Mark Charles Skarohlid

US Patent:

6668640, Dec 30, 2003

Filed:

Aug 12, 2002

Appl. No.:

10/217060

Inventors:

Steven Floyd Alwin - St. Paul MN
Dennis James Cronin - Shakopee MN
Mark Charles Skarohlid - Burnsville MN

Assignee:

Rosemount Aerospace Inc. - Burnsville MN

International Classification:

G01L 700

US Classification:

7317002

Abstract:

A system for providing independent and dissimilar aircraft parameter estimations includes first and second dual-channel electronic multi-function probes (MFPs) positionable adjacent an aircraft skin. Each dual-channel electronic MFP has pressure sensing ports and an electronics housing. Located within the electronics housing of each dual-channel electronic MFP are first and second electronics channels. The first electronics channel of the first dual-channel electronic MFP is electrically coupled with the first electronics channel of the second dual-channel electronic MFP can provide a first air data system providing aircraft parameter estimations. The second electronics channel of the first dual-channel electronic MFP can be electrically coupled with the second electronics channel of the second dual-channel electronic MFP to provide a second air data system providing aircraft parameter estimations. The first and second air data systems are independent and dissimilar from one another.

US Patent:

6761057, Jul 13, 2004

Filed:

Sep 13, 2001

Appl. No.:

09/952043

Inventors:

Dennis J. Cronin - Apple Valley MN
Thomas D. Amerson - Minneapolis MN
Roger D. Foster - Burnsville MN
Steve F. Alwin - St. Paul MN
Mark C. Skarohlid - Brooklyn Park MN

Assignee:

Rosemount Aerospace Inc. - Burnsville MN

International Classification:

G01C 2500

US Classification:

73 178, 702116

Abstract:

A method of detecting errors in air data sensing systems having multi-function probes being used in combinations to define probe systems includes a step (A) of, for each probe system, making a first prediction of an aircraft parameter as a function of local angles of attack at two member probes of the particular system, and making a second prediction of the aircraft parameter as a function of local pressure ratios at the two member probes of the particular system. A step (B) is performed in which, for each of the probe systems, the first and second predictions of the aircraft parameter are compared to determine whether the first and second predictions are within a predetermined threshold of each other. Then, a step (C) is performed in which, for each of the probe systems, if the first and second predictions of the aircraft parameter are not within the predetermined threshold of each other, then the particular probe system is identified as having a malfunctioning member probe.