Method and apparatus for limiting attitude drift during turns

• US 20020193916A1
• Filed: 08/09/2002
• Published: 12/19/2002
• Est. Priority Date: 12/22/1999
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Wilson, Ronald D., Lehfeldt, James J., Katz, Kenneth P., Oberg, Joseph M., Sample, William G.
• Granted Patent: US 6,556,897 B2
• Time in Patent Office: Days
• US Class Current: 701/4
• CPC Class Codes: G01C 19/30 Erection devices, i.e. devices for restoring rotor axis to a desired position for instrument indicating the vertical G01C19/46
• CPC Class Codes: G01C 21/18 Stabilised platforms, e.g. by gyroscope
• CPC Class Codes: G01C 21/188 for accumulated errors, e.g. by coupling inertial systems with absolute positioning systems

Abstract

An apparatus, method and computer program product useful for supplying the pilot of an aircraft with aircraft attitude information. During bank angles exceeding a predefined limit, the roll gyro is slaved to a roll angle estimator for improved system accuracy.

Claims

1. An apparatus for outputting roll angle information comprising:

an input for receiving a signal indicative of roll rate;

a first device, coupled to said input, for obtaining an Euler roll angle from said signal;

a first error correction device, coupled to said first device, for correcting errors in said Euler roll angle;

a second error correction device, coupled to said first error correction device, for supplying a roll angle estimate to said first error correction device, during a period of time when said Euler roll angle exceeds a predefined limit; and

an output for outputting a signal indicative of corrected roll angle information.

2. The apparatus of claim 1 wherein said apparatus comprises a feedback control loop.

3. The apparatus of claim 1 wherein said second error correction device further comprises:

a roll angle estimator input for receiving a plurality of signals indicative of an airspeed and a yaw rate;

a roll angle estimator for obtaining said roll angle estimate as a function of said airspeed, said yaw rate and acceleration due to gravity; and

an output, coupled to said first error correction device, for outputting a signal indicative of said roll angle estimate.

4. The apparatus of claim 3 wherein said second error correction device further comprises:

an auxiliary input for receiving a roll level sensor signal; and

means for combining said roll level signal with said roll estimate signal to obtain said signal indicative of said roll angle estimate.

5. The apparatus of claim 1 wherein said predefined limit is six degrees.