By Agneta Balint (Ed)
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The number and size of the hyperboxes should be based on a priori information on the physical properties of the vehicle on hand, and may be defined in terms of state variables as Mach number, angle of attack and engine thrust. , 2003) to interpolate between the local models to ensure smooth model transitions. Numerical simulations of various maneuvers with aerodynamic uncertainties in the model and actuator failures are presented. The maneuvers are performed at several flight conditions to demonstrate that the control laws are valid for the entire flight envelope.
The available virtual controls in this step are the angular rates X 3 . The relevant equations of motion for this part of the design are given by X 2 = A2 F1 ( X ,U ) + B2 ( X ) X 3 + H 2 ( X ) (27) where ⎡ tan β + tan γ sin μ ⎢ 1 ⎢ −1 A2 = ⎢ mV cos β ⎢ 0 ⎣ tan γ cos μ 0 1 cos α ⎡ 0⎤ ⎢ cos β ⎥ ⎢ 0 ⎥ , B2 = ⎢ − cos α tan β ⎥ ⎢ sin α ⎥ ⎢ 0⎦ ⎢⎣ sin α ⎤ ⎥ cos β ⎥ 1 − sin α tan β ⎥ ⎥ 0 cos α ⎥ ⎥⎦ 0 31 Adaptive Backstepping Flight Control for Modern Fighter Aircraft ⎡ ⎤ g ⎢T ( sin α tan γ sin μ + sin α tan β − cos α sin β tan γ cos μ ) − tan β cos γ cos μ ⎥ V ⎢ ⎥ 1 ⎢ sin α g ⎥ H2 = T cos γ cos μ + ⎥ mV ⎢ cos β V ⎢ ⎥ g ⎢ ⎥ −T cos α cos β + cos γ sin μ ⎢⎣ ⎥⎦ V are known (matrix and vector) functions.
Both the control law and the aircraft model are written as C S-functions in MATLAB/Simulink. 447 deg; where h is the altitude of the aircraft, and all other trim states are equal to zero. Furthermore, two maneuvers are considered: 1) a climbing helical path and 2) a reconnaissance and surveillance maneuver. The latter maneuver involves turns in both directions and some altitude changes. The simulations of both maneuvers last 300 s. The reference trajectories are generated with second-order linear filters to ensure smooth trajectories.