. THE FLEXIBLE MODEL

A complete model of the aircraft is obtained by adding its rigid and flexible models at the outputs (see Figure 2.2). A real modal state – space representation of the flexible part is given in appendix A. The corresponding flexible modes are:

Eigenvalue

Damping

Freq. (rad/s)

-2.42Є-01

+

7.34e+00i

3.29Є-02

7.35Є+00

-2.42Є-01

7.34e+00i

3.29е-02

7.35е+00

-4.39e-01

+

8.бІе+ООі

5.09е-02

8.62е+00

-4.39e-01

8.бІе+ООі

5.09Є-02

8.62е+00

-З. ОЗе-01

+

1.25е+01і

2.42е-02

1.25е+01

-З. ОЗе-01

1.25е+01і

2.42е-02

1.25Є+01

-2.93Є-01

+

1.35е+01і

2.1бе-02

1.35Є+01

-2.93Є-01

1.35е+01і

2.16Є-02

1.35Є+01

-7.15e-01

+

1.4ІЄ+01І

5.07е-02

1.4ІЄ+01

-7.15е-01

1.4ІЄ+01І

5.07Є-02

1.4ІЄ+01

-2.24e-01

+

1.43е+01і

І. Ббе-02

1.43Є+01

-2.24Є-01

1.43е+01і

1.56е-02

1.43Є+01

In chapter 4, uncertainties in the natural frequencies of the bending modes above will be introduced in the aircraft model.

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