Non-saturating airspeed/attitude controls

Details Non-saturating airspeed/attitude controls Non-saturating airspeed/attitude controls

1981-03-30

1983-05-24

Smith, Jerry

Boots, shoes, and leggings

244 1713, 244177, 244182, G06F 1550, G06G 778

Patent

active

043853560

ABSTRACT:
In a helicopter automatic flight control system having both automatic pitch attitude retention (70, 71) and automatic airspeed hold (84) and responsive both to pitch attitude error (206) and integrated (241) airspeed error (230), saturation of either the attitude error or integrated airspeed error circuitry is avoided by sensing (171) integrated airspeed error buildup to a threshold magnitude (which may be a significant fraction of the instantaneous authority of the automatic flight control system), and causing (169, 167) automatic slewing of the pitch attitude reference signal toward the current pitch attitude and reduction of the integrated airspeed error. In a disclosed embodiment, the correction of attitude reference and reduction of airspeed error is effected by utilizing an equal effective time constant (220, 221; 258, 259) for both actions over the same period of time (170, 168, 175).

REFERENCES:
patent: 3711042 (1973-01-01), Rempfer et al.
patent: 4129275 (1978-12-01), Gerstine et al.
patent: 4168045 (1979-09-01), Wright et al.
patent: 4206891 (1980-06-01), Perez et al.
patent: 4304375 (1981-12-01), Builta et al.

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