Automatic outer loop centering of aircraft inner loop

Details Automatic outer loop centering of aircraft inner loop Automatic outer loop centering of aircraft inner loop

1981-03-30

1983-05-24

Smith, Jerry

Boots, shoes, and leggings

244 1713, 244177, G06F 1550, G06G 778

Patent

active

043853552

ABSTRACT:
An aircraft automatic flight control system includes a pair of fast, limited authority inner loop actuators (12, 13) responsive to signals (52-55) indicative of aircraft attitude (68, 69) or other flight parameters such as airspeed (84), the inner loop being recentered by an outer loop actuator (37) responsive to attitude or other aircraft parameter-indicating signals (54, 55). Commands (40) applied to the outer loop are applied in a lagged fashion (58, 59) in opposite direction so as to drive the inner loop actuators (12, 13) back toward the center of their authority. The rate of response of the outer loop (FIG. 2, FIG. 5) is adaptive in dependence upon airspeed (93, 96, 212, 213) and in response to magnitude of inner loop input (101, FIG. 2). An integral gain (41), pulsed (39), open loop drive of the outer loop actuator (37) and outer loop automatic shutdown (38) are disclosed.

REFERENCES:
patent: 4004756 (1977-01-01), Gerstine et al.
patent: 4029271 (1977-06-01), Murphy et al.
patent: 4078750 (1978-03-01), Tomlinson
patent: 4109886 (1978-08-01), Tribken et al.
patent: 4213584 (1980-07-01), Tefft et al.
patent: 4279391 (1981-07-01), Adams et al.

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