Glide slope control signal processing system
AssigneeThe Boeing Company
InventorsJimmie H. Boone, Robert D. Simpson
Life of this patent
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Abstract
A rate-limited, signal magnitude limited, non-linearized lag circuit for processing glide slope error signals to reject noise and reduce aircraft response to hardover signals due to ground transmitter malfunctions or other anomalies. A feature of an embodiment includes a logic circuit connected to the lag circuit for preventing aircraft deviation due to hardover signals.
Claims5
In combination in a pitch axis control system for an aircraft having longitudinal axis control surfaces:
- means for generating a signal representative of glide slope error;
- means including a servo system connected to drive said longitudinal axis control surfaces;
- rate limited lag circuit means including an integrator circuit coupled between said means for generating a signal representative of glide slope error and said means including a servo system connected to drive said longitudinal axis control surfaces;
- and, logic circuit means connected in circuit between said means for generating a signal representative of glide slope error and said rate limited lag circuit means for controlling the output of said integrator circuit.
In a glide slope control system for an aircraft, a circuit for processing signals representative of glide slope error comprising:
- adder circuit means having a first input terminal adapted for coupling signals to representative of glide slope error, a second input terminal, and an output terminal;
- signal limiter circuit means;
- integrator circuit means having first and second input terminals and an output terminal;
- said signal limiter circuit means coupled in circuit path between said output terminal of said adder circuit means and said first input terminal of said integrator circuit means;
- feedback circuit means connected to provide feedback gain between said output terminal of said integrator circuit means and said second input terminal of said adder circuit means;
- and, further feedback circuit means connected between said output terminal of said integrator circuit means and said second input terminal of said integrator circuit means for providing command signal limiting.
In combination in a glide slope control system for providing glide slope command signals in an aircraft having first means for providing signals representative of glide slope error, and second means for providing signals representative of glide slope error rate:
- glide slope error detector circuit means responsive to said signals representative of glide slope error for providing a first logic control output signal when said signal representative of glide slope error exceeds a predetermined amplitude level;
- glide slope error rate detector circuit means responsive to said signals representative of glide slope error rate for providing a second logic control output signal when said signal representative of glide slope rate exceeds a predetermined rate;
- and
- And circuit means responsive to said first and second logic control output signals for maintaining a constant amplitude glide slope command signal.
Dependencies are inferred from the claim text.