Aircraft roll-yaw fault protocols

Details Aircraft roll-yaw fault protocols Aircraft roll-yaw fault protocols

1981-03-30

1984-11-20

Smith, Jerry

Boots, shoes, and leggings

244 1713, 244177, G06F 1550, G06G 770

Patent

active

044842830

ABSTRACT:
In an aircraft automatic flight control system, automatic shutdown (42) of the roll axis thereof (FIG. 1) as a consequence of faults detected therein also provides automatic shutdown of the yaw axis thereof (180) in the same fashion as detection of faults in the yaw axis (171, 167) provides shutdown of the yaw axis. Coupling of the roll axis shutdown into the yaw axis shutdown allows determining which of three axes cause lighting of a single trim shutdown indicator by resetting the yaw shutdown register (145) and simultaneously resetting both the pitch and roll shutdown registers by means of a single cyclic pitch control switch. Automatic yaw trim outer loop and yaw inner loop stability systems are disclosed (FIG. 2).

REFERENCES:
patent: 4003532 (1977-01-01), Adams, Sr. et al.
patent: 4067517 (1978-01-01), Barnum
patent: 4270168 (1981-05-01), Murphy et al.
patent: 4313201 (1982-01-01), Fischer et al.

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