Aircraft short-term roll attitude retention system

Details Aircraft short-term roll attitude retention system Aircraft short-term roll attitude retention system

1981-11-27

1985-02-19

Smith, Jerry

Boots, shoes, and leggings

244178, G06F 1550, B64C 1100

Patent

active

045009678

ABSTRACT:
An automatic flight control system, for an aircraft having a roll attitude retention outer loop actuator (29), a roll stability inner loop actuator (25) and a control stick (26) for positioning control surfaces of the aircraft to control its roll attitude, includes means (54, 55) to provide a roll error signal (56) indicative of the deviation in roll attitude from a desired roll attitude. The roll attitude retention outer loop actuator (29) is controlled by a proportional (61) and integral (62) function of the roll error when force is not applied to the stick, but only as a proportional function when force is applied to the stick (48, 49, 51, 62). The roll stability inner loop actuator is controlled by a washed out (72) proportional (64) function of the roll error signal to provide short-term roll retention at roll attitudes established by the control stick during turns against trim. Sensing force on the stick (51, 95, FIG. 1) and roll attitude of a predetermined threshold magnitude (107) provides adjustments in relative gain (113, 117, 70, 71, FIG. 1; 154, 157, 160-163, FIG. 4) during turns against trim.

REFERENCES:
patent: 3921941 (1975-11-01), Lehfedt
patent: 4371936 (1983-02-01), Adams et al.
patent: 4371939 (1983-02-01), Adams et al.
patent: 4385355 (1983-05-01), Verzella et al.

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