When an aircraft will fly itself perfectly level with no pilot input we call the aircraft “trimmed”. When the center of gravity is too far back (aft) the aircraft becomes unstable and the aircraft designer needs to be sure we can control pitch. When the center of gravity is too far forward the aircraft will be very stable and the aircraft may not have enough control movement to attain the desired change in attitude. This is also why when we begin ground roll the rudder only just has enough effect to counter the yaw from the engine power.Ĭhanges in power have the same effect for rudder and elevator, as the thrust from the engine forces air past the control surface. This is why at high speed we need only tiny control inputs, yet at landing speed we move the stick or yoke almost the entire way back. *At an increased airspeed, increased airflow increases the force from a change in wing shape which produces greater rotational force around that axis. High input = high rotational force around the axis.Low input = low rotational force around the axis.No input = no rotational force around the axis.When we move a primary controls surface we change the shape of that wing. The rudder and vertical stabilizer are a wing, the elevator and horizontal stabilizer are a wing, and clearly the wing and ailerons are a wing. The more we change the shape, via greater control input, the greater the rotating force around the axis that we produce. Nose up cause the aircraft to slow, nose down causes the aircraft to speed up. Right rudder if held will then cause right roll.Įlevator initially changes the pitch, but the secondary effect is a change in airspeed. Rudder has a secondary effect of roll in that after an aircraft yaws from rudder, the aircraft rolls to the side with wing further back, ie the side you are pressing rudder. Some designers create aileron designs that reduce this adverse aileron effect. So the secondary effect of aileron is yaw. Right rudder yaws the aircraft to the right, left rudder yaws the aircraft to the left.Īileron has a secondary effect in that after it rolls the aircraft it then begins to yaw as the aircraft slips towards the lower wing. Right movement rolls the aircraft to the right and left movement to the left. The ailerons roll the aircraft in the direction the yoke or stick is moved. When the elevator is pushed forward, the elevator goes downwards and the aircraft pitches nose down. When the elevator is pulled back, the elevator comes upwards and the aircraft pitches nose up. When a control first deflects we call this the primary effect. Aileron – controls roll around the longitudinal axis (red).Rudder – controls yaw around the normal axis (blue).Elevator – controls pitch around the lateral axis (green).**The primary controls of an aircraft are the: (these generally in exam) Back to: Basic Aeronautical Knowledge For RAA & RPL & PPL
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