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The Development of Neural Network Based System Identification ...

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7.3 EXPERIMENTAL RESULTS 205<br />

Yaw Rate (deg/s)<br />

80<br />

60<br />

40<br />

20<br />

0<br />

−20<br />

NNAPC−Offline<br />

Reference<br />

NNAPC−Online<br />

−40<br />

0 50 100 150 200 250 300 350 400<br />

Sample (k)<br />

Tail Rotor Collective Pitch<br />

0.4<br />

0.2<br />

δ ped<br />

NNAPC−Offline<br />

δ ped<br />

NNAPC−Online<br />

Disturbance<br />

0<br />

−0.2<br />

0 50 100 150 200 250 300 350 400<br />

Sample (k)<br />

(a) Yaw rate, r<br />

15<br />

Altitude (cm)<br />

10<br />

5<br />

NNAPC−Offline<br />

Reference<br />

NNAPC−Online<br />

0<br />

0 50 100 150 200 250 300 350 400<br />

Sample (k)<br />

Collective Pitch<br />

1<br />

0.8<br />

0.6<br />

0.4<br />

0.2<br />

δ col<br />

NNAPC−Offline<br />

δ col<br />

NNAPC−Online<br />

0<br />

0 50 100 150 200 250 300 350 400<br />

Sample (k)<br />

(b) Altitude, z<br />

Figure 7.15 <strong>The</strong> NNAPC controllers’ response comparison under input disturbances for yaw and<br />

altitude channels. <strong>The</strong>se disturbances are introduced one at a time with the control responses shown<br />

here being overlaps <strong>of</strong> two separate test runs.

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