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The Lockheed rotor system used a control gyro, similar in principle to that of the Bell stabilizer bar, but designed for both hands-off stability and rapid control response of the hingeless rotor system. In fly-by-wire helicopters or Remote Control (RC) models, a microcontroller with gyroscope sensors and a Venturi sensor can replace the ...
The pilot's use of control inputs in a hover is as follows: the cyclic is used to eliminate drift in the horizontal plane (e.g., forward, aft, and side to side motion); the collective is used to maintain desired altitude; and the tail rotor (or anti-torque system) pedals are used to control nose direction or heading. It is the interaction of ...
The tail rotor system rotates airfoils, small wings called blades, that vary in pitch in order to vary the amount of thrust they produce.The blades most often utilize a composite material construction, such as a core made of aluminum honeycomb or plasticized paper honeycomb, covered in a skin made of aluminum or carbon fiber composite.
The critical rollover angle is 5°-8°. Once exceeded, main rotor thrust continues the roll, and recovery via cyclic control is impossible. [1] A helicopter is susceptible to a rolling tendency, called dynamic rollover, when close to the ground, especially when taking off or landing. For dynamic rollover to occur, some factor has to first cause ...
Since the tail rotor is driven by the main rotor transmission during autorotation, heading control is maintained as in normal flight. Several factors affect the rate of descent in autorotation: density altitude, gross weight, rotor rotational speed, and forward airspeed. The pilot's primary control of the rate of descent is airspeed.
Detail of the pitch control mechanism of an EC135 Fenestron. Increased safety for people on the ground because the enclosure provides peripheral protection. [5] [18] Greatly reduced noise and vibration due to the enclosure of the blade tips and greater number of blades. [5] [18] A decrease in power requirements during the cruise phase of flight ...
Three methods are used to vary the pitch: oil pressure, centrifugal weights, or electro-mechanical control. Engine oil pressure is the usual mechanism used in commercial propeller aircraft and the Continental and Lycoming engines fitted to light aircraft. In aircraft without a constant speed unit (CSU), the pilot controls the propeller blade ...
Coaxial rotors solve the problem of main rotor torque by turning each set of rotors in opposite directions. The opposite torques from the rotors cancel each other out. Rotational maneuvering, yaw control, is accomplished by increasing the collective pitch of one rotor and decreasing the collective pitch on the other. This causes a controlled ...