ROLLING MODE

It was observed in Sec. 6.7 that the rolling convergence is a motion of almost a single degree of freedom, rotation about the x-axis. This suggests that it can be approxi­mated with the equation obtained from (4.9,19) by putting v = r = 0, and consider­ing only the second row, that is,

p = $„P (6-8,7)

which gives the approximate eigenvalue

XR = %P = LpH’x + I’zxNp (6.8,8)

The result obtained from (6.8,8) for the B747 example is AR = —0.434, 23% smaller than the true value -0.562. This approximation is quite rough.

An alternative approximation has been given by McRuer et al. (1973). This ap­proximation leads to a second-order system, the two roots of which are approxima­tions to the roll and spiral modes. In some cases the roots may be complex, corre­sponding to a “lateral phugoid”—a long-period lateral oscillation. The approximation corresponds to the physical assumption that the side-force due to gravity produces the same yaw rate r that would exist with /3 = 0. Additionally Yp and Yr are ne­glected. With no approximation to the rolling and yawing moment equations the sys­tem that results for horizontal flight is

0 = ~u0r + g(f) (a)

p = !£vv + !£pp + £rr (b)

r = Jfvv + Ярр + Ягг (c) (6.8,9)

ROLLING MODE ROLLING MODE

Ф = P (d)

The result of applying (6.8,11) to the B747 example is

A, = -0.00734 and A* = -0.597

These are within about 1 % and 6% of the true values, respectively, so this is seen to be a good approximation for both modes, certainly much better than (6.8,7) for the rolling mode.

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