Helicopter control with multiple schedule rotor speed decay anticipator
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United States of America Patent
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-
Jun 4, 1991
Grant Date -
N/A
app pub date -
May 19, 1989
filing date -
May 19, 1989
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
The speed 54,56 of the free turbine 40 of a helicopter engine 22 is compared 134,138 with the speed 142,140 of the helicopter rotor 10 to indicate 106,108 a specific magnitude of autorotation and the deceleration 150 of the rotor above either one of two threshold magnitudes 220,222 (dependent on the magnitude of autorotation) is utilized 81,68,69 to increase fuel flow 72 to the engine according to a specific schedule 160,162 determined by the type of autorotation, in anticipation of rotor speed droop which would otherwise occur during recovery from the autorotation maneuver.
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