Fail safe system with common mode avoidance

• US 5,631,656 A
• Filed: 03/01/1995
• Issued: 05/20/1997
• Est. Priority Date: 03/01/1995
• Status: Expired due to Term

• Current Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Original Assignee: Honeywell Incorporated (Honeywell International Inc.)
• Inventors: Girts, Robert D., Hartman, Randolph G.
• Primary Examiner(s): Issing, Gregory C.
• Application Number:
  US08/397,297
• Time in Patent Office: 811 Days
• Field of Search: 342/357, 342/173, 364/424.03, 364/439
• US Class Current: 342/357.32
• CPC Class Codes: G01S 1/026 of associated receivers

Abstract

A fail operational system including two sets of first and second sensors responsive to different stimuli to produce signals indicative of a condition, and a comparator for comparing the outputs of the first and second sensors to produce a "valid" signal when the outputs are substantially the same.

Claims

1. A fully monitored system comprising:

a first sensing unit responsive to a first set of variables to produce a first output indicative of a condition;

a second sensing unit responsive to a second set of variables different from the first set of variables to produce a second output indicative of the condition;

comparing means receiving the first and second outputs and producing a valid output only if the first and second outputs are substantially the same.

2. Apparatus according to claim 1 further including receiving means connected to receive one of the first and second outputs and connected to the comparing means to receive the valid output to indicate that the one of the first and second outputs is valid.

3. Apparatus according to claim 2 wherein the first sensing unit is an inertial reference unit, the second sensing unit is a global position sensor and the receiving means is the flight control system of an aircraft.

4. Apparatus according to claim 3 wherein the first set of variables is the output of a plurality of gyroscopes and accelerometers, and the second set of variables is the signals from satellites.

5. Apparatus according to claim 4 wherein the first and second outputs relate to aircraft attitude and attitude rate.

6. Apparatus according to claim 5 wherein the first and second outputs relate to aircraft position.

7. Apparatus according to claim 2 further including a second fully monitored system having a third sensing unit like the first sensing unit and responsive to the first set of variables to produce a third output indicative of the condition, having a fourth sensing unit like the second sensing unit and responsive to the second set of variables to produce a fourth output indicative of the condition, and having a second comparator operable to produce a second valid output only when the third and fourth output are substantially the same, said receiving means receiving one of the third and fourth outputs and the second valid output to indicate that the one of the third and fourth outputs is valid.