Airplane controls: Definition, Components, Function

Airplane controls are the systems and mechanisms used to maneuver and operate an aircraft during flight. Airplane controls include the pilot's input devices, control surfaces, instrument panel, flight control system, and elevators. Airplane controls enable navigation, altitude adjustment, and aircraft management. Understand how airplane controls work together to guarantee safe flight operations. Airplane controls impact the aircraft's performance and handling characteristics.

Flight controls consist of ailerons, elevators, and rudders. Flight controls allow pilots to control the airplane's direction and movement around three axes: longitudinal, lateral, and vertical. Pilots manipulate the control column to adjust ailerons and elevators, while rudder pedals control yaw. Control surface movements translate pilot inputs into desired aircraft attitudes and directions. Flight controls include flaps and trim tabs.

What is a flight control system?

A flight control system is a set of components that manage aircraft orientation and trajectory. Flight control systems consist of control surfaces, cockpit controls, connecting linkages, and operating mechanisms. Older aircraft use mechanical or hydro-mechanical systems, while newer aircraft employ fly-by-wire technology for safety and efficiency.

Control surfaces include ailerons, elevators, rudders, and flaps. Cockpit controls comprise yokes, sticks, and pedals for pilot input. Connecting linkages use rods and cables to transmit control movements. Operating mechanisms employ mechanical systems, hydro-mechanical systems, or fly-by-wire technology.

Flight control systems manage aircraft orientation and trajectory. Stability control is maintained through precise adjustments of control surfaces. Integration with aircraft systems enhances performance. Redundancy features guarantee safety through multiple independent channels.

Newer flight control systems utilize fly-by-wire technology. Digital controls and electronic components replace traditional mechanical linkages. Sensor systems measure flight data and provide feedback mechanisms. Flight computers process software algorithms to control aircraft movements.

Actuators and hydraulics play vital roles in flight control systems. Control actuators use servo motors to move control surfaces. Hydraulic systems employ fluid dynamics and pressure regulation for aircraft. Hydraulic pressure of 3000-5000 psi is used in commercial airliners. Fly-by-wire systems reduce aircraft weight by up to 7% compared to conventional systems.

What are the primary flight controls?

The primary flight controls are ailerons, elevator (or stabilator), and rudder. Ailerons control roll, elevator manages pitch, and rudder handles yaw. These controls enable pilots to maneuver aircraft during flight. Pilots operate ailerons and elevators using the stick or yoke, while rudder is controlled by pedals.

The primary flight controls are detailed in the table below.

Ailerons are wing-mounted control surfaces located near the wingtips on the trailing edge. Ailerons control the aircraft's roll by moving in opposite directions, increasing lift on one wing while decreasing it on the other. This movement allows the aircraft to rotate around its axis.

The elevator is a tail-mounted control surface incorporated into the horizontal stabilizer. Elevators control the airplane's pitch by adjusting their position, making the nose of the aircraft pitch up or down. This adjustment enables the aircraft to rotate around its lateral axis and affects its climb or descent.

Stabilators are tail-integrated alternatives to traditional elevators in some aircraft. Stabilators combine the functions of the horizontal stabilizer and elevator, providing pitch control for the airplane. The stabilator configuration offers a streamlined design and advanced aerodynamic efficiency.

Rudders are mounted on the vertical stabilizer of the airplane. Rudders provide yaw control for the aircraft, enabling rotation around the vertical axis. Rudders aid in steering the aircraft and maintaining coordinated flight during maneuvers.

Canards are forewing-mounted control surfaces used as a configuration for pitch control in some aircraft designs. Canards operate in the opposite manner to elevators, with the control surface located at the front of the aircraft. This configuration offers advantages in terms of stability and maneuverability for certain aircraft types.

What are secondary flight controls?

Secondary flight controls are devices that regulate airflow over aircraft surfaces. Flaps, slats, spoilers, and trim systems enhance precision, handling, and performance. These controls refine lift, drag, and control effort during flight phases, reducing pilot workload and boosting safety.

Secondary flight controls are detailed in the table below.

Flaps are secondary flight controls located on wing trailing edges. Flaps increase lift during takeoff and landing by altering wing camber. Pilots extend flaps to varying degrees depending on flight phase, using hydraulic or electric systems for actuation. Flaps produce drag, aiding in speed reduction during approach and landing.

Slats are leading edge devices that enhance lift at lower speeds. Slats prevent stalls during takeoff and landing by extending the wing's leading edge. Fixed and retractable slats exist, with both designs improving low-speed performance.

Spoilers and spoilerons reduce lift and increase drag on aircraft. Pilots use spoilers to control descent rates and assist braking by disrupting airflow over the wings. Spoilerons are asymmetrically deployed spoilers used for roll control, providing maneuverability during flight phases.

Trim systems stabilize aircraft attitude by balancing control forces. Elevator, aileron, and rudder trim systems adjust control surfaces to maintain flight without constant pilot input. Trim tabs reduce the force needed to move primary control surfaces, decreasing pilot workload during flights.

Air brakes increase drag to manage speed and descent rates. Air brakes deploy from the aircraft's fuselage or wings, creating drag for deceleration or descents. Pilots use air brakes to control approach speeds and prevent overspeeding in flight conditions.
Krueger flaps extend the wing leading edge to enhance aerodynamics. Krueger flaps are not as common as slats but serve a purpose in modifying wing shape. Krueger flaps refine low-speed performance by increasing wing camber and lift generation during takeoff and landing.

What is a flight control servo?

Flight control servos are devices that manipulate aircraft control surfaces like ailerons, elevators, and rudders. Servos convert electrical signals into mechanical movements, allowing pilots to control direction, altitude, and attitude with responsiveness. These compact components guarantee controlled flight operations.

Flight control servo mechanisms consist of several key components. Servo motors provide force, achieving speeds of 0.1-0.2 seconds for 60 degree rotation. Servo actuators exert 10-20 kg-cm (88.5-176.9 oz-in) of torque to move control surfaces against aerodynamic loads. Control electronics process pilot inputs and generate command signals with pulse widths of 1-2 milliseconds. Feedback sensors measure servo arm positions to within 0.1 degrees for precise control.

The servo system operates as a closed feedback loop for precision. Servo response times are under 0.1 seconds from command to deflection. Power requirements range from 4.8-6.0 volts for servos. Servos require 7.4 volts or higher for torque output.

Servos integrate with aircraft control surfaces to enable controlled flight. Aileron servos deflect wing surfaces up to 20 degrees to induce aircraft roll. Elevator servos adjust the horizontal stabilizer by 15-30 degrees to control aircraft pitch. Rudder servos deflect the vertical stabilizer up to 30 degrees for yaw and directional control. Precise servo actuation of these surfaces is pivotal for stable flight dynamics.

Aerodynamic forces on control surfaces impact servo operation. Control surface deflection angles are calibrated 5-15 degrees for normal flight. Deflections of 20-30 degrees enable maneuvers. Servo precision maintains desired surface positions within 0.5 degrees to assure predictable aircraft attitude and flight path control.

What are the functions of flight controls in an aircraft?

The functions of flight controls in an aircraft include allowing pilots to control the airplane's direction by manipulating its movement around three axes: longitudinal, lateral, and vertical. Controls include ailerons for roll, elevator for pitch, and rudder for yaw. Controls like flaps and trim tabs assist in lift and stability.

Primary flight controls consist of ailerons, elevators, and rudder. Ailerons control roll and lateral motion, allowing pilots to bank the aircraft by creating lift differences between wings. Elevator controls pitch and vertical motion, adjusting the nose attitude through angle changes on the tail surface. Rudder controls yaw and directional changes, enabling turns through adjustments to the vertical stabilizer.

Secondary flight controls include flaps and trim tabs. Flaps increase lift and drag, facilitating takeoff and landing operations at slower speeds. Trim tabs maintain stability and reduce control pressures, allowing pilots to tune aircraft attitude without constant input.

Engine controls manage thrust and power allocation. Throttles regulate engine power output, optimizing performance for flight phases. Power management systems distribute thrust across multiple engines when applicable.

Pilots interact with flight controls through inputs and operations. Control column movements adjust ailerons and elevators, while rudder pedals control yaw. Pilots execute commands to achieve desired aircraft attitudes and directions, translating their inputs into control surface movements.

Aircraft dynamics affect flight control effectiveness. Stability considerations ascertain the aircraft maintains its intended flight path. Maneuverability factors determine the aircraft's responsiveness to control inputs. Aerodynamic principles govern how control surfaces generate forces to rotate the aircraft around its axes.