By Agneta Balint (Ed)
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The control inputs of the model are the elevator, ailerons, rudder, and leading-edge flaps, as well as the throttle setting. The leading-edge flaps are not used in the control design. , 2007). Before giving the equations of motion for the F-16 model, some reference frames to describe the aircraft motion are needed. The reference frames used in this paper are the Earth-fixed reference frame FE , used as the inertial frame; the vehiclecarried local Earth reference frame FO , with its origin fixed in the center of gravity of the aircraft, which is assumed to have the same orientation as FE ; the wind-axes reference frame FW , obtained from FO by three successive rotations of χ , γ , and μ ; the stability-axes reference frame FS , obtained from FW by a rotation of − β ; and the body-fixed reference frame FB , obtained from FS by a rotation of α , as is also indicated in Fig.
26 Advances in Flight Control Systems The engine angular momentum he is assumed to be constant. , 1979) is implemented, which calculates the thrust as a function of altitude, Mach number, and throttle setting δ t . This model is given in tabular form. The aerodynamic forces L, Y, and D (expressed in the wind reference frame FW ) and moments L , M , and N (expressed in body fixed frame FB ) are summations of the various aerodynamic contributions stored in lookup tables. , 1979). 3. Adaptive control design In this section we aim to develop an adaptive guidance and control system that ( asymptotically tracks a smooth prescribed inertial trajectory Y ref = x ref y ref z ref ) T with position states X 0 = ( x y z ) .
2 Manoeuvre 1: upward spiral In this section the results of the numerical simulations of the first test maneuver, the climbing helical path, are discussed. For each of the three flight conditions, five cases are considered: nominal, the aerodynamic stability and control derivatives used in the control law perturbed with +30% and with -30% with respect to the real values of the model, a lockup of the left aileron at +10 deg, and a lockup at -10 deg. No actuator sensor information is used. In Fig.
Advances in Flight Control Systems by Agneta Balint (Ed)