legs v.s. Skids:
  
  If a gimbaled microlight rotorcraft with skids is about to touchdown and it has excessive forward velocity the pilot will attempt to aerodynamically reduce the forward velocity. To to this he must push far forward on the overhead stick. This push will swing the pilot and the skids back and this will cause the leading portion of the skids to contact the ground first.
  
  If there is still some forward velocity at this time, will the craft not run the risk of tumbling forward?
  
  Perhaps human legs might be better since at the start of the touchdown the pilot's feet will relieve some of the gravitational pull on the rotors. Then the pilot can walk forward, while still applying full forward arm extension so that the partially loaded rotor can continue to exert some rearward thrust.

• Torque-Yaw Coupling:
• Particularly during an unexpected and automatic entry into autorotation. The speed RRPM of the two rotors will always be equal and the torque will be equal at some specific setting due to the initial set op of the collective setting on both rotors. However the craft will want to yaw under different flight conditions such as autorotation and forward flight.
• If the craft was required to autorotate to the ground then the application of emergency power preceeding the actual landing will almost certainly cause the craft to yaw. This should be eliminated by letting the rudder go into its home position.

• xx

• xx

• Principal Assembly:
• Source for blades.
• Finish the CNC table?
• ????
• Design the rotor hub and drive.
• Consider the precone & gimbal position relationship in respect to speed stability
• Controller:
• Balancing of power to motors.
• Tripod Supports:

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