ABSTRAK M Fadhil Dzaki Syamsul
PUBLIC Alice Diniarti COVER M Fadhil Dzaki Syamsul
PUBLIC Alice Diniarti
BAB 1 M Fadhil Dzaki Syamsul
Terbatas  Alice Diniarti
» Gedung UPT Perpustakaan
Terbatas  Alice Diniarti
» Gedung UPT Perpustakaan
BAB 2 M Fadhil Dzaki Syamsul
Terbatas  Alice Diniarti
» Gedung UPT Perpustakaan
Terbatas  Alice Diniarti
» Gedung UPT Perpustakaan
BAB 3 M Fadhil Dzaki Syamsul
Terbatas  Alice Diniarti
» Gedung UPT Perpustakaan
Terbatas  Alice Diniarti
» Gedung UPT Perpustakaan
BAB 4 M Fadhil Dzaki Syamsul
Terbatas  Alice Diniarti
» Gedung UPT Perpustakaan
Terbatas  Alice Diniarti
» Gedung UPT Perpustakaan
BAB 5 M Fadhil Dzaki Syamsul
Terbatas  Alice Diniarti
» Gedung UPT Perpustakaan
Terbatas  Alice Diniarti
» Gedung UPT Perpustakaan
PUSTAKA M Fadhil Dzaki Syamsul
Terbatas  Alice Diniarti
» Gedung UPT Perpustakaan
Terbatas  Alice Diniarti
» Gedung UPT Perpustakaan
On flight control implementation, the control surface actuator system plays one of the
key roles that will significantly affect the closed-loop performance of the aircraft. The
actuators must provide the required effort for moving the control surface so that the
desired control action can be reached. Any failure on the actuator system will limit or
degrade the operation of the control surface, so that it will affect the performance of
the system in controlling the aircraft, or even worse, may bring the aircraft into an
unsafe condition. In this project, the effect of some control surface problem due to
actuator failures are modeled, simulated, and analyzed. To reconstruct the situation, the
control device failure model is integrated into the flight dynamic model of an aircraft.
The numerical model of the equation then is used for simulating the aircraft response
under some failure condition. It can be seen from the simulation results that control
surface failure can significantly affect the trim condition of the aircraft, since the
failures can change the balance of forces and moments that work on the aircraft. The
simulation results also show that for some control surface failures they may initiate an
asymmetrical response from the aircraft dynamics. On closed-loop simulations, where
some type of flight control systems for stabilization and maneuvering tasks are
implemented, control surface failures may affect the performance of the control system.
The results of the study suggest that any possibilities of control surface failure must be
anticipated, by using a robust control scheme or other reconfigurable schemes that can
cope with the change in the dynamic characteristics due to the failures.