Martin J Gomez

US Patent:

8172172, May 8, 2012

Filed:

Nov 18, 2011

Appl. No.:

13/299924

Inventors:

Martin L. Gomez - Fairfax VA, US
Robert Parks - San Jose CA, US
Adam J. Woodworth - Melrose MA, US

Assignee:

Aurora Flight Sciences Corporation - Manassas VA

International Classification:

B64C 37/02
B64C 23/06

US Classification:

244 2, 2441993, 244 3, 244 1 TD

Abstract:

A system and method for docking various types of aircraft is disclosed. An aerodynamic lifting structure docking mechanism for docking two or more aircraft is provided comprising an aerodynamic lifting structure. The aerodynamic lifting structure includes a first and second airflow adjustment mechanism. The aerodynamic lifting structure further includes a first hard docking mechanism, and a second hard docking mechanism, and still further includes a soft docking mechanism. The first and second airflow adjustment mechanisms are configured to substantially remove any aerodynamic lifting structure vortices around each of the aerodynamic lifting structure tip areas. The soft docking mechanism is configured to soft dock a first aerodynamic lifting structure with a second aerodynamic lifting structure. The first hard docking mechanism is configured to hard dock with the second hard docking mechanism, thereby temporarily attaching the first aerodynamic lifting structure with the second aerodynamic lifting structure.

US Patent:

8226025, Jul 24, 2012

Filed:

Nov 18, 2011

Appl. No.:

13/299883

Inventors:

Martin L. Gomez - Fairfax VA, US
Robert Parks - San Jose CA, US
Adam J. Woodworth - Melrose MA, US

Assignee:

Aurora Flight Sciences Corporation - Manassas VA

International Classification:

B64C 37/02
B64C 23/06
B64D 5/00

US Classification:

244 2, 244 3, 2441992, 2441993, 244 1 TD

Abstract:

A system and method for docking various types of aircraft is disclosed. An aerodynamic lifting structure docking mechanism for docking two or more aircraft is provided comprising an aerodynamic lifting structure. The aerodynamic lifting structure includes a first and second airflow adjustment mechanism. The aerodynamic lifting structure further includes a first hard docking mechanism, and a second hard docking mechanism, and still further includes a soft docking mechanism. The first and second airflow adjustment mechanisms are configured to substantially remove any aerodynamic lifting structure vortices around each of the aerodynamic lifting structure tip areas. The soft docking mechanism is configured to soft dock a first aerodynamic lifting structure with a second aerodynamic lifting structure. The first hard docking mechanism is configured to hard dock with the second hard docking mechanism, thereby temporarily attaching the first aerodynamic lifting structure with the second aerodynamic lifting structure.

US Patent:

20090127376, May 21, 2009

Filed:

Sep 15, 2008

Appl. No.:

12/210711

Inventors:

Martin L. Gomez - Fairfax VA, US
Robert Parks - San Jose CA, US
Adam J. Woodworth - Melrose MA, US

International Classification:

B64C 37/02

US Classification:

244 2

Abstract:

A system and method for docking various types of aircraft is disclosed. An aerodynamic lifting structure docking mechanism for docking two or more aircraft is provided comprising an aerodynamic lifting structure. The aerodynamic lifting structure includes a first and second airflow adjustment mechanism. The aerodynamic lifting structure further includes a first hard docking mechanism, and a second hard docking mechanism, and still further includes a soft docking mechanism. The first and second airflow adjustment mechanisms are configured to substantially remove any aerodynamic lifting structure vortices around each of the aerodynamic lifting structure tip areas. The soft docking mechanism is configured to soft dock a first aerodynamic lifting structure with a second aerodynamic lifting structure. The first hard docking mechanism is configured to hard dock with the second hard docking mechanism, thereby temporarily attaching the first aerodynamic lifting structure with the second aerodynamic lifting structure.

US Patent:

20130085629, Apr 4, 2013

Filed:

Oct 1, 2012

Appl. No.:

13/632849

Inventors:

Aurora Flight Sciences Corporation - Manassas VA, US
Thorsten Hisam - Manassas VA, US
Martin Gomez - Manassas VA, US

Assignee:

Aurora Flight Sciences Corporation - Manassas VA

International Classification:

G06F 17/00

US Classification:

701 15

Abstract:

The present disclosure endeavors to provide systems, methods and apparatus for ensuring aircraft compliance with governmental guidelines, such as, for example, MRCR Category II compliance. A hardware-based system may be employed to reduce range and/or payload below predetermined ranges and a payload capacities. Also provided herein are hardware-based systems, methods, and apparatus for restricting a system's range to predetermined range and/or the payload to a predetermined limit using, for example, a Application-Specific Integrated Circuit (ASIC) installed in the flight control system.

US Patent:

20170203839, Jul 20, 2017

Filed:

Jan 11, 2017

Appl. No.:

15/403818

Inventors:

- Manassas VA, US
Martin Gomez - Fairfax VA, US
Dan Cottrell - Manassas VA, US
Jean-Charles Lede - Oakton VA, US
Tom Roberts - Bristow VA, US
Dorian Colas - Seattle WA, US
Brian Whipple - Manassas VA, US
Tim Nuhfer - Sterling VA, US
Herb Hunter - Herndon VA, US
Jonathan Grohs - Manassas VA, US
Steve Petullo - Bristow VA, US

International Classification:

B64C 29/00
B64D 27/24
B64D 29/02
B64C 39/12

Abstract:

A hybrid propulsion aircraft is described having a distributed electric propulsion system. The distributed electric propulsion system includes a turbo shaft engine that drives one or more generators through a gearbox. The generator provides AC power to a plurality of ducted fans (each being driven by an electric motor). The ducted fans may be integrated with the hybrid propulsion aircraft's wings. The wings can be pivotally attached to the fuselage, thereby allowing for vertical take-off and landing. The design of the hybrid propulsion aircraft mitigates undesirable transient behavior traditionally encountered during a transition from vertical flight to horizontal flight. Moreover, the hybrid propulsion aircraft offers a fast, constant-altitude transition, without requiring a climb or dive to transition. It also offers increased efficiency in both hover and forward flight versus other VTOL aircraft and a higher forward max speed than traditional rotorcraft.