By Agneta Balint (Ed)

ISBN-10: 9533072180

ISBN-13: 9789533072180

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**Additional info for Advances in Flight Control Systems **

**Example text**

Finally, the same maneuvers are also simulated with a lockup at ±10 deg of the left aileron. 1 Control parameter tuning We start with the selection of the gains of the static control law and the bandwidths of the command filters. Lyapunov stability theory only requires the control gains to be larger than zero, but it is natural to select the largest gains of the inner loop. Larger gains will, of course, result in smaller tracking errors, but at the cost of more control effort. , 2007). However, getting the desired closed-loop response is still an extensive trial-and-error procedure.

1990): −c 11 z11 ⎡ ⎤ ⎢ ⎥ B1Gˆ 1 ( X ,U , X 2 ) = ⎢ −V ref ( c 02 z02 + c 12 sin z12 ) ⎥ − A1Fˆ1 − H 1 + X 1des ⎢⎣ ⎥⎦ −c 13 z13 (18) where Fˆ1 is the estimate of F1 and ⎡ ⎢ ⎢ ˆ G1 ( X ,U , X 2 ) = ⎢ ⎢ ⎢ ⎣ ( ( ⎤ ⎥ ˆL ( X ,U ) + Lˆ ( X ,U )α + T sin α sin μ ⎥ 0 α ⎥ ⎥ ˆL ( X ,U ) + Lˆ ( X ,U )α + T sin α cos μ ⎥ 0 α ⎦ T ) ) (19) with the estimate of the lift force decomposed as Lˆ ( X ,U ) = Lˆ 0 ( X ,U ) + Lˆα ( X ,U )α The estimate of the aerodynamic forces Fˆ is defined as 1 ˆ Fˆ1 = ΦTF1 ( X ,U ) Θ F1 (20) ˆ is a vector with unknown constant where ΦTF1 is a known (chosen) regressor function and Θ F1 parameters.

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.

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