Fly by wire/fly by light control system with manual override

• US 5,197,697 A
• Filed: 02/08/1991
• Issued: 03/30/1993
• Est. Priority Date: 02/08/1991
• Status: Expired due to Fees

• Current Assignee: Rockwell International Corporation
• Original Assignee: Rockwell International Corporation
• Inventors: Pattison, David C., Lyloc, Woon
• Primary Examiner(s): Basinger, Sherman
• Assistant Examiner(s): BIDWELL, ANNE
• Application Number:
  US07/652,849
• Time in Patent Office: 781 Days
• Field of Search: 244/196, 244/197, 244/76 R, 244/75 R, 244/175
• US Class Current: 244/197
• CPC Class Codes: G05D 1/0061 for transition from automatic pilot to manual pilot and vice versa

Abstract

An improved fly by wire or fly by light system which provides for a smooth manual override of the autopilot function by allowing the pilot to modify the autopilot command to the control surfaces by physically manipulating the yoke to a position different than that commanded by the autopilot.

Claims

1. An improved flight control system comprising:

autopilot means for generating command signals;

means coupled with the autopilot means, for transmitting the command signal;

yoke signal generator means for generating a yoke signal corresponding to the orientation of a yoke in an aircraft cockpit;

means coupled with said yoke signal generator means, for transmitting the yoke signal;

comparator means, coupled with said means coupled with the autopilot means and the means coupled with said yoke signal generator means, for generating a deviation signal corresponding to the difference between said command signal and the yoke signal;

means for generating a modified command signal as a function of the deviation signal;

control surface servo means coupled with the means for generating a modified command signal for manipulating an aircraft control surface;

yoke servo means coupled with a yoke in an aircraft cockpit and further coupled with said means coupled with the autopilot means for transmitting the command signal, the yoke servo means for physically manipulating the yoke in response to the command signal;

means for modifying the deviation signal and thereby generating a deadened deviation signal where the deadened deviation signal corresponds to that portion of the deviation signal which exceeds a predetermined threshold;

wherein the means coupled with the autopilot means for transmitting the command signal comprises a conducting wire;

wherein the means coupled with said yoke signal generator means for transmitting the yoke signal comprises a conducting wire;

wherein the comparator means comprises an operational amplifier configured as a summer;

wherein the means for generating a modified command signal as a function of the deviation signal comprises an operational amplifier configured as a summer; and

wherein the means for modifying the deviation signal comprises an operational amplifier configured as a dead zone.

2. An improved flight control system comprising:

autopilot mans for generating command signals;

means coupled with the autopilot means, for transmitting the command signal;

yoke signal generator means for generating a yoke signal corresponding to the orientation of a yoke in an aircraft cockpit;

means coupled with said yoke signal generator means, for transmitting the yoke signal;

comparator means, coupled with said means coupled with the autopilot means and the means coupled with said yoke signal generator means, for generating a deviation signal corresponding to the difference between said command signal and the yoke signal;

means for generating a modified command signal as a function of the deviation signal;

control surface servo means coupled with the means for generating a modified command signal for manipulating an aircraft control surface;

yoke servo means coupled with a yoke in an aircraft cockpit and further coupled with said means coupled with the autopilot means for transmitting the command signal, the yoke servo means for physically manipulating the yoke in response to the command signal;

means for modifying the deviation signal and thereby generating a deadened deviation signal where the deadened deviation signal corresponds to that portion of the deviation signal which exceeds a predetermined threshold;

wherein the means coupled with the autopilot means for transmitting the command signal comprises a conducting wire; and

wherein the means coupled with said yoke signal generator means for transmitting the yoke signal comprises a conducting wire; and

wherein the comparator means, the means for generating a modified command signal and the means for manipulating the deviation signal comprise a digital processor.

3. A flight control system of claim 2 where the yoke signal generator means comprises a linear variable differential transformer.