Tested, dissimilar helicopter stability augmentation

Details Tested, dissimilar helicopter stability augmentation Tested, dissimilar helicopter stability augmentation

G - Physics

05

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341/81

G05D 1/08 (2006.01) G05D 1/00 (2006.01)

Patent

CA 1153810

- 24 - Tested, Dissimilar Helicopter Stability Augmentation Abstract The main roll and yaw axes of a helicopter having a main rotor operative in response to cyclic and col- lective pitch commands and a tail rotor operative in response to pitch commands, include stability inputs to actuators which are selectively provided by an analog channel, a digital channel, or one half by each, the digital channels being manifested in a digital computer system which includes programs of self-test, in-flight comparison between the inputs and outputs of corresponding analog and digital chan- nels, and ground tests of testable rate gyro inputs to the various digital and analog channels and the outputs thereof.

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