Maneuver-force gradient system

Details Maneuver-force gradient system Maneuver-force gradient system

1983-02-22

1986-01-07

Lall, Parshotam S.

Boots, shoes, and leggings

244 1713, 244181, 318584, 318585, G05D 108

Patent

active

045637431

ABSTRACT:
A maneuver force gradient system causes a helicopter, that otherwise tends to pitch up in a banked turn, to pitch nose-down. A command signal (25) is provided as a function of the roll angle to operate the longitudinal trim actuator (27) which automatically moves the cyclic control (50) resiliently (28) forward to push the nose down. The pilot must consequently pull back on the cyclic control (50) to achieve a desired pitch attitude, thereby establishing a longitudinal positive maneuver-force gradient. The system is operable only when the pilot initiates a roll (33, 38, 50, 51) and the roll angle equals or exceeds 30.degree. (30, 33, 36, 37). Both analog (FIG. 1) and digital (FIG. 2) embodiments are disclosed, and the invention may be practiced in association with an AFCS (101) having the longitudinal trim actuator (27) and resilient linkage (28).

REFERENCES:
patent: 4067517 (1978-01-01), Barnum
patent: 4261537 (1981-04-01), Tisdale, Sr. et al.
patent: 4387430 (1983-06-01), Verzella et al.
patent: 4387432 (1983-06-01), Fischer et al.
patent: 4392203 (1983-07-01), Fischer et al.
patent: 4484283 (1984-11-01), Verzella et al.

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