Aeronautics and astronautics – Aircraft control – Automatic
Patent
1976-12-16
1978-05-16
Blix, Trygve M.
Aeronautics and astronautics
Aircraft control
Automatic
91361, 91363R, 244 83G, 244 85, 318628, G05D 110
Patent
active
040894940
ABSTRACT:
In a hydraulic actuator such as those used in multiple degree freedom motion bases for aircraft simulators, a secondary force sensitive hydraulic servo loop is added in parallel to the primary position feedback servo loop with the secondary loop having a servo valve possessing substantially greater band pass and less capacity than the main valve used in the first servo loop. Force feedback from the control actuator is applied degeneratively to the smaller servo valve, thereby reducing noise and jitter caused by responses of the system outside the response of the primary servo loop. The response of the main servo loop which control the position of the actuator is low pass and restricts response to the full desired band pass of operational frequencies. The secondary loop is high pass and is shaped to prevent degeneration of operational frequencies while providing optimum gain and phase for the degeneration of the unwanted high frequency portion of the band wherein noise and jitter reside.
REFERENCES:
patent: 3120787 (1964-02-01), Schmitt
patent: 3552271 (1971-01-01), Suggs
patent: 3752189 (1973-08-01), Marr
Anderson Alvin M.
Comley William
Engum Douglas B.
Blix Trygve M.
Eisenzopf Reinhard J.
Jason Walter J.
McDonnell Douglas Corporation
Royer Donald L.
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