Janet E Davis

US Patent:

6716407, Apr 6, 2004

Filed:

Jun 18, 2001

Appl. No.:

09/883760

Inventors:

Janet B. Davis - Thousand Oaks CA
David B. Marshall - Thousand Oaks CA
Peter Ernest David Morgan - Thousand Oaks CA
Kris Shigeko Oka - West Covina CA

Assignee:

The Boeing Company - Chicago IL

International Classification:

C01F 1700

US Classification:

423305, 1062861, 1062862, 1062865, 1062866, 1062868, 10628717, 10628718, 10628719, 423306, 501126

Abstract:

Monazite or xenotime-based blanket coatings that stiffen ceramic fabrics without causing embrittlement at temperatures of at least as high as 2400Â F. are provided. Methods for making the coatings are also provided. The methods comprise the synthesis of high purity, monazite and xenotime powders with the stoichiometric ratio of metal to phosphorous of about 1:1.

US Patent:

7281688, Oct 16, 2007

Filed:

Apr 27, 2006

Appl. No.:

11/380450

Inventors:

Brian Nelson Cox - Thousand Oaks CA, US
Janet B. Davis - Thousand Oaks CA, US
Julia Mack - Encino CA, US
David Bruce Marshall - Thousand Oaks CA, US
Peter E. Morgan - Thousand Oaks CA, US
Olivier H. Sudre - Thousand Oaks CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64G 1/58

US Classification:

2441591, 2441717

Abstract:

A self-transpiring hot skin for a hypersonic or reusable space vehicle that can provide protection to the vehicle during short periods of abnormally high heat flux (either planned in the flight profile or an off-nominal event). The hot skin includes a ceramic composite structure having an internal cavity that is coupled either to the insulating layer or directly to the support structure of the hypersonic vehicle. The internal cavity includes a material system that vaporizes, sublimes or decomposes into a gas when the temperature exceeds the upper temperature capability of the composite material. The gas transpires through the outer layer of the composite material to provide cooling to the outer layer below the upper temperature capability. Cooling may occur both by conduction of heat from the composite material to the transpiring gas and by the interaction of the transpiring gas with the boundary layer of hypersonic flow over the outer surface, leading to a reduction of the heat flux entering the surface.

US Patent:

7516918, Apr 14, 2009

Filed:

May 11, 2006

Appl. No.:

11/432865

Inventors:

Brian N. Cox - Thousand Oaks CA, US
Janet B. Davis - Thousand Oaks CA, US
Sergio Luis dos Santos e Lucato - Thousand Oaks CA, US
David B. Marshall - Thousand Oaks CA, US
Brock S. McCabe - Malibu CA, US
Olivier H. Sudre - Thousand Oaks CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64D 29/00
B64C 9/02
B32B 5/08

US Classification:

244 53R, 244 53 B, 244133, 244 38, 4282934

Abstract:

An exemplary morphable ceramic composite structure includes a flexible ceramic composite skin and a truss structure attached to the skin. The truss structure can morph shape of the skin from a first shape to a second shape that is different than the first shape. The flexible ceramic composite skin may include a single-layer of three-dimensional woven fabric fibers and a ceramic matrix composite. The truss structure may include at least one actuatable element or an actuator may move a portion of the truss structure from a first position to a second position. A cooling component may be disposed in thermal communication with the skin. The cooling component may include thermal insulation or a cooling system that circulates cooling fluid in thermal communication with the skin. The morphable ceramic composite structure may be incorporated into any of an air inlet, combustor, exhaust nozzle, or control surfaces of a hypersonic aircraft.

US Patent:

7823529, Nov 2, 2010

Filed:

May 23, 2006

Appl. No.:

11/438387

Inventors:

Julia J. Mack - Encino CA, US
Janet B. Davis - Thousand Oaks CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B05C 13/00

US Classification:

118 63, 118 52, 118423

Abstract:

To produce a ceramic foam-filled structural sandwich panel, a coating of a pre-ceramic slurry is applied on a preform. The preform includes a foam template sandwiched between a plurality of panels. In addition, the coating is cured to the preform, the preform is modified, and the coating is converted to a ceramic.

US Patent:

8017213, Sep 13, 2011

Filed:

Apr 21, 2006

Appl. No.:

11/379677

Inventors:

Olivier H. Sudre - Thousand Oaks CA, US
Janet B. Davis - Thousand Oaks CA, US
Stanley A. Lawton - Clayton MD, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B32B 3/06

US Classification:

428100, 428 97, 2952502

Abstract:

A temperature tolerant hook and loop attachment, a method of forming a sheet of the hooks and, a method of insulating the skin of a flight vehicle. Temporary loops are formed in a fabric containing temperature tolerant fiber tows, e. g. , the tows may be carbon, a metal, a carbide such as carbon silicide, a nitride, or an oxide. The temporary loops are stiffened (e. g. , with resin, metal or ceramic), and severed to form temperature tolerant fiber composite hooks. The sheet may be cut and permanently applied, for example, to the skin of a spacecraft or aircraft. A fibrous material, e. g. , fibrous insulation or batting, may be pressed in place or formed into the hooks, or the fibrous material may be attached to another structure and pressed in place for a temperature tolerant hook and loop attachment.

US Patent:

8309197, Nov 13, 2012

Filed:

Dec 17, 2008

Appl. No.:

12/316991

Inventors:

Janet Davis - Thousand Oaks CA, US
David Marshall - Thousand Oaks CA, US
Olivier Sudre - Thousand Oaks CA, US

Assignee:

Teledyne Scientific & Imaging, LLC - Thousand Oaks CA

International Classification:

B32B 7/02
F01D 11/08

US Classification:

428 86, 428 92, 428 95, 428 96, 4283099, 4283122, 4151744

Abstract:

Devices, systems and methods for fabricating improved ceramic composite turbine shrouds with abradable seals are disclosed. A high temperature seal with an abradable coating is provided. The seal comprises a three-dimensional, high-density woven composite base structure recessed below the abradable coating, with loops incorporated in and protruding from the base structure. The abradable coating is integrally attached to the base structure via the loops. Additionally, a graded density seal is provided with a three-dimensional, low-density woven composite structure. The low-density structure is abradable. A three-dimensional, high-density woven composite base structure is recessed below the low-density structure, with the low-density structure integrally attached to the base structure via weaving.

US Patent:

8556589, Oct 15, 2013

Filed:

Dec 30, 2009

Appl. No.:

12/650172

Inventors:

Janet B Davis - Thousand Oaks CA, US
David B Marshall - Thousand Oaks CA, US
Olivier H Sudre - Thousand Oaks CA, US
Sergio dos Santos e Lucato - Thousand Oaks CA, US

Assignee:

Teledyne Scientific & Imaging, LLC - Thousand Oaks CA

International Classification:

B64C 11/00

US Classification:

416224, 416230, 416241 B

Abstract:

A protective hybrid composite for a rotor blade is based on the use of tape cast ceramic layers densified by pre-ceramic polymer infiltration methods and laminated together with polymer matrix composite prepregs, with or without an embedded metallic mesh, to form a conforming helicopter blade cladding that is laminated to the blade surface for added erosion protection. The hybrid composite is fabricated to net shape and laminated to the blade using either an adhesive or a polymer composite prepreg inner layer. Installation is accomplished by a standard composite fabrication method of vacuum bagging the blade while the system is laminated to its surface. Repair methods based on removal of ceramic tiles is facilitated by incorporation of a metallic mesh element laminated beneath the ceramic tiles that can be used to heat the tile and decrease its adhesion strength.

US Patent:

20040110440, Jun 10, 2004

Filed:

Nov 19, 2003

Appl. No.:

10/717351

Inventors:

Janet Davis - Thousand Oaks CA, US
David Marshall - Thousand Oaks CA, US
Peter Ernest Morgan - Thousand Oaks CA, US
Kris Oka - West Covina CA, US

International Classification:

B32B018/00
B32B011/00
C09K003/00

US Classification:

442/178000, 106/287180, 106/287170, 501/095200, 501/088000, 501/103000, 501/111000, 501/126000, 501/127000, 442/004000, 442/051000

Abstract:

Monazite or xenotime-based blanket coatings that stiffen ceramic fabrics without causing embrittlement at temperatures of at least as high as 2400 F. are provided. Methods for making the coatings are also provided. The methods comprise the synthesis of high purity, monazite and xenotime powders with the stoichiometric ratio of metal to phosphorous of about 1:1.