Aircraft pitch attitude signal generator

A circuit for use in aircraft having a longitudinal accelerometer signal source, a vertical gyroscope signal source and an air speed signal source, for computing a signal representing the horizontal acceleration of the aircraft, comprising:

• means for combining the longitudinal accelerometer signal with the gyroscope signal to generate a horizontal acceleration signal;
• means, responsive to said air speed signal, to generate an acceleration signal based on air speed;
• means for combining a function of said horizontal acceleration signal with said air acceleration signal to generate an acceleration error signal;
• and
• means for combining a function of said acceleration error signal with said horizontal acceleration signal to generate the computed acceleration signal.

A circuit for generating a computed pitch signal for use in aircraft having an air speed signal source, a longitudinal accelerometer signal source, and a vertical gyroscope signal source representing pitch attitude, comprising:

• a first summing junction circuit for subtracting the longitudinal accelerometer signal from the gyro pitch signal to produce a longitudinal acceleration signal;
• a second summing junction circuit for summing said longitudinal acceleration signal with an acceleration correction signal to produce a computed acceleration signal;
• a differentiating circuit for differentiating said air speed signal;
• a third summing junction circuit for subtracting said computed acceleration signal from said differentiating air speed signal to produce an acceleration error signal;
• a first integrator circuit for integrating said acceleration error signal to produce said acceleration correction signal;
• a fourth summing junction circuit for subtracting said computed acceleration signal from the gyro pitch circuit to produce an inertial pitch circuit;
• a fifth summing junction circuit for subtracting the computed pitch signal from said inertial pitch signal to produce a pitch error signal;
• a second integrator circuit for integrating said pitch error signal to produce a pitch correction signal;
• and
• a sixth summing junction circuit for combining said pitch correction signal with the gyro pitch circuit to produce the computed pitch circuit.