Helicopter rotor

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A helicopter rotor is the rotating part of a helicopter which generates an aerodynamic Lift (force). The helicopter rotor, also called the rotor system, usually refers to the helicopter's main rotor which is mounted on a vertical mast over the top of the helicopter, although it can refer to the helicopter's tail rotor as well. A helicopter's rotor is generally made up of two or more rotor blades, although several earlier helicopters had a rotor with a single main rotor blade. The main rotor provides both lift and thrust, while the tail rotor provides thrust to compensate for the main rotor's torque.
Contents
1 History and development
2 Rotor head design
2.1 Parts and functions
2.2 Swash plate
2.3 Fully articulated rotors
2.4 Semi-rigid rotor
2.5 Stabilizer bar
2.6 Tail rotors
3 Rotor configurations
3.1 Single main rotor
3.1.1 Tail rotor
3.1.2 Ducted fan
3.1.3 NOTAR
3.1.4 Tip jets
3.2 Dual rotors (counterrotating)
3.2.1 Tandem
3.2.2 Coaxial
3.2.3 Intermeshing
3.2.4 Transverse
4 Blade design
5 Limitations and hazards
6 References
7 External links
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History and development
Before the development of powered helicopters in the mid 20th century, autogyro pioneer Juan de la Cierva researched and developed many of the fundamentals of the rotor. Cierva is credited with successful development of multi-bladed, fully articulated rotor systems. This type of system is widely used today in many multi-bladed helicopters.
In the 1930s, Arthur Young improved stability of two bladed rotor systems with the introduction of a stabilizer bar. This system was used in several Bell and Hiller helicopter models. It is also used in many remote control model helicopters.
Rotor head design
The rotor head is a robust hub with attachment points for the blades and mechanical linkages designed to control the pitch of the blades.
Parts and functions

The simple rotor of a Robinson R22.
The simple rotor of a Robinson R22 showing (from the top):
The following are driven by the link rods from the rotating part of the swashplate.
Pitch hinges, allowing the blades to twist about the axis extending from blade root to blade tip.
Teeter hinge, allowing one blade to rise vertically while the other falls vertically. This motion occurs whenever translational relative wind is present, or in response to a cyclic control input.
Scissor link and counterweight, carries the main shaft rotation down to the upper swashplate
Rubber covers protect moving and stationary shafts
Swashplates, transmitting cyclic and collective pitch to the blades (the top one rotates)
Three non-rotating control rods transmit pitch information to the lower swashplate
Main mast leading down to main gearbox

An advanced rotor head for a Sikorsky S-92
Swash plate
Main article: Swashplate (helicopter)
The pitch of main rotor blades can be varied cyclically throughout its rotation in order to control the direction of rotor thrust vector. Collective pitch is used to vary the magnitude of rotor thrust. These blade pitch variations are controlled by tilting and/or raising or lowering the swash plate with the flight controls.
The swash plate is two concentric disks or plates, one plate rotates with the mast, connected by idle links, while the other does not rotate. The rotating plate is also connected to the individual blades through pitch links and pitch horns. The non-rotating plate is connected to links which are manipulated by pilot controls, specifically, the collective and cyclic controls.
The swash plate can shift vertically and tilt. Through shifting and tilting, the non-rotating plate controls the rotating plate, which in turn controls the individual blade pitch.
Fully articulated rotors
During the development of the autogyro, Juan de la Cierva built scale models to test his designs. After promising results, he built full size models. Just prior to takeoff, his autogyro rolled unexpectedly and was destroyed. Believing this to have been caused by sudden wind gusts, Cierva rebuilt it only to suffer an almost identical accident. These setbacks caused Cierva to consider why his models flew successfully, while the full-sized aircraft did not.
Cierva realized that the advancing blade on one side created greater lift than on the retreating side due to increased airspeed on the advancing side which creates a rolling force. The scale model was constructed with flexible materials, specifically rattan, which eliminated the rolling moment as the blades flapped, and compensated for dissymmetry of lift. Cierva concluded that the full size steel rotor hub was far too rigid and introduced flapping hinges at the rotor hub.
Flapping hinges...(and so on)

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