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Typical trim tabs on aileron, rudder and elevator. Trim tabs are small surfaces connected to the trailing edge of a larger control surface on a boat or aircraft, used to control the trim of the controls, i.e. to counteract hydro- or aerodynamic forces and stabilise the boat or aircraft in a particular desired attitude without the need for the operator to constantly apply a control force.
Most fixed-wing aircraft have a trimming control surface on the elevator, but larger aircraft also have a trim control for the rudder, and another for the ailerons. The rudder trim is to counter any asymmetric thrust from the engines. Aileron trim is to counter the effects of the centre of gravity being displaced from the aircraft centerline ...
The most commonly available control is a wheel or other device to control elevator trim, so that the pilot does not have to maintain constant backward or forward pressure to hold a specific pitch attitude [4] (other types of trim, for rudder and ailerons, are common on larger aircraft but may also appear on smaller ones).
Elevators' effect on pitch Elevator and pitch trim tab of a light aircraft. Elevators are flight control surfaces, usually at the rear of an aircraft, which control the aircraft's pitch, and therefore the angle of attack and the lift of the wing. The elevators are usually hinged to the tailplane or horizontal stabilizer.
In some aircraft trim devices are provided to eliminate the need for the pilot to maintain constant pressure on the elevator or rudder controls. [5] [6] The trim device may be: a trim tab on the rear of the elevators or rudder which act to change the aerodynamic load on the surface. Usually controlled by a cockpit wheel or crank. [5] [7]
When the stick is neutral and the load factor is 1g, the aircraft remains in level flight without the pilot changing the elevator trim. Horizontal side stick movement commands a roll rate, and the aircraft maintains a proper pitch angle once a turn has been established, up to 33° bank.
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Rotating the control wheel controls the ailerons and the roll axis. Fore and aft movement of the control column controls the elevator and the pitch axis. [1] When the yoke is pulled back, the nose of the aircraft rises. When the yoke is pushed forward, the nose is lowered.
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