Thrust and flight path control decoupling system

Details Thrust and flight path control decoupling system Thrust and flight path control decoupling system

1975-03-17

1976-11-02

Kunin, Stephen G.

Aeronautics and astronautics

Aircraft control

Automatic

73178R, 2351502, G05D 108

Patent

active

039892085

ABSTRACT:
Signals representative of the acceleration of an aircraft due to the change in flight path angle are coupled through a high pass filter (washout circuit) to obtain a short term compensation signal (V.sub.comp) which signal is further coupled to a low pass filter which provides short term integration to obtain the compansation signal (.DELTA. V.sub.comp) representative of change in speed in response to change in flight path angle. These compensation signals (V.sub.comp) and (.DELTA. V.sub.comp) are summed respectively with signals representative of longitudinal acceleration (or thrust control damping) and air speed error (or thrust control reference) to inhibit short term thrust control of the aircraft due to small flight path angle perturbations thereby improving the manual path control handling quality and the stability of the aircraft by the automatic control system. A modification of the system is disclosed for avoiding sensor noise developed by the .alpha. (angle of attack) vane sensor by utilization of other inputs to the system signal processing.

REFERENCES:
patent: 3448948 (1969-06-01), Reerink
patent: 3594553 (1971-07-01), McElroy
patent: 3748900 (1973-07-01), Lindquist
patent: 3774017 (1973-11-01), Zagalsky
patent: 3901466 (1975-08-01), Lambregts

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