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-10 0 10
20 30 q0 50 60 70
. a, deq
Fig. 8 59 Loss of roll damping of X-29 model at high angles of attack.41
STABILITY AND CONTROL PROBLEMS AT HIGH ANGLES OF ATTACK 731
problem but could not eliminate it.41 This loss ofroll damping coupled with a high
yaw-to-roll inertia (/7-//x - 10) made the configuration susceptible to wing rock.
The wing rock amplitude increased with angle of attack and, at a -. 35 deg, the
peak amplitude exceeded 25 deg. An interesting aspect of this study42 vvas that
the wing rock was not fundamentally altered by the individual removal of either
the canard or the wings or the vertical tail.
The use of a stability augmentation system (SAS) with roll rate feedback effec
tively suppresses the wing rock as shown in Fig. 8.60. With SAS off at 7 s, the
configuration rapidly develops wing rock. The traces of roll and yaw rates indicate
that the motion is predominantly a roll about the body axis. Turning the SAS on
at 18 s effectively suppressed the wing rock.
CL, deg
p, deg/s
r, deg/s
S, deg
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30
20
10
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PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL4(91)
