Aircraft pitch attitude signal generator

Details Aircraft pitch attitude signal generator Aircraft pitch attitude signal generator

1977-04-20

1978-06-13

Ruggiero, Joseph F.

Boots, shoes, and leggings

73178R, 244181, 244191, 340 27NA, 364453, G06G 778

Patent

active

040952711

ABSTRACT:
In order to provide a more accurate representation of aircraft pitch attitude for use in aircraft head up display devices, a circuit for generating a computed pitch signal responds to a longitudinal accelerometer and a vertical gyroscope within the aircraft wherein the computed pitch signal is generated by adding to the gyro pitch signal a correction factor computed by subtracting the value of the computed pitch signal from an inertial pitch signal derived from the longitudinal accelerometer. In order to compensate for the effects of aircraft acceleration on the longitudinal accelerometer signal, a computed acceleration signal derived from the difference between the longitudinal accelerometer signal and the gyro pitch signal is subtracted from the longitudinal accelerometer to generate the inertial pitch signal. To further compensate the systems for long term errors in the gyro pitch signal, the combined longitudinal acceleration and gyro pitch signal is subtracted from a differentiated air speed signal and the resulting difference signal is integrated over time to generate an acceleration correction signal that is applied to the computed acceleration signal.

REFERENCES:
patent: 3215374 (1965-11-01), Olshausen
patent: 3686626 (1972-08-01), Bateman et al.
patent: 3691356 (1972-09-01), Miller
patent: 3851303 (1974-11-01), Muller
patent: 3948096 (1976-04-01), Miller
patent: 4012713 (1977-03-01), Greene et al.

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