Chapter 6 Flight Controls
Introduction
This chapter focuses on the flight control systems a pilot uses to control the forces of flight and the aircraft’s direction and attitude.
It should be noted that flight control systems and characteristics can vary greatly depending on the type of aircraft flown.
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 rods, cables, pulleys, and sometimes chains to transmit the forces of the flight deck controls to the control surfaces.
Mechanical flight control systems are still used today in small general and sport category aircraft where the aerodynamic forces are not excessive.
As aviation matured and aircraft designers learned more about aerodynamics, the industry produced larger and faster aircraft.
Therefore, the aerodynamic forces acting upon the control surfaces increased exponentially.
To make the control force required by pilots manageable, aircraft engineers designed more complex systems.
At first, hydromechanical designs, consisting of a mechanical circuit and a hydraulic circuit, were used to reduce the complexity, weight, and limitations of mechanical flight controls systems.
As aircraft became more sophisticated, the control surfaces were actuated by electric motors, digital computers, or fiber optic cables.
Called “fly-by-wire,” this flight control system replaces the physical connection between pilot controls and the flight control surfaces with an electrical interface.
In addition, in some large and fast aircraft, controls are boosted by hydraulically or electrically actuated systems.
In both the fly-by-wire and boosted controls, the feel of the control reaction is fed back to the pilot by simulated means.
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