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the periods would be about 10 sec. Since the yaw rotational
motion filter for this configuration had a break
frequency of 0.55 rad/sec, the motion cue’s phase distortion
at the task frequency was 90°. It is possible that this
distortion was adversely affecting performance.
Figure 21 illustrates the rms pedal rate for this task. The
analysis of variance indicated that the decrease in pedal rate
was statistically significant when translational motion
was added (F(1,4) = 11.69, p = 0.027). No significant
differences were noted when rotational motion was added,
and translational and rotational motion effects did not
interact.
Subjective Performance Data. The average pilotrated
compensation required for this task is shown in
figure 22. Large variations in pilot opinion occurred, but
no statistically significant differences were noted. Based on
the variation in the data, one cannot say that the motion
configurations affected the amount of subjective compensation
required. However, the trends shown in figure 22
follow those in Task 1 (fig. 15).
Figure 23 shows the mean motion-fidelity ratings for
Task 2. Here motion fidelity was significantly higher
when translational motion was present (F(1,4) = 47.9,
p = 0.002), whereas the presence of rotational motion did
not affect rated fidelity. Rotational and translational effects
did not interact. So, pilots believed that the lack of translational
motion was objectionable as compared to flight.
However, the lack of rotational motion, as long as there
was translational motion, was not perceived as a fidelity
degradation.
24
-150
-100
-50
0
50
100
Yaw rotation, deg
-5
0
5
Ayp, ft/sec2
-50
0
50
Yaw rot. accel., deg/sec2
0 20 40 60 80
-2
-1
0
1
2
Pedal, in
Time, sec
-150
-100
-50
0
50
100
Yaw rotation, deg
-5
5
0
Ayp, ft/sec2 -
50
0
50
Yaw rot. accel., deg/sec2
0 20 40 60 80
-2
-1
0
1
2
Pedal, in
Time, sec
Figure 19. Comparison of full motion and no motion for Task 2.
25
No rotation Rotation
-2
0
2
4
6
8
10
No. of overshoots
No translation
Translation
Figure 20. Measured performance for Task 2.
No rotation Rotation
0
0.5
1
1.5
2
Rms pedal rate, in/sec
No translation
Translation
Figure 21. Control rate for Task 2.
No rotation Rotation
Min.
Mod.
Consid.
Extens.
Compensation
No translation
Translation
Figure 22. Pilot compensation for Task 2.
No rotation Rotation
Low
Med.
High
Fidelity
No translation
Translation
Figure 23. Motion fidelity for Task 2.
Figure 24 illustrates pilot reports of whether lateral
translational motion was present. There were significantly
more reports of lateral translational motion when it was
present (70%), than when it was not (5%) (F(1,4) = 14.8,
p = 0.018). There was no significant effect of rotational
motion on lateral translational motion reports, nor was
there any significant rotational motion and lateral
translational motion interaction (unlike Task 1).
In the reporting of rotational motion, the rotational and
translational motion factors interacted (fig. 25) (F(1,4) =
20.0, p = 0.011). Rotational motion was reported 90% of
the time when translational motion was present, both
when rotational motion was actually present and when it
was absent. Only when translational motion was absent
did the presence of rotational motion lead to increased
reports of rotational motion. When no motion was
presented, rotational reports occurred 27% of the time on
average, but increased to 65% of the time when a
rotational motion was added.
To summarize the results for this task, lateral translational
motion was again the key motion variable. Its addition
reduced control activity, improved motion fidelity, and led
to the belief that rotational motion was also present when
it was not present. These results are similar to those of
Task 1, except for the interesting result that the addition
of rotational motion degraded performance slightly in
Task 2.
26
No rotation Rotation
0%
100%
% of time trans. mot. reported
No translation
Translation
Figure 24. Lateral translational motion perception for
Task 2.
No rotation Rotation
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Helicopter Flight Simulation Motion Platform Requirements(19)
