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STATIC STABILITY AND CONTROL 253
We observe that the stick-free maneuver stability is higher than the stick-free
stability in level flight and the stick-free maneuver point is aft of the stick-free
neutral point. This increase in stick-free stability during the maneuver, as said
before,is caused by the angular velocity S2 and the associated increase in tail angle
of attack Acti.r. The stick-free maneuver margin is given by
For a stable aircraft, H:n > 0.
HL = NL - xcg
(3.209)
Stick force gradient. As we know, the stick force is directly proportional to
A8e = 8e.R - 8V:/, the difference between the required elevator deflection and the
floating angle of the elevator. Recall that these two quantities are also related to
the stick-fixed and the stick-free stability levels of the airplane, respectively.
From Eq. (3.101), we have
8e.R = - CC., &~i ), (3.210)
The floating angle of the elevator is given by
so that
= - C;~B as (3.211)
Cha
= - C,,., [C.. (1 - : ) + s-2j ] (3.212)
A8e = 8e.R - 8e.f (3.213)
CL
=-cC.,GC~),+~C [C (i-J)+'2J-] (3.214)
Differentiating with respect to CL and rearranging, we obtain
dA8e
(3,215)
d~ = - 01, &~ )..
In incremental form, we can write the above equation as
(3.216)
A8e = _ACC., G~: ),.
The corresponding increment in hinge-moment coefficient is given by
ACh = Ch8.e A8e (3.217)
Ch8.,
=- AC G~),. . (3.218)
The incremental stick force, i.e., the additional stick force above that required in
254 PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
level fiight, is given by .
AFs - -Gi AHM
(3.219)
= -G i qr Scce ACh (3.220)
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