• To provide additional cyclic control in an electrically powered rotorcraft that has 2-blade teetering rotor(s).
• The primary source of the additional control power comes from the inclusion of Hub Springs, or alternatively Offset Teetering Hinges, in the rotorhub. Each of these two devices creates a sinusoidal two-per-rev moment (vibration).
• To minimize the vibration a second device, which is referred to as the Motor/Reducer/Gyro Assembly (MRGA), is also included. It consists of a Control Moment Gyroscope, which incorporates the electric motor that drives the craft's rotor through an internal gearbox.
• The Control Moment Gyroscope also creates a sinusoidal two-per-rev moments. However, these two moments are nearly 90º in advance of the two-per-rev moments created by the Hub Springs, or the alternative Offset Teetering Hinges. [How the 90º offset in phase is achieved.]
• The four sinusoidal moments per rotor revolution combine to minimize vibration when off-center cyclic is applied; while at the same time providing greater control of a rotorcraft with teetering rotor(s), particularly during a condition of zero-gravity.

• July 31, 2011 ~ In addition to the above, consider incorporating Torque-Pitch Coupling (also see; Electrotor-SloMo - Control Flight - Auto-Collective by Torque-Pitch) into the rotors, thereby providing enhanced control power to the collective, as well.

Drawing of Principal Assemblies (w/ Offset Teetering Hinge ~ ~ w/ Teetering Hinge & Hub Spring):

 For the general arrangement of other configurations under consideration see the links on this page.

• To give improved cyclic response to a 2-bladed helicopter rotor by maintaining a constant moment on the craft when off-center cyclic is applied.
• To provide control power if the rotor should experience zero-gravity.
• To give greater stability due to the gyroscopic effect of the motor.
• To provide additional rotational inertia to the rotor at entry and at flare during an autorotation.
• For the motor to serve as a generator; to perhaps charge a capacitor for a powered flare during a landing from an autorotative descent.
• To simplify the helicopter's principle components and reduce the craft's weight.

• Principle Assembly:
• A 2-blade teetering rotor assembly that is complete with electric motor, gear reduction, flight controls, motor controls, and blades.
• Peripheral Assembly:
• Preferably; Intermeshing, Interleaving or Side-by-side configured fuselages, which offer the additional advantages of; easy yaw control, reduced cross-couplings, and a better power-to-weight ratio.

• Rotor:
• Motor/Reducer/Gyro Assy:
• Control - Flight & Power
• OTHER: Electrical - Power Storage

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