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A typical helicopter has three flight control inputs: the cyclic stick, the collective lever, and the anti-torque pedals. [2] Depending on the complexity of the helicopter, the cyclic and collective may be linked together by a mixing unit , a mechanical or hydraulic device that combines the inputs from both and then sends along the "mixed ...
Its comprises helicopter aerodynamics, stability, control, structural dynamics, vibration, and aeroelastic and aeromechanical stability. [ 1 ] By studying the forces in helicopter flight, improved helicopter designs can be made, though due to the scale and speed of the dynamics, physical testing is non-trivial and expensive.
In forward flight a helicopter's flight controls behave more like those of a fixed-wing aircraft. Applying forward pressure on the cyclic will cause the nose to pitch down, with a resultant increase in airspeed and loss of altitude. Aft cyclic will cause the nose to pitch up, slowing the helicopter and causing it to climb.
For an overloaded helicopter that can only hover IGE it may be possible to climb away from the ground by translating to forward flight first while in ground effect. [11] The ground-effect benefit disappears rapidly with speed but the induced power decreases rapidly as well to allow a safe climb. [ 12 ]
Below, the helicopter rotor has lost power, and the craft is making an emergency landing. Autorotation is a state of flight in which the main rotor system of a helicopter or other rotary-wing aircraft turns by the action of air moving up through the rotor, as with an autogyro, rather than engine power driving the rotor.
Aircraft flight mechanics are relevant to fixed wing (gliders, aeroplanes) and rotary wing (helicopters) aircraft.An aeroplane (airplane in US usage), is defined in ICAO Document 9110 as, "a power-driven heavier than air aircraft, deriving its lift chiefly from aerodynamic reactions on surface which remain fixed under given conditions of flight".
Although its principle is also found in earlier patents by other screw inventors. The first successful implementation of the swashplate was made by de la Cierva in 1922 in his autogyro. [2] In 1907 before the flight test of Cornu's helicopter. Can be seen wheels (plates) with levers controlling the pitch of the propellers.
[1] [2] Unlike fixed-wing aircraft, of which the stall occurs at relatively low flight speed, the dynamic stall on a helicopter rotor emerges at high airspeeds or/and during manoeuvres with high load factors of helicopters, when the angle of attack(AOA) of blade elements varies intensively due to time-dependent blade flapping, cyclic pitch and ...