The first major step in the development of flight control systems for military aircraft is the fly-by-wire (FBW) flight control system, which is designed as a multiredundant system. The old flight control system with mechanical links from the pilot control column (yoke) and rudder pedals to the control surfaces is using the power of the pilot’s arms and legs to directly move the control surfaces. The two rudders ensure the control of the yaw movement of the military aircraft.Īs the flight speed of military aircraft has increased continuously, it was necessary to develop new flight control systems. The two vertical stabilizers provide the stability of the military aircraft around the vertical axis. The horizontal stabilizer provides stability for the military aircraft, and it can be slowly rotated to act as an elevator (both for pitch control). Leading-edge slats are used to increase the aircraft lift during takeoff and landing maneuvers when the aircraft has a low speed. Flaperons are also used as ailerons to roll aircraft therefore, the flaperons combine the functions of flaps and ailerons. Primary flight control surfaces of a modern military aircraft.įlaperons are flight control surfaces on the rear wing of a military aircraft used as flaps during takeoff and landing maneuvers when the aircraft has a low speed. The latest flight control system is called fly-by-light system. The command imposed by the pilot with a side stick/rudder pedal or autopilot is converted into light signals to the flight control computer and to the electrical or electrohydraulic actuators of each control surface and receives light signals from the motion transducer of each control surface. The latest major step in the evolution of military aircraft flight control systems is the replacement of copper wires with the fiber-optic cables, which have a much lower weight and a much higher capacity to carry digital information (light or photons). This stage of development of aeronautical technologies has been called the fly-by-wire flight control system. The first major step is the pilot with a side stick/rudder pedal or an autopilot, who sends commands converted to electrical signals to a flight control computer and, in turn, interprets and sends wired electrical commands to the electrohydraulic actuators of each control surface and receives electrical signals from the motion transducer of each control surface. As the flight speed steadily increased, it was necessary to develop new flight control systems to replace the old pilot control with mechanical connections to the control surfaces. This chapter presents major stages in the evolution of military aircraft flight control systems.
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