Michael Lowell Maxwell
Land Surveyors at Shoreline Dr, Long Beach, CA

2008010, May 8, 2008

Apr 30, 2007

11/790999

Michael K. Maxwell - Long Beach CA, US
Richard J. Gardiner - Murray UT, US

B32B 3/14

156382

A system for manufacturing a molded composite structure is disclosed. In one embodiment, the system includes a first preparing component configured to prepare a material stack, wherein the material stack comprises a core section having first and second opposing sides, and wherein the first preparing component further comprises: a first applying component configured to apply first and second substantially fibrous support layers on the first side and second opposing side of the core section wherein the substantially fibrous support layers provide a vacuum path for evacuation of the core section; a second applying component configured to apply an adhesive layer on the first and second support layers and on any other surface of the core not covered by the first and second support layers; and a third applying component configured to apply a thermoplastic barrier layer on the adhesive layers covering all surfaces of the core; a second preparing component configured to prepare a resin; a third preparing component configured to prepare a mold; a placing component configured to place the material stack in the mold; an evacuating component configured to evacuate air from the core section of the material stack through the vacuum path provided by the substantially fibrous support layers; a sealing component configured to seal the evacuated core section, wherein the sealing component further comprises a first curing component configured to cure the adhesive layer to adhere the support layers and thermoplastic barrier layer to the core sections such that after sealing, the thermoplastic barrier layer prevents air from entering the core section, thereby forming an evacuated material stack; an infusing component configured to infuse the mold and the evacuated material stack with the resin to form the structure; a second curing component configured to cure the structure; and a removing component configured to remove the structure from the mold.

2013018, Jul 18, 2013

Jul 11, 2012

13/546388

ANDREAS KIENZLE - Mottingen Balgheim, DE
ROBERTA HINES - LONG BEACH CA, US
MICHAEL MAXWELL - LONG BEACH CA, US

SGL CARBON SE - WIESBADEN

F41H 5/04, F41H 5/02

89 3602, 264 296

A device and process of forming a defensive, ceramic based, applique armor for covering and protecting a substrate which may be exposed to attack by projectiles, the applique armor having a flat or curved armor plate formed of ceramic material and having a first surface and a second surface; wherein the ceramic material being formed of silicon carbide with carbon fibers (C/SiC) and the ceramic material has a plurality of holes on at least one of the surfaces; the holes having a diameter smaller than an anticipated bullet or ammunition projectile and the holes being set obliquely relative to at least one surface, whereby the device and process provide holes formed by press molding, boring, drilling, or combinations thereof.

2008000, Jan 10, 2008

Dec 4, 2006

11/607854

Kazuhiko Mochida - Rancho Palos Verdes CA, US
Curtis Longo - Alta Loma CA, US
Garrick Talavera - Rolling Hills Estates CA, US
Takao Tate - Shizuoka, JP
Michael Maxwell - Long Beach CA, US

B64D 35/00, F16F 15/00, F16H 37/06

244060000, 267136000, 477034000, 07466500A

A power train for a vehicle may include at least two power sources configured to supply power for propelling the vehicle. Each of the power sources may include a power source output shaft. The power train may further include a transmission including at least two transmission inputs operably coupled to the at least two power source output shafts, and a single transmission output shaft configured to supply power to a propulsion member. The power train may also include a controller configured to control operation of the at least two power sources, and the controller may include a full-authority digital electronic controller (FADEC).

7226559, Jun 5, 2007

Dec 4, 2001

10/000148

Michael K. Maxwell - Long Beach CA, US
Richard J. Gardiner - Murray UT, US

Toyota Motor Sales, U.S.A., Inc. - Torrance CA

B29C 70/48, B32B 3/12

264511, 264257, 264258, 264259, 264263, 264313, 264314, 264317, 264324, 264571, 156245, 156286, 1563071, 1563077

A method for molding composite structures whereby a material stack including a core having first and second opposing sides is prepared. The preparing of the material stack includes applying a fibrous support layer on at least one of the first side and the second side of the core section, applying an adhesive layer on the support layer, and applying a thermoplastic barrier layer on the adhesive layer. The method also includes preparing a resin and a mold; placing the material stack in the mold; sealing the core; infusing the mold and material stack with resin; curing the structure; and removing the structure from the mold. In one embodiment, the method creates a composite aircraft wing panel.

2010014, Jun 10, 2010

Apr 30, 2007

11/790998

Michael K. Maxwell - Long Beach CA, US
Richard J. Gardiner - Murray UT, US

B64C 3/20, B64C 3/00, B64C 3/18, B64D 37/02, B64D 37/04, B64D 47/00

2441231

A composite wing panel is disclosed. In one embodiment, a wing panel for an aircraft includes an external skin having a substantially smooth laminar surface, the external skin including multiple layers of a cured material; a sealed core material located within the external skin, the core material having first and second side opposing sides and having been substantially evacuated of air; and a support element disposed within the external skin, the external skin and support element being co-bonded or co-cured together.

2007020, Sep 6, 2007

Apr 30, 2007

11/790997

Michael Maxwell - Long Beach CA, US
Richard Gardiner - Murray UT, US

B32B 9/04, B29C 65/00

428414000, 156285000, 428411100, 428413000, 428421000, 428473500

A molded composite structure and a method of manufacturing a molded composite structure are disclosed. In one embodiment, an aircraft wing panel and a method for manufacturing an aircraft wing panel are disclosed. In another embodiment, the method of manufacturing a molded composite structure uses a resin transfer molding process.