What controls the pitch of the main rotor blades in a helicopter?

The pitch of the main rotor blades in a helicopter is primarily controlled by cyclic control. The cyclic control allows the pilot to change the pitch angle of the rotor blades progressively as they rotate, which alters the lift produced by each blade at different points in the rotor's rotation. This enables the helicopter to tilt in the desired direction, allowing for lateral movement and forward flight.

In contrast, collective control pertains to the simultaneous adjustment of the pitch angle of all blades, which changes the overall lift of the helicopter but does not direct the rotor like cyclic control does. Throttle control is related to the engine power and does not directly affect blade pitch, while tail rotor control is specifically for managing yaw and counteracting the torque produced by the main rotor. Understanding these distinctions highlights the critical role of cyclic control in maneuvering a helicopter.