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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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