F-control Quiz 1 Flashcards
Aircraft control systems
are carefully designed to provide adequate responsiveness to control inputs while allowing a natural feel
Primary Flight Controls
Ailerons
Rudder
Elevator
Ailerons
control roll about the longitudinal axis
connected to the control yoke
Ailerons Example
The upward deflection of the right aileron decreases the camber resulting in decreased lift on the right wing.
The corresponding downward deflection of the left aileron increases the camber resulting in increased lift on the left wing. Thus, the increased lift on the left wing and the decreased lift on the right wing causes the aircraft to roll to the right.
Adverse Yaw
Since the downward deflected aileron produces more lift as evidenced by the wing raising, it also produces more drag. This added drag causes the wing to slow down slightly.
Adverse Yaw
it is more pronounced in low airspeeds
Ailerons Designed To Counteract Adverse Yaw
- Differential ailerons
2.Frise-type ailerons
3.Coupled ailerons and rudder
Differential Ailerons
one aileron is raised a greater distance than the other aileron and is lowered for a given movement of the control wheel or control stick.
Frise-Type Ailerons
when pressure is applied to the control wheel, or control stick, the aileron that is being raised pivots on an offset hinge
Frise-Type Ailerons
also forms a slot so air flows smoothly over the lowered aileron, making it more effective at high angles of attack.
Coupled Ailerons and Rudder
are linked controls. This is accomplished with rudder-aileron interconnect springs, which help correct for aileron drag by automatically deflecting the rudder at the same time the ailerons are deflected.
Elevator
controls pitch about the lateral axis
Elevator
is connected to the control column in the flight deck by a series of mechanical linkages
Up-elevator position
Aft movement of the control column deflects the trailing edge of the elevator surface up
Up-elevator position
decreases the camber of the elevator and creates a downward aerodynamic force, which is greater than the normal tail-down force that exists in straight-and level flight.
in a elevator the pitching moment occurs
about the CG.
T-tail
type of empennage where the tailplane (horizontal stabilizer) is mounted to the top of the fin
Stabilator
is essentially a one-piece horizontal stabilizer that pivots from a central hinge point
Antiservo tabs
are incorporated on the trailing edge to decrease sensitivity
Rudder
controls movement of the aircraft about its vertical axis
is controlled by the left and right rudder pedals.
Balance Weights
In a elevator it reduce overcontrol and help stability
Rudder
Counter adverse yaw created by ailerons
