Search

Josef A Fila

from Pryor, OK
Age ~69
Get Report
Also known as:
Josef Antonin Fila, Josef R Fila, Joseph A Ila
Related to:
Mark Jones, 42Robert Jones, 78Allison C Sinclair, 35Courtney Pierson, 37
Connected to:
Adam Fila, 50Amy E Fila, 48Corey J Fila, 56David L Fila, 72Emily A Fila, 33Kathleen Fila, 72Richard L Fila, 74Robert S Fila, 79Michael J Filachek, 63Timothy M Filafusi, 63

Josef Fila Phones & Addresses

  • Pryor, OK
  • 833 Jarman Dr, Jamestown, NC 27282 (912) 920-3511
  • Higganum, CT
  • Haddam, CT
  • 139 Mariners Ct, Savannah, GA 31419 (912) 920-3511
  • Euless, TX
  • Saginaw, TX
  • Arlington, TX

Resumes

Resumes

Josef Fila Photo 1

Greensboro And Winston-Salem, North Carolina Area

View page
Location:
4070 east 496, Pryor, OK 74361
Industry:
Aviation & Aerospace
Work:

Greensboro and Winston-Salem, North Carolina Area
Skills:
Stress Analysis
Finite Element Analysis
Msc.patran
Composites
Metal Fabrication
Aircraft
Nastran
Machine Tools
Aerospace
Analysis
Aircraft Design
Catia
Manufacturing
Flight Test
Helicopters
Abaqus
Aerospace Engineering
Composite Structures
Six Sigma
Matrixone
Structural Analysis
Lean Manufacturing
Aerodynamics
Pro Engineer
Design Engineering
Avionics
Aviation
Fatigue Analysis
Solidworks
Airworthiness
Gd&T
Engineering Management
Aeronautics
Program Management
Systems Engineering
Fortran
Femap
Engineering
Mechanical Engineering
Mathcad
Fracture Mechanics
Manufacturing Engineering
Aircraft Maintenance
Damage Tolerance
Josef Fila Photo 2

Josef Fila

View page
Josef Fila Photo 3

Josef Fila

View page

Publications

Us Patents

Thermal-Acoustic Sections For An Aircraft

View page
US Patent:
8413762, Apr 9, 2013
Filed:
Dec 8, 2011
Appl. No.:
13/314954
Inventors:
Tongan Wang - Garden City GA, US
Andrew Foose - Savannah GA, US
David Charles Hornick - Midway GA, US
Josef Fila - Jamestown NC, US
Assignee:
Gulfstream Aerospace Corporation - Savannah GA
International Classification:
E04B 1/82
E04B 1/84
H02N 2/00
B32B 3/12
US Classification:
181292, 181290, 181294, 310327, 310334, 310335, 428116
Abstract:
Embodiments of thermal-acoustic sections for an aircraft for reducing noise along an acoustic path produced from an acoustic source are provided herein. The thermal-acoustic section comprises a first porous layer having a first characteristic acoustic impedance. A second porous layer is disposed adjacent to the first porous layer and has a second characteristic acoustic impedance that is greater than the first characteristic acoustic impedance. The thermal-acoustic section is configured to be positioned along the acoustic path such that at least a portion of the noise from the acoustic source is directed through the first porous layer to the second porous layer to promote absorption of the noise.

Vibration Isolation System Using Electrical Cables As Mass

View page
US Patent:
8534594, Sep 17, 2013
Filed:
Apr 11, 2011
Appl. No.:
13/084200
Inventors:
Tongan Wang - Garden City GA, US
David C. Hornick - Midway GA, US
Andrew S. Foose - Savannah GA, US
Josef A. Fila - Savannah GA, US
Assignee:
Gulfstream Aerospace Corporation - Savannah GA
International Classification:
B64C 1/40
B64C 1/00
F16M 11/00
US Classification:
244 1N, 244119, 2441291, 248560
Abstract:
A vibration isolation system for attenuating vibration energy between two aircraft structures, such as between the aircraft's fuselage and interior cabin. The vibration isolation system includes a first isolator attached to the first structure, a second isolator attached to the second structure, and an intermediate mass attached between the first and second isolators. The intermediate mass may be electrical cables, wiring bundles, a cable holder, or other component disposed between the two structures. Cable holder intermediate masses can be fabricated from an electrically conductive material to provide electromagnetic interference shielding for cables disposed therein. Multiple vibration isolation systems can be disposed between the fuselage and interior cabin to provide a less noisy cabin. Additional noise and vibration suppressors, such as skin damping material and acoustic blankets, also can be disposed between the fuselage and interior cabin to further reduce noise in the interior cabin.

Flat-Cured Composite Structure

View page
US Patent:
20100043955, Feb 25, 2010
Filed:
Aug 19, 2009
Appl. No.:
12/544055
Inventors:
David C. Hornick - Midway GA, US
Josef Fila - Savannah GA, US
International Classification:
B32B 37/00
B29C 65/00
B32B 3/02
B32B 3/12
B32B 17/02
D04H 13/00
US Classification:
156182, 1563071, 156285, 428 69, 428116, 4282934, 428178, 4282921, 442203
Abstract:
An embodiment of the invention includes a composite structure fabricated from at least one pre-cured flat face sheet applied to a core with an adhesive. Once the pre-cured flat face sheet is applied to the core, curing of the adhesive may take place to bond the pre-cured flat face sheet to the core. Before the bonding of the pre-cured flat face sheet to the core takes place, the pre-cured flat face sheet may be prepared by separately curing a composite face sheet.

Thermal-Acoustic Sections For An Aircraft

View page
US Patent:
20130206504, Aug 15, 2013
Filed:
Mar 12, 2013
Appl. No.:
13/797127
Inventors:
GULFSTREAM AEROSPACE CORPORATION - , US
John Maxon - Richmond Hill GA, US
Andrew Foose - Savannah GA, US
David Charles Hornick - Midway GA, US
Josef Fila - Jamestown NC, US
Assignee:
GULFSTREAM AEROSPACE CORPORATION - Savannah GA
International Classification:
B64C 1/40
US Classification:
181292
Abstract:
Embodiments of thermal-acoustic sections for an aircraft for reducing noise along an acoustic path produced from an acoustic source are provided herein. The thermal-acoustic section comprises a first porous layer having a first characteristic acoustic impedance. A second porous layer is disposed adjacent to the first porous layer and has a second characteristic acoustic impedance that is greater than the first characteristic acoustic impedance. The thermal-acoustic section is configured to be positioned along the acoustic path such that at least a portion of the noise from the acoustic source is directed through the first porous layer to the second porous layer to promote absorption of the noise.

Thermal-Acoustic Sections For An Aircraft

View page
US Patent:
20140216845, Aug 7, 2014
Filed:
Dec 4, 2013
Appl. No.:
14/096833
Inventors:
- SAVANNAH GA, US
John Maxon - Richmond Hill GA, US
Andrew Foose - Savannah GA, US
David Charles Hornick - Midway GA, US
Josef Fila - Jamestown NC, US
Assignee:
GULFSTREAM AEROSPACE CORPORATION - SAVANNAH GA
International Classification:
B64C 1/40
US Classification:
181292
Abstract:
Embodiments of thermal-acoustic sections for an aircraft for reducing noise along an acoustic path produced from an acoustic source are provided herein. The thermal-acoustic section comprises a first porous layer having a first characteristic acoustic impedance. A second porous layer is disposed adjacent to the first porous layer and has a second characteristic acoustic impedance that is greater than the first characteristic acoustic impedance. The thermal-acoustic section is configured to be positioned along the acoustic path such that at least a portion of the noise from the acoustic source is directed through the first porous layer to the second porous layer to promote absorption of the noise.
Control profile
Josef A Fila from Pryor, OK, age ~69 Get Report