Charles E Bateman

US Patent:

7098810, Aug 29, 2006

Filed:

Feb 19, 2004

Appl. No.:

10/782055

Inventors:

Charles D. Bateman - Bellevue WA, US
John H. Gover - Bellevue WA, US
Steven C. Johnson - Issaquah WA, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

G08B 23/00

US Classification:

340963, 701 9, 701 11, 701301, 244197

Abstract:

Methods and systems for performing auto-recovery for an aircraft. An example system includes position and information systems, an automatic flight control system, a database, and a processor. The database includes terrain data, airport data, obstacle data, and protected airspace data. The processor determines if one of a caution alert or a warning alert exists based on data stored in the database and information received from the position and information systems. Auto-recovery instructions are generated and sent to the automatic flight control system if no positive flight control input has been performed at time of expiration of a waiting period. Auto-recovery instructions are generated based on an analysis of two or more auto-recovery routes. The system does not perform auto-recovery if components of the system fail to meet a predefined validity or integrity level.

US Patent:

7274308, Sep 25, 2007

Filed:

Dec 6, 2005

Appl. No.:

11/164808

Inventors:

Charles Donald Bateman - Bellevue WA, US
David Bryan Alexander Fleming - Kirkland WA, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

G08G 5/00

US Classification:

340959, 340945, 340963, 701 9, 701 14

Abstract:

A processor, software code, and a method for generating warning indicating that flaps are not suitably in a take-off position. A first component is configured to receive a first signal indicative of one of a group of flaps positions, the group including a take-off position. A second component is configured to receive a second signal indicative of an aircraft position. A third component is configured to compare the aircraft position to the contents of a database and to, by the comparison, determine whether the aircraft position is within a runway perimeter. A fourth component is configured to generate an alarm when the aircraft is within the runway perimeter and the flaps position is not the take-off position.

US Patent:

7626514, Dec 1, 2009

Filed:

Oct 4, 2006

Appl. No.:

11/538593

Inventors:

Yasuo Ishihara - Kirkland WA, US
Charles D. Bateman - Bellevue WA, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

G08G 5/00

US Classification:

340959, 340945, 340961, 340969, 340970, 340971, 244 751, 244182, 701 7, 701 9

Abstract:

Systems and methods for controlling activation of a look-ahead function of a terrain alert and warning system. The system receives rate of climb and aircraft speed information, compares the rate of climb and aircraft speed information to a predefined threshold, and deactivates a look-ahead function based on the comparison.

US Patent:

7670214, Mar 2, 2010

Filed:

Aug 31, 2006

Appl. No.:

11/469376

Inventors:

Kevin J Conner - Kent WA, US
Yasuo Ishihara - Kirkland WA, US
Charles D. Bateman - Bellevue WA, US

Assignee:

Honeywell International Inc. - Morristown NJ

International Classification:

B64D 13/02
B64D 13/00
B60H 1/00

US Classification:

454 74, 454 70, 454 71, 454 75, 454 76

Abstract:

Methods and systems for providing a depressurization alert. An example method includes receiving a cabin depressurization discrete signal, determining if the cabin depressurization discrete signal is valid, and issuing a cabin depressurization alert, if the cabin depressurization discrete signal was determined to be valid. In accordance with further aspects of the invention, a time delay is executed before the receiving, determining, and issuing steps are repeated. The cabin depressurization discrete signal is determined not valid if uncorrected pressure is not greater than a predefined altitude. The uncorrected pressure is a raw pressure value produced by a Pitot-Static system. Also, the cabin depressurization discrete signal is determined not valid if the aircraft's altitude above an intended runway is not greater than a first predefined value. Additionally, the cabin depressurization discrete signal is determined not valid if an aircraft's altitude above terrain is not greater than a second predefined value.

US Patent:

20070115140, May 24, 2007

Filed:

Nov 21, 2005

Appl. No.:

11/164392

Inventors:

Charles Bateman - Bellevue WA, US
David Fleming - Kirkland WA, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ

International Classification:

G08B 21/00

US Classification:

340945000

Abstract:

A processor, software code, and a method for generating warning indicating that flaps are not suitably in a take-off position. A first component is configured to receive a first signal indicative of one of a group of flaps positions, the group including a take-off position. A second component is configured to receive a second signal indicative of an aircraft position. A third component is configured to compare the aircraft position to the contents of a database and to, by the comparison, determine whether the aircraft position is within a runway perimeter. A fourth component is configured to generate an alarm when the aircraft is within the runway perimeter and the flaps position is not the take-off position.

US Patent:

20070239326, Oct 11, 2007

Filed:

Apr 5, 2006

Appl. No.:

11/398955

Inventors:

Steve Johnson - Issaquah WA, US
Yasuo Ishihara - Kirkland WA, US
Charles Bateman - Bellevue WA, US

International Classification:

G01C 23/00

US Classification:

701009000, 701003000

Abstract:

Systems and methods for monitoring an altitude in a flight vehicle are disclosed. In an embodiment, a system includes a barometric altimeter system operable to determine an altitude of the flight vehicle relative to a pressure datum that is adjustably selectable, and at least one altitude determination system that is operable to determine an altitude of the flight vehicle without reference to the selected pressure datum. A processor is coupled to the barometric altimeter system and to the at least one altitude determination system that is operable to receive altitude information from the barometric altimeter system and the at least one altitude determination system to compare the respective altitude information and determine if an altitude discrepancy exists.

US Patent:

20140039785, Feb 6, 2014

Filed:

Aug 1, 2012

Appl. No.:

13/564526

Inventors:

Charles Donald Bateman - Bellevue WA, US
Robert A. Champion - Mukilteo WA, US
Ruy C. Brandao - Redmond WA, US

Assignee:

HONEYWELL INTERNATIONAL INC. - Morristown NJ

International Classification:

B64D 43/00

US Classification:

701301

Abstract:

Systems and methods for improving the presentation of wake turbulence information. A processor located on an ownship receives position, heading and type information of another aircraft and position and heading information of the ownship. The processor determines if a possible wake condition exists from the other aircraft based on at least a portion of the received information and at least one predefined threshold and generates a wake icon if a wake condition is determined to exist. The wake condition exists when the ownship's altitude is below a first threshold altitude and above a second threshold altitude, wherein the first and second threshold altitudes are based on the other aircraft's altitude.

US Patent:

40300650, Jun 14, 1977

Filed:

Jul 19, 1976

Appl. No.:

5/706519

Inventors:

Charles Donald Bateman - Bellevue WA

Assignee:

Sundstrand Corporation - Rockford IL

International Classification:

G01C 500

US Classification:

340 27AT

Abstract:

By utilizing a radio altimeter in conjunction with a measure of the aircraft speed, landing gear position and flap position, an aircraft terrain warning system is made possible which provides a voice warning indicating that the aircraft is too low with respect to the terrain when the aircraft is above a predetermined speed. For aircraft speeds below the predetermined speed, a voice warning is provided when the aircraft is below a predetermined altitude with the landing gear up indicating that the aircraft is too low with the gear up and when the gear is down and the flaps are not in a landing position and the aircraft descends below a second predetermined altitude a voice warning is generated indicating that the aircraft is too low with flaps up.