Report of the Second Piloted Aircraft Flight Control System - Acgsc.org

lication of equations. - The method of applying equations (2)
the calculations of the traneient is presented in figure 3.
As ahown in figure 3, the end of the acceleration phaee 1; defined by
the inflection point of the solution of equation (6) for E > 1. For
E < 1, the second order equation may be used to approximate the entire
t&mient and therefore the inflection point need not be evaluated.
Figure 4 is a plot of rise time against no-load time conatant for a
range of values of inertia index. The chart is computed from the relations
shown in figure 3. The rise time is defined as the time to reach
90 percent of the flnal value.
erinrntal response. - Figure 5 shows the characteristic agreement
bctwe?calcuiated and meataured responses (reported in reference 1) in
a series of rune in vhidh the factors that determine the parameters T
and E have been varied. Ae can be sten, t& calculated rehnsee
have provided a close agpmdmation of the actual responses over a wide
range of conditions. It may be of particular interest to note that the
effect of magnitude of the input step ars predicted by the approximating
tiquatiom is evident in the measured responses.
Peak cylinder pressure during a transient. - In a transient under a
heavy load, the downstream cylinder presaure may exceed the supply pressure.
For this reason an evaluation of the peak cylinder pressure is
significant from a structural standpoint . It is shown in reference 1
that the ratio of the mnxrnnlm cylinder pressure to the supply pressure
is a function solely of the inertia index. The relation derived in reference
1 is plotted in figure 6. Also ihom in figure 6 are experimental
values reported in reference 1.
Response to a Sinu~oidal Input
Basic dynsmic considerations. - It has been shown that under an
inertia load, the trans'ient response of the servomotor is nonlinear,
The basic character of the transient response has been shown to vary
with time in the transient. It can therefore be expected that the frequency
response will also exhibit noanear characterXstics and that the
basic character of the response will vary with the frequency of the
input.
Law frequency amplitude attenuation and phase shiFt. - At low fre-
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