Synthesized attitude and heading inertial reference

• US 5,841,537 A
• Filed: 08/11/1997
• Issued: 11/24/1998
• Est. Priority Date: 08/11/1997
• Status: Expired due to Term

• Current Assignee: Rockwell Collins, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Rockwell International Corporation
• Inventors: Doty, James H.
• Primary Examiner(s): Turner, Samuel A.
• Application Number:
  US08/909,479
• Time in Patent Office: 470 Days
• Field of Search: 356/350, 364/184, 364/187, 701/220, 702/221
• US Class Current: 356/484
• CPC Class Codes: G01C 19/72 with counter-rotating light beams in a passive ring, e.g. fibre laser gyrometers
• CPC Class Codes: G01C 21/166 Mechanical, construction or arrangement details of inertial navigation systems

Abstract

An inertial reference system for determining the attitude and rate of change of attitude of a vehicle such as an aircraft is disclosed. Redundancy of the inertial reference system may be accomplished by replacement of one of the fiber optic gyroscopes of an otherwise dual fiber optic gyros installation with a low-cost reference IMU. Failure detection and isolation of a fiber optic gyroscope system may be accomplished with a low-cost reference IMU rather than with an additional fiber optic gyroscope. The information provided by the eliminated fiber optic gyroscope is synthesized from the output of the remaining fiber optic gyroscope and the output of the low-cost reference IMU.

Claims

1. A high integrity sensor system consisting of:

a precision sensor system, a less precise secondary sensor system, and means to allow detection of a fault in the precision sensor system by utilizing signals from both sensor systems, wherein said means to allow detection of a fault utilizes a short-term stability characteristic of said secondary sensor system to detect faults while concomitantly correcting longer-term errors in said secondary sensor system.

2. Claim 1 wherein the means to allow detection of a fault in the precision sensor system consists of a system to produce a pseudo-independent output by utilizing data from both said primary and secondary sensor systems.

3. Claim 1 wherein said secondary sensor system has fewer axes of sensitivity than said precision sensor system, and wherein means are provided whereby at least some faults of the precision sensor system are detected.

4. Claim 2 wherein said secondary sensor system has fewer axes of sensitivity than said precision sensor system, and wherein means are provided whereby at least some of the faults of the precision sensor system are detected.

5. Claim 1 wherein said precision sensor system is an attitude and heading reference system and wherein said secondary sensor system is a reference inertial measurement unit.

6. An inertial reference system for determining the attitude and rate of change of attitude of a vehicle, comprising:

an attitude and heading reference system including at least three precision gyroscopes and an electronics system for providing attitude and rate of change of attitude information of the vehicle about a first directional axis; and

a second reference system for providing a reference signal, said second reference system provides an independent measurement of attitude and rate of change of attitude information of the vehicle; and

means, operationally connected to said attitude and heading reference system and to said second reference system, for synthesizing attitude and rate of change of attitude information of the vehicle about a second directional axis of the vehicle from said attitude and rate of change of attitude and from said reference signal.