OPEN-LOOP ROLL CONTROL

When investigating open-loop roll control it is appropriate to consider the ratio of the roll time constant TR to some typical maneuver time tm, and/or the maximum roll acceleration following a unit step aileron input. The Laplace transform of the roll acceleration following a unit step aileron input (Д5Я = 1 js) can be found from (12.9,3)

ТцАф

TgS + 1

The maximum roll acceleration occurs at t = 0, and from the initial value theorem is

Figure 12.19 gives the pilot rating boundaries obtained from roll response studies of fighter-type aircraft (ref. 12.15). The lower boundary on these iso-opinion curves is blamed on oversensitivity of the controls and probably

Fig. 12.19 Pilot rating of open-loop roll re­sponse (from ref. 12.15).

has the same basis as the poor ratings achieved with overly large values of the CAP discussed in the section on longitudinal handling qualities.