What is the primary function of rotorcraft cyclic pitch control?

The primary function of rotorcraft cyclic pitch control is to tilt the main rotor disc in various directions. This control mechanism allows the pilot to manage the aircraft's altitude and direction by changing the pitch angle of the rotor blades as they rotate. When the cyclic control is manipulated, it alters the angle of attack of the rotor blades at different points in their rotation, which effectively changes the lift produced in specific areas and causes the rotorcraft to move forward, backward, or laterally.

This ability to tilt the rotor disc is crucial for maneuvering and controlling the flight path of the rotorcraft. For instance, tilting the disc forward causes the rotorcraft to move forward, while tilting it to the side results in lateral movement. This dynamic control is essential for various flying operations, including takeoff, landing, and in-flight adjustments.

The other options do not accurately describe the function of cyclic pitch control. While rotor strength and rotor speed-synchronization are important aspects of rotorcraft design and operation, they are not the primary focus of the cyclic control mechanism. Maintaining altitude despite rotor tilt involves a combination of cyclic and collective controls, but the cyclic itself is specifically designed to alter the directional orientation of the rotor disc.