Aircraft lift control system with acceleration and attitude limi

Details Aircraft lift control system with acceleration and attitude limi Aircraft lift control system with acceleration and attitude limi

1981-09-08

1984-11-27

Smith, Jerry

Boots, shoes, and leggings

244181, 364433, G06G 778

Patent

active

044854463

ABSTRACT:
An aircraft vertical lift guidance signal is developed for providing optimum aircraft lift with limiting to avoid excessive acceleration and attitude. A lift computer produces an angle of attack signal as a function of aircraft altitude rate minus longitudinal acceleration such that demand increases in acceleration result in an increased angle of attack, thereby limiting acceleration. Attitude limiting is achieved by limiting the longitudinal signal to a constant value in response to aircraft acceleration exceeding a reference level.

REFERENCES:
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patent: 3805033 (1974-04-01), Manke et al.
patent: 3814912 (1974-06-01), Manke et al.
patent: 3901466 (1975-08-01), Lambregts
patent: 4019702 (1977-04-01), Annin
patent: 4106094 (1978-08-01), Land
patent: 4326253 (1982-04-01), Cooper et al.
patent: 4347572 (1982-08-01), Berwick, Jr. et al.
patent: 4390950 (1983-06-01), Muller

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