Aircraft short-term roll attitude retention system

• US 4,500,967 A
• Filed: 11/27/1981
• Issued: 02/19/1985
• Est. Priority Date: 11/27/1981
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Murphy, Richard D., Clelford, Douglas H., Perez, Ricardo L.
• Primary Examiner(s): Smith, Jerry
• Assistant Examiner(s): Fleming, Michael R.
• Application Number:
  US06/325,391
• Time in Patent Office: 1,180 Days
• Field of Search: 364/434, 364/435, 244/178, 244/179, 244/17.13
• US Class Current: 701/12
• CPC Class Codes: G05D 1/0061 for transition from automatic pilot to manual pilot and vice versa
• CPC Class Codes: G05D 1/0858 specially adapted for vertical take-off of aircraft

Abstract

An automatic flight control system, for an aircraft having a roll attitude retention outer loop actuator (29), a roll stability inner loop actuator (25) and a control stick (26) for positioning control surfaces of the aircraft to control its roll attitude, includes means (54, 55) to provide a roll error signal (56) indicative of the deviation in roll attitude from a desired roll attitude. The roll attitude retention outer loop actuator (29) is controlled by a proportional (61) and integral (62) function of the roll error when force is not applied to the stick, but only as a proportional function when force is applied to the stick (48, 49, 51, 62). The roll stability inner loop actuator is controlled by a washed out (72) proportional (64) function of the roll error signal to provide short-term roll retention at roll attitudes established by the control stick during turns against trim. Sensing force on the stick (51, 95, FIG. 1) and roll attitude of a predetermined threshold magnitude (107) provides adjustments in relative gain (113, 117, 70, 71, FIG. 1; 154, 157, 160-163, FIG. 4) during turns against trim.

Claims

1. An aircraft automatic flight control system comprising:

a vertical gyro providing a roll axis output signal indicative of the direction and magnitude of bank angle of the aircraft with respect to level;

roll control means, including a pilot control stick and actuator means including a roll attitude retention outer loop portion and a roll stability inner loop portion, for providing commands to the control surfaces of the aircraft for controlling the roll attitude of the aircraft, lateral force on said control stick providing input commands to said control surfaces which override input commands related to the positioning of said roll attitude retention outer loop portion; and

signal processing means responsive to said roll axis output signal of said vertical gyro and connected to said roll control means, for selectively providing a desired roll attitude reference signal, for providing a roll error signal indicative of the difference in roll attitude indicated by said desired roll attitude reference signal and said roll axis output signal, responsive to said roll control means for providing a signal indicative of lateral force in excess of a predetermined threshold magnitude being applied to said control stick, for providing to said roll attitude retention outer loop portion a first roll command signal which is a first proportional function of said roll error signal in response to the presence of said force signal and which is both said first proportional function and an integral function of said roll error signal in response to the absence of said force signal, for providing a second roll command signal to said roll stability inner loop portion which is a second proportional function of said roll error signal;

characterized by;

said signal processing means providing said second roll command signal to said roll stability inner loop portion which is a washed out proportion of said roll error signal, whereby a turn induced by lateral force applied to said control stick against a trim position established by said roll attitude retention outer loop portion in response to said roll error signal will be stabilized by said roll stability inner loop portion responding to said washed out function of said roll error signal to stabilize the aircraft against attitude perturbations which result in short-term changes in said roll error signal.

2. An aircraft automatic flight control system according to claim 1 characterized by said signal processing means being responsive to said roll error signal and to said force signal to provide a turn against trim signal indicative of a roll angle in excess of a predetermined threshold magnitude being established by lateral force of the stick, against a trim attitude established by said roll attitude retention outer loop portion in response to said roll error signal, and for providing, in response to presence of said turn against trim signal, said first and second roll command signals with the ratio of said first proportional function to said second proportional function being greater than the ratio thereof in the absence of said turn against trim signal.

3. An automatic flight control system according to claim 2 characterized by said signal processing means being responsive to the absence of said force signal and said roll error signal indicating an aircraft roll attitude of less than a predetermined termination magnitude to cease providing said turn against trim signal.