Steven D Colby

US Patent:

20130179011, Jul 11, 2013

Filed:

Jan 10, 2012

Appl. No.:

13/347109

Inventors:

Steven D. Colby - Owego NY, US
Stephen C. Moraites - Owego NY, US

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

G06F 19/00
G05D 1/00

US Classification:

701 16

Abstract:

Systems and methods for automatically identifying one or more candidate emergency landing sites to a pilot of an aircraft are described. The candidate emergency landing sites lie within a current flight-capable range of an aircraft, and may include non-airfield landing sites. The candidate sites may be calculated by an on-board processing system. Various types of data, such as digital terrain elevation data, ground-cover data, hostile-threat data, surface-water data, aircraft parameter data, and flight-obstacle data may be used by an on-board processing system to calculate one or more candidate emergency landing sites suitable for landing the aircraft. A pilot may initiate an emergency landing site identification process during in-flight distress via a button, touch-sensitive screen, or voice-recognition input. The systems and methods may be useful in combat scenarios.

US Patent:

20130249262, Sep 26, 2013

Filed:

Mar 22, 2012

Appl. No.:

13/427425

Inventors:

Carl R. Herman - Owego NY, US
Jason C. Twedt - Waverly NY, US
Jean-Francois Darcy - Pittsford NY, US
Steven D. Colby - Owego NY, US

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

B64D 11/06
G08B 6/00
G08B 23/00
B60R 22/00
B60N 2/66

US Classification:

2972171, 340963

Abstract:

A system for tactile presentation of information to a pilot of an aircraft. The system comprises a pilot seat, a plurality of tactors, and a controller configured to control the plurality of tactors to tactually present the threat information to the pilot by producing one or more tactile stimuli based on situational awareness information. The tactors in the plurality of tactors are physically coupled to the pilot seat and the threat information is indicative of a threat to the aircraft. In some embodiments, at least one pressure sensor may be physically coupled to the pilot seat and the plurality of tactors may be configured to tactually present the threat information to the pilot based at least in part on data obtained by the at least one pressure sensor.

US Patent:

20170183104, Jun 29, 2017

Filed:

Sep 8, 2016

Appl. No.:

15/259805

Inventors:

- Bethesda MD, US
Steven D. Colby - Owego NY, US

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

B64D 45/00
G01C 21/00

Abstract:

Some embodiments include a countermeasure assistance system that, in response to detecting a threat to an aircraft, calculates and presents via a user interface an instruction to assist a pilot in evading the threat. For example, the system may determine a direction to which the aircraft should be turned to present a beam of the aircraft toward the threat, which may assist in evading a radar-enabled threat. The system may calculate a shortest turn to present the beam to the threat. The system may additionally display information regarding a position, nature, and degree of the threat, including through formatting of at least a portion of a user interface for displaying information regarding the threat. The system may additionally calculate and display an intervisibility zone for the threat and for the aircraft's current position to further assist the pilot in navigating to an area at which the threat may be evaded.

US Patent:

20170096237, Apr 6, 2017

Filed:

Jun 29, 2016

Appl. No.:

15/196367

Inventors:

- Bethesda MD, US
Steven D. COLBY - Owego NY, US

International Classification:

B64D 45/00

Abstract:

Combined modality hover drift cueing methods, systems and computer readable media are disclosed. For example, some implementations can include a system comprising one or more sensors, and a combined modality hover drift cueing controller coupled to the one or more sensors and configured to determine hover drift and to control a plurality of indicators in response to determined hover drift. The system can also include a mode selector coupled to the combined modality hover drift cueing controller and configured to provide an indication of mode selection between one of a first mode, a second mode and a third mode, wherein the first mode is a combined modality mode. The system can further include a peripheral vision hover drift indicator coupled to the controller and mounted on an inside surface of an aircraft cockpit, and a tactile feedback indicator coupled to the controller.

US Patent:

20170059354, Mar 2, 2017

Filed:

Jun 10, 2016

Appl. No.:

15/179270

Inventors:

- Bethesda MD, US
Steven D. COLBY - Owego NY, US

International Classification:

G01C 23/00

Abstract:

Projected synthetic vision methods, systems and computer readable media are disclosed. For example, a system can include one or more sensors, a terrain database, and a projected synthetic vision controller coupled to the one or more sensors and the terrain database, the projected synthetic vision controller configured to generate and project synthetic vision images based on aircraft position, terrain information and aviator boresight information. The system can also include one or more projectors coupled to the projected synthetic vision controller.

US Patent:

20150277561, Oct 1, 2015

Filed:

Mar 26, 2014

Appl. No.:

14/225784

Inventors:

- Bethesda MD, US
Steven D. Colby - Owego NY, US

Assignee:

LOCKHEED MARTIN CORPORATION - Bethesda MD

International Classification:

G06F 3/01
B64D 45/00

Abstract:

Combined modality hover drift cueing methods, systems and computer readable media are disclosed. For example, some implementations can include a system comprising one or more sensors, and a combined modality hover drift cueing controller coupled to the one or more sensors and configured to determine hover drift and to control a plurality of indicators in response to determined hover drift. The system can also include a mode selector coupled to the combined modality hover drift cueing controller and configured to provide an indication of mode selection between one of a first mode, a second mode and a third mode, wherein the first mode is a combined modality mode. The system can further include a peripheral vision hover drift indicator coupled to the controller and mounted on an inside surface of an aircraft cockpit, and a tactile feedback indicator coupled to the controller.

US Patent:

20150241221, Aug 27, 2015

Filed:

Feb 24, 2014

Appl. No.:

14/187533

Inventors:

- Bethesda MD, US
Steven D. Colby - Owego NY, US

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

G01C 21/20
G01C 23/00

Abstract:

Projected synthetic vision methods, systems and computer readable media are disclosed. For example, a system can include one or more sensors, a terrain database, and a projected synthetic vision controller coupled to the one or more sensors and the terrain database, the projected synthetic vision controller configured to generate and project synthetic vision images based on aircraft position, terrain information and aviator boresight information. The system can also include one or more projectors coupled to the projected synthetic vision controller.

US Patent:

20150169273, Jun 18, 2015

Filed:

Dec 16, 2013

Appl. No.:

14/107518

Inventors:

- Bethesda MD, US
Steven D. Colby - Owego NY, US

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

G06F 3/14
B63B 49/00
B64D 43/00

Abstract:

Peripheral vision hover drift cueing methods, systems and computer readable media are disclosed. For example, a system can include one or more sensors, and a peripheral vision hover drift cueing controller coupled to the one or more sensors and configured to determine hover drift and to control a plurality of indicators in response to determined hover drift. The system can also include a first hover drift indicator coupled to the controller and mounted on an inside surface of a vehicle cockpit; and a second hover drift indicator coupled to the controller and mounted on an inside surface of the vehicle cockpit.