• To evaluate, possibly develop, and then possibly prototype an Interleaving rotorcraft that utilizes electric power and perhaps electric control.

• A laterally symmetrical Interleaving configuration;
• To eliminate the need for constant yaw control.
• Incorporates 'Absolutely' Rigid Rotors.
• To provide a faster response to cyclic control inputs.
• To reduce the downwash on the fuselage by provide a small amount of the Advancing Blade Concept during hover.
• Pusher Propeller.
• The pusher propeller will partially offload the rotors (taking them in the direction of a gyrocopter's rotors).
• This should also reduce the downwash on the fuselage during cruise.
• The 'Absolutely' Rigid Rotors would generate large moments therefore an electronic limitation should be incorporated into the flight control system.

• Probably a greater vibration on the fuselage due to downwash during hover, however the six blades and smaller blade radius will place any vibration at a frequency of +/- 50 Hz., which is considerably removed from the objectionable 15 hz. In addition, this higher frequency will result in a lower amplitude. Also, the CVJ +HS rotor will reduce the downwash from the retreating blades during forward flight. Whether the vibration is acceptable or objectionable is anyone's guess.

• Both the outer frame and the armature rotate. They drive against each other and therefore rotate in opposite directions. This opposed-rotation results in a 'free' 2:1 speed reduction when the propeller is rotating.
• DC brushless.

• For an understanding of the drive motor and drive train see; Inrunner+Outrunner_Motor

• Early 1-seat interleaving helicopter. OTHER: Helicopter - Outside - Interleaved - Landgraf ~ H-4
• OTHER: Helicopter - Inside - Interleaving - Electric Ultralight & UAV
• Electric UniCopter
• General: OTHER: Aerodynamic - Rotor Disk - Dual Configuration - Interleaving

• Disk loading:
• The overlapping area will produce a disk loading that will be just about twice that of the non-overlapping area. This is because twice as many blades are passing through the overlapping area. An advantage of this in forward flight is that the high thrust from the tips of the retreating blades on one rotor are operating in the low thrust root area of the other rotor. In addition, the fuselage is inside the 75% of rotor radius.
• Lateral symmetry of lift is not necessary. This means that the thrust in the overlapping area can be reduced and the thrust on the outside halves of the disks can be increased.
• During hover the downwash on the fuselage and spars will be significantly reduced. In addition the fact that there are twice as many blades passing over the fuselage will double the frequency (For a Very-Light helicopter the frequency will be roughly 500 RRPM x 6 / 60 seconds = 50 hz, which is quite removed from the worst at 15 hz). The greater thrust on the advancing blades (outside forward) = greater drag on the advancing blades = slight longitudinal reverse thrust.
• During cruse, the same will apply plus these blades will now be retreating and moving the thrust further out toward the blade tips.
• Wild Thought:
• Assuming that the batteries and the pilot have a similar weight, consider deleting the central fuselage by locating the pilot under one rotor and the batteries under the other rotor.

• OTHER: Helicopter - Inside - Interleaving - Morphing

• Independent Root & Tip Control (incorporating Reverse Velocity Utilization)
• Large Chord and Low Tip Speed (including Absolutely Rigid Rotors + Pusher Propeller)
• Advancing Blade Concept (subset of the above)

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