The development of closed loop control has been one of the major technological
achievements of the twentieth century, and its concepts married with analogue and digital
computation led to explosive growth in the sophistication of the technology and the ubiquity
of its application. By that, an automatic flight control system is able to stabilize an inherently
unstable airplane or to provide a stability augmentation system (SAS). In other words, there
is no margin for error in its response to atmospheric disturbances and to commands that
come from navigation system. Moreover it improves the handling qualities, the flight comfort
and reduces the costs when an airplane is under control of an autopilot.
This specific project is destined to simulate and analyze the operating parameters (i.e.,
altitude, pitch angle, airspeed, throttle level, and elevator angle) of a passenger aircraft -
Boeing 747-100 –in longitudinal motion deflected from its ordered flight trajectory and
atmospheric condition when related with its reference steady flight parameters.
For all cases studied, the results are satisfactory controlled and expected. Future works can
be done in using the differential equations instead of linearized ones, which increases the
range of possible cases to be studied.
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