Aeronautics and astronautics – Aircraft control – Automatic
Patent
1976-02-23
1977-08-23
Kunin, Stephen G.
Aeronautics and astronautics
Aircraft control
Automatic
244195, 318563, G05D 100
Patent
active
040435261
ABSTRACT:
A system for rapidly disengaging, with minimum nuisance disengagements, a nventional autopilot system upon detecting hardover failure, which is defined as any autopilot failure which results in rapid and sustained displacement of an aircraft aerodynamic control surface. The aircraft pitch rate is measured and compared with established limits. If these limits are exceeded, the system causes automatic disengagement. Disengagement is inhibited for gust disturbances by deriving a nose up or down signal from the pitch rate signal which is then compared with a signal indicating the direction of elevator hinge moment; if the two directions are opposing, disengagement is inhibited. Disengagement is also inhibited in the event of pilot action. Also, the autopilot pitch axis command line is monitored and a disengagement overriding any inhibits is generated when the signal on that line exceeds certain limits for the altitude hold mode and for the attitude hold mode of the autopilot.
REFERENCES:
patent: 2762962 (1956-09-01), Meredith et al.
patent: 3880385 (1975-04-01), Reynolds et al.
patent: RE25491 (1963-12-01), Lee et al.
Donley Shawn T.
Freitag Valentine A.
Hansen Henry
Kunin Stephen G.
Sciascia R. S.
The United States of America as represented by the Secretary of
Weinstein Stanton D.
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