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Following series on real-time control systems
Unmanned aerial vehicles usually operate in environments with different sources of disturbances, from wind gusts and variations in the ambient conditions to more complex situations, such as variations in the effective payload (for package delivery, refueling, ground attack or air-to-air combat). This renders some challenges when considering full autonomy.
In order to face these challenges, modern aircraft rely heavily on computational systems in an attempt to achieve optimal performance. The control system that regulates aircraft attitude greatly depend upon the performance of the integrated subsystems. That is:
the resulting aircraft performance depends on the flight control system, engine control system, fuel control system, environment control systems, hydraulic and electrical control system, and so on
Briefly, the flight control system (FCS) is a digital, full authority fly-by-wire system which receives inputs from the path planning algorithm and integrated sensors (gyros (Roll, Pitch, Yaw) and accelerometers (Normal and Lateral), total pressure, static pressure, calibrated air speed, angle of attack and side slip. FCS processes the inputs and using flight control laws (CLAW) implemented in the Digital Flight Control Computer (DFCC) controls the movement of the surface actuators during normal flying as well as under certain failure conditions.
Although it is expected that the DFCC maintains the aircraft within a specified flight envelope, in some scenarios faults may occur whether from operating in uncommon conditions or unaccounted effects within the control design. The following series on aircraft controls will present a study and analysis on these fault cases.
