The control rotors received four signals at each step.

The second bank of five rotors was termed the control rotors.

After passing through the control rotors, the outputs were divided into ten groups of various sizes, ranging from 1-6 wires.

A control stick cyclically controls rotor pitch angle.

Each rotor contained a notch (or more than one) that controlled rotor stepping.

In response, Cierva developed a direct control rotor hub, which could be tilted in any direction by the pilot.

All these parameters control the characteristics of the control rotor which results in the following rate of the main rotor.

It offers excellent value for money, and when equipped with the optional soil density control rotor gives good control over the density of filling.

Charles Kaman founded the company in December 1945 with $2,000 of capital and his invention of the servo-flap controlled rotor.

Later in the program, the tilt of the wings was linked to the collective control to limit lift and to control rotor speed during autorotational profiles.

The system developed relieved the helicopter pilot of the need to control rotor speed directly and in this way was the forerunner of all subsequent systems world wide.

Options: Tray destacker, soil density control rotor, belt filling option for vacuum formed trays, stainless steel chains on filler hopper.

The collective levers have integral throttles, although these are not used to control rotor rpm, which is automatically governed, but are used for starting and shutting down the engine.

The disassemblable rotors consisted of an insert with electrical contacts and scramble wiring, and an outer ring with mechanical pins whose presence or absence controlled rotor stepping.

The X-Wing circulation control rotor concept was developed in the mid-1970s by David W. Taylor Naval Ship Research and Development Center under DARPA funding.