Flight Control Amt1-1

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The most basic flight control system designs are mechanical and date back to early aircraft. They operate with a collection of mechanical parts, such as

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rods, cables, pulleys

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are still used today in small general and sport category aircraft where the aerodynamic forces are not excessive.

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Mechanical flight control system

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this flight control system replaces the physical connection between pilot controls and the flight control surfaces with an electrical interface.

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Fly by wire

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Current research at the NASA Dryden Flight Research Center involves ______ The goal of this project is to develop an adaptive neural network-based flight control system

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Intelligent Flight Control Systems (IFCS).

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Constitute the primary control system and are required to control an aircraft safely during flight.

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ailerons, elevator (or stabilator), and rudder

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Constitute the secondary control system and improve the performance characteristics of the airplane or relieve the pilot of excessive control forces.

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Wing flaps, leading edge devices, spoilers, and trim systems

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At low airspeeds, the controls usually feel 1._______ , and the aircraft responds slowly to control applications. At higher airspeeds, the controls become increasingly 2._____ and aircraft response is more rapid.

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1. soft and sluggish

2. firm

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Movement of any of the three primary flight control surfaces (ailerons, elevator or stabilator, or rudder), changes the

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airflow and pressure distribution over and around the airfoil.

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The purpose of these design limits is to prevent the pilot from inadvertently overcontrolling and overstressing the aircraft during normal maneuvers.

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control-stop mechanisms

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Aileron

Airplane movement:

Axes of rotation:

Type of stability:

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Airplane movement: roll

Axes of rotation: longitudinal

Type of stability: lateral

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Elevator/stabilation

Airplane movement:

Axes of rotation:

Type of stability:

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Airplane movement: Pitch

Axes of rotation: Lateral

Type of stability: longitudinal

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Rudder

Airplane movement:

Axes of rotation:

Type of stability:

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Airplane movement: yaw

Axes of rotation: vertical

Type of stability: directional

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The purpose is to provide control about the airplane’s roll axis

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Aileron

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The ailerons are attached to the 1._________ of each wing and move in the 2._______ from each other. Ailerons are connected by 3._____ , bell cranks, pulleys, and/or push-pull tubes to a 4._______.

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1. outboard trailing edge

2. opposite direction

3. cables

4. control wheel or control stick

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are located at the rear side of aircraft wings.

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Aileron

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Ailerons are typically 1._____ in shape with well defined length and made of 2._____ to achieve stability and rigidity. The ailerons function by working in opposite directions, i.e, when one moves in the upward direction the other moves in downward direction.

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1. rectangular

2. metal

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Common types of Ailerons:

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1. Differential Aileron

2. Frise Ailerons

3. Flaperons

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With this type of aileron when pressure is applied to the control wheel, the aileron that is being raised pivots on an offset hinge.

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frise-type aileron

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operates and functions in a process except for the part where the aileron which gets deflected upwards is deflected at a greater distance than the one which is deflected in the downward direction.

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Differential aileron

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This projects the leading edge of the aileron into the airflow and creates drag. It helps equalize the drag created by the lowered aileron on the opposite wing and reduces adverse yaw.

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Frise type aileron

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It combine both aspects of flaps and ailerons.

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Flaperon

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READ!!!!

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In addition to controlling the bank angle of an aircraft like conventional ailerons, flaperons can be lowered together to function much the same as a dedicated set of flaps. The pilot retains separate controls for ailerons and flaps.

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is used to combine the separate pilot inputs into this single set of control surfaces .

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Mixer

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Many designs that incorporate flaperons mount the control surfaces ________ to provide undisturbed airflow at high angles of attack and/or low airspeeds

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away from the wing

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COUPLED AILERONS AND RUDDER is accomplished with _________ .

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rudder-aileron interconnect springs

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help correct for aileron drag by automatically deflecting the rudder at the same time the ailerons are deflected.

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Rudder-aileron interconnect spring

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is a result of differential drag and the slight difference in the velocity of the left and right wings.

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Adverse yaw

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From the pilot’s perspective, the yaw is

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opposite the direction of the bank

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READ!!!!!

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Adverse yaw becomes more pronounced at low airspeeds. At these slower airspeeds, aerodynamic pressure on control surfaces are low, and larger control inputs are required to effectively maneuver the aircraft. As a result, the increase in aileron deflection causes an increase in adverse yaw. The yaw is especially evident in aircraft with long wing spans.

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It controls pitch about the lateral axis.

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Elevator

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Like the ailerons, the elevator is connected to the ________ in the flight deck by a series of mechanical linkages.

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control wheel

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Aft movement of the control wheel deflects the trailing edge of the elevator surface up. This is usually referred to as the .

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up-elevator position

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READ!!

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The up-elevator position decreases the camber of the elevator and creates a downward aerodynamic force. The overall effect causes the tail of the aircraft to move down and the nose to pitch up. The pitching moment occurs about the center of gravity (CG).

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READ!!!!

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The strength of the pitching moment is determined by the distance between the CG and the horizontal tail surface, as well as by the aerodynamic effectiveness of the horizontal tail surface.

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Moving the control wheel forward has the opposite effect. In this case, elevator camber 1._____, creating more lift on the horizontal stabilizer/elevator. This moves the tail 2._____ and pitches the nose down. Again, the pitching moment occurs about the 3 _____.

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1. increases

2. upward

3. CG

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factors in elevator effectiveness controlling pitch.

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Stability, power, thrust line, and the position

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READ!!!

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Stability, power, thrust line, and the position of the horizontal tail surfaces on the empennage are factors in elevator effectiveness controlling pitch. For example, the horizontal tail surfaces may be attached near the lower part of the vertical stabilizer, at the midpoint, or at the high point, as in the T-tail design.

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In this configuration, the elevator is above most of the effects of downwash from the propeller, as well as airflow around the fuselage and/or wings during normal flight conditions.

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T-tail

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removes the tail from the exhaust blast of the engines.

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T-tail

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READ!!!!

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Operation of the elevators in this undisturbed air allows control movements that are consistent throughout most flight regimes. T-tail designs have become popular on many light and large aircraft, especially those with aft fuselage-mounted engines because the T-tail configuration removes the tail from the exhaust blast of the engines. Seaplanes and amphibians often have T-tails in order to keep the horizontal surfaces as far from the water as possible. An additional benefit is reduced noise and vibration inside the aircraft.

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is essentially a one-piece horizontal stabilizer that pivots from a central hinge point.

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Stabilator

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are incorporated on the trailing edge to decrease sensitivity.

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Antiservo tabs

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utilizes the concept of two lifting surfaces. Its functions as a horizontal stabilizer located in front of the main wings.

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Canard

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READ!!!!

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In effect, the canard is an airfoil similar to the horizontal surface on a conventional aft-tail design. The difference is that the canard actually creates lift and holds the nose up, as opposed to the aft-tail design which exerts downward force on the tail to prevent the nose from rotating downward.

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controls movement of the aircraft about its vertical axis.

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Rudder

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The rudder controls movement of the aircraft about its vertical axis. This motion is called

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Yaw

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The rudder is controlled by the .

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left and right rudder pedals

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When the rudder is deflected into the airflow, a horizontal force is exerted in the 1._____. By pushing the left pedal, the rudder moves 2.______. This alters the airflow around the vertical stabilizer/rudder and creates a 3._______ that moves the tail to the right and yaws the nose of the airplane to the left.

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1. opposite direction

2. left

3. sideward lift

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utilizes two slanted tail surfaces to perform the same functions as the surfaces of a conventional elevator and rudder configuration.

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V-tail design

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The fixed surfaces act as both horizontal and vertical stabilizers.The movable surfaces, which are usually called

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Ruddervators