This chapter covers basic aerodynamics, aircraft stability, dynamic response, longitudinal and lateral control and response, powered flying controls, stability augmentation systems and helicopter flight control. This is to establish the background to fly-by-wire (FBW) flight control (Chap. 4) and autopilots (Chap. 8).

    Basic aerodynamics and aircraft stability are explained. An aircraft’s dynamic response to a disturbance is analysed and equations of motions derived. The principles of longitudinal and lateral control are described. It is stated that an aircraft is said to be stable if it tends to return to its original position after being subjected to a disturbance without any control action by the pilot. It is explained that unstable aircraft have advantages including higher performance, reduced weight and increased agility, but they need a high-speed automatic control, known as a ‘fly-by-wire’ flight control system, to correct the tendency to divergence. The possible need to improve damping and stability in three axes by a stability augmentation system is described. It is stated that for high-speed aircraft, the forces needed to move the controls are too much for the pilot and that powered flying controls are needed, which are analysed in detail. This chapter concludes by describing the principles of helicopter flight control.


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