Vincent T Padden

US Patent:

8544361, Oct 1, 2013

Filed:

Sep 6, 2011

Appl. No.:

13/225982

Inventors:

Vincent Padden - Stuart FL, US

Assignee:

Blair HSM Composites LLC - Medford NY

International Classification:

F16C 7/00
F16C 7/02

US Classification:

74579R, 74579 E

Abstract:

A link fitting having bearing supports, an inner core and an outer band surrounding it all. Each bearing support includes a first stepped portion, a separate second stepped portion and a recess disposed between the first and second stepped portions. The inner core includes a central elongate layer, a first outer layer and a second outer layer. The first and second outer layers are disposed on opposed first and second sides of the central layer. The first outer layer engages the first side of the central layer and a portion of the first stepped portion on each of the two bearing supports. The second outer layer engaging the second side of the central layer and a portion of the second stepped portion on each of the two bearing supports. Opposed first and second ends of the central layer disposed within the recesses of each of the two bearing supports.

US Patent:

20100047613, Feb 25, 2010

Filed:

Aug 19, 2009

Appl. No.:

12/583360

Inventors:

Vincent T. Padden - Stuart FL, US

Assignee:

Air Industries Group, Inc. - Bay Shore NY

International Classification:

B32B 3/00
B32B 15/00
B32B 38/00

US Classification:

428614, 428189, 156263

Abstract:

A composite brace, strut, or link for any application requiring the transfer of a concentrated load uses a stepped insert at the lug end to distribute the applied loads into a composite structure formed of a stacked arrangement of internal and external plies of composite material. The manufacture of the brace, strut, or link is performed in a cost effective manner. The composite lay-up is done so that many individual parts can be cut from the initial multi-part assembly, allowing the economy of scale to lower fabrication costs of the individual manufactured parts. The structure provides a system whereby the concentrated load applied at the stepped inserts can be distributed into the composite material without any gapping or separation as would occur in a traditionally configured end fitting joint between a circular metallic bushing and the adjacent composite material interface.

US Patent:

20140014256, Jan 16, 2014

Filed:

Sep 17, 2013

Appl. No.:

14/028650

Inventors:

Vincent PADDEN - Stuart FL, US

Assignee:

Blair HSM Composites LLC - Medford NY

International Classification:

B32B 37/12
B32B 37/14

US Classification:

156 91, 156192, 156185

Abstract:

A method of forming a composite link fitting including joining two opposed bearing supports with an inner laminate core having a longitudinal axis extending there between. Each bearing support including a bearing bore formed as an aperture, a first stepped portion, a separate second stepped portion and a recess formed therein. The recess extending toward the bearing bore between an extent of the first and second stepped portions to a recess bottom. The inner laminate core including a central elongate layer, a first outer layer and a second outer layer, with the first and second outer layers disposed on opposed first and second sides of the central elongate layer. First and second ends of the central elongate layer disposed within respective recesses. Also, the method including wrapping an outer band around the two bearing supports and the inner laminate core to form the composite link fitting.

US Patent:

53908783, Feb 21, 1995

Filed:

Feb 9, 1993

Appl. No.:

8/015122

Inventors:

Vincent T. Padden - Brightwaters NY

Assignee:

Grumman Aerospace Corporation - Long Island NY

International Classification:

B64D 2700

US Classification:

244 53R

Abstract:

An isolator assembly for use in minimizing mechanical thermal and/or vibrationary strains between two structures is disclosed. The isolator assebly generally includes two spaced base members which are interconnected by a plurality of equally spaced rods. The length, diameter and material of the rods are determined based on the particular environment within which the isolator assembly is utilized. The invention has particular application in supporting a hot air blower tube within a cowling of a jet engine unit.

US Patent:

55002722, Mar 19, 1996

Filed:

Jan 11, 1995

Appl. No.:

8/371432

Inventors:

Vincent T. Padden - Brightwaters NY

Assignee:

Northrop Grumman Corporation - Los Angeles CA

International Classification:

B32B 324

US Classification:

428140

Abstract:

Thin perforated sheets of titanium are interleaved between adjacently situated graphite/epoxy plies--in the area where metal fittings are to be installed. Epoxy flows through these perforations so as to achieve a gripping mechanism between the titanium sheet and the graphite/epoxy plies. The result is efficient transfer of load in the titanium to the composite fiber materials without suffering the cost penalty of extensive graphite/epoxy buildups (without interleaved titanium sheets). Epoxy plugs within the titanium sheet perforations bond to confronting surfaces of the graphite/epoxy plies and provide a fail safe gripping mechanism between the titanium sheet and adjacent graphite/epoxy plies to allow for the load transfer between the titanium sheet and the graphite/epoxy plies in the unlikely event that the shear bond between the faces of the titanium sheet and the graphite/epoxy plies becomes completely disbonded.

US Patent:

52246701, Jul 6, 1993

Filed:

Sep 13, 1991

Appl. No.:

7/759231

Inventors:

Vincent T. Padden - Brightwaters NY

Assignee:

Grumman Aerospace Corporation - Bethpage NY

International Classification:

B64C 126

US Classification:

244123

Abstract:

A graphite epoxy spoiler for an aircraft wing is manufactured by estimating the shear force to which the spoiler will be subject, and forming a fitting attachment surface and fitting designed to eliminate a separate shear attachment between the spoiler structure and the center attachment/drive fitting. This permits use of a one piece co-cured honeycomb sandwich construction for the spoiler.