Maneuver detector circuit for use in autothrottle control systems having thrust and flight path control decoupling

• US 4,155,525 A
• Filed: 10/25/1977
• Issued: 05/22/1979
• Est. Priority Date: 10/25/1977
• Status: Expired due to Term

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Peter-Contesse, Henri
• Primary Examiner(s): Kunin, Stephen G.
• Application Number:
  US05/844,684
• Time in Patent Office: 574 Days
• Field of Search: 73/178 R, 244/181, 244/182, 244/188, 340/27 R, 340/27 AT, 340/27 SS, 364/431, 364/434, 364/440
• US Class Current: 244/182
• CPC Class Codes: G05D 1/063 by acting on the motors

Abstract

A maneuver detector generates a maneuver-detect signal when signals representative of elevator deflection and flight path deviation are representative of a deliberate maneuver condition and no maneuver-detect signal when the relationship of the two signals is indicative of elevator deflection such as to oppose a flight path deviation, e.g., as caused by turbulence condition or configuration change.

Claims

1. In combination in an autothrottle control system for an aircraft having an input terminal for receiving a signal representative of compensated longitudinal acceleration:

means for providing a first signal representative of -V+ g/w Δ

T)

where

V= aircraft longitudinal acceleration, inertial

g= gravity constant,

w= aircraft weight, and

Δ

T= incremental change in thrust;

variable time constant filter means responsive to said first signal for providing a first compensation signal;

means for providing a signal representative of longitudinal acceleration information of said aircraft;

means having an output terminal for combining said first compensation signal and said signal representative of longitudinal acceleration information of said aircraft for providing said signal representative of compensated longitudinal acceleration at said output terminal, said output terminal coupled to said input terminal;

a maneuver detector circuit for generating a maneuver detect signal when signals representative of elevator deflection and flight path deviation are representative of a deliberate maneuver condition and a non-maneuver detect signal when said signals representative of elevator deflection and flight path deviation are indicative of elevator deflection such as to oppose a flight path deviation of the aircraft due to turbulence or configuration change of the aircraft; and

,

integrating and limiting circuit means coupled between said maneuver detector circuit and said variable time constant filter means.

2. In combination in an autothrottle control system for an aircraft having an input terminal for receiving a signal representative of compensated longitudinal acceleration:

means for providing a first signal representative of (-V+ g/W Δ

T)

where

V= aircraft longitudinal acceleration, inertial

g= gravity constant,

W= aircraft weight, and,

T= incremental change in thrust;

variable time constant filter means responsive to said first signal for providing a first compensation signal;

means for providing a signal representative of longitudinal acceleration information of said aircraft;

means having an output terminal for combining said first compensation signal and said signal representative of longitudinal acceleration information of said aircraft for providing said signal representative of compensated longitudinal acceleration at said output terminal, said output terminal coupled to said input terminal;

a maneuver detector circuit;

integrating and limiting circuit means coupled between said maneuver detector circuit and said variable time constant filter means; and

wherein said means for providing a first signal representative of (-V+ g/WΔ

T) comprises;

summing circuit means responsive to a plurality of signals representative of a thrust paratmeter of a corresponding plurality of engines for said aircraft for providing a summary circuit output signal;

gain programming circuit means responsive to a signal representative of altitude of the aircraft for providing a gain programming circuit output signal;

multiplier circuit means responsive to said summing circuit output signal and said gain programming circuit output signal for providing a signal representative of+ (g/W)Δ

T; and

summing amplifier circuit means responsive to said signal representative of+ (g/W)Δ

T and said signal representative of longitudinal acceleration information of said aircraft for providing said first signal representative of (-V+ g/WΔ

T).

3. An aircraaft maneuver detector circuit having an output terminal for providing a positive polarity signal upon the occurrence of a pilot-initiated maneuver, said circuit comprising:

means for providing a signal representative of elevator deflection;

means for providing a signal representative of flight path deviation;

multiplier circuit means responsive to said signal representative of elevator deflection and said signal representative of flight path deviation for providing said positive polarity signal upon the occurrence of said pilot-initiated maneuver and a negative polarity signal upon the occurrence of other maneuvers; and

,

a diode coupled between said multiplier circuit means and said output terminal for providing said positive polarity signals at said output terminal upon the occurrence of said pilot-initiated maneuver.