Scott Owen Peck

US Patent:

20020102384, Aug 1, 2002

Filed:

Jan 29, 2001

Appl. No.:

09/771766

Inventors:

Scott Peck - Palo Alto CA, US
W. Bonneville - Cupertino CA, US
John Cooney - Mountain View CA, US

International Classification:

B32B003/20

US Classification:

428/116000

Abstract:

An embedded heat pipe sandwich panel having components made using dissimilar materials is described. An exemplary embedded heat pipe sandwich panel comprises graphite faceskins secured to aluminum honeycomb core using traditional film adhesives. One or more aluminum heat pipes are embedded in the sandwich panel and thermally coupled to the faceskins using a high thermal conductivity gasket material disposed between the panel faceskins and the heat pipes.

US Patent:

20030082315, May 1, 2003

Filed:

Oct 31, 2001

Appl. No.:

10/001492

Inventors:

Mitchell Mehlman - Pleasanton CA, US
Scott Peck - Palo Alto CA, US

International Classification:

B32B003/12

US Classification:

428/016000

Abstract:

A dimensionally stable honeycomb core and sandwich structure for use in spacecraft applications. The sandwich structure comprises inner and outer faceskins that sandwiches the dimensionally stable honeycomb core. The honeycomb core comprises a fiber and polymer laminate, oriented at a predetermined optimized angle relative to a ribbon direction of the core. Fiber is selected based on strength, modulus and thermal expansion coefficient properties. The polymer is selected based on inherent adhesive properties, coefficient of thermal expansion, moisture absorption, outgassing and its ability to perform in a space environment. The volumetric fraction of fiber and resin and the fiber angular orientation is determined based on the desired system performance, which includes achieving the lowest coefficient of thermal expansion in the plane of the sandwich (ribbon and anti ribbon), as well as through the thickness (z direction). Demanding applications may use ultra-high thermal conductivity fibers where the unidirectional thermal conductivity (K) is greater than 400 W-M/C to minimize the temperature gradients hence achieving a more uniform temperature distribution and lower distortion over the temperature range of interest.

US Patent:

20060029807, Feb 9, 2006

Filed:

Aug 4, 2004

Appl. No.:

10/911466

Inventors:

Scott Peck - Palo Alto CA, US

International Classification:

B32B 5/12

US Classification:

428411100

Abstract:

The fundamental premise of designing structures with laminated composite materials is that the materials can be tailored to meet requirements by choosing the materials, thicknesses or thickness fractions, and orientation angles of constituent materials. Minimum weight, dimensional stability, natural frequency, and thermal conductivity are typical goals. This invention is NOT about the analysis of laminated materials and composites, of which there is no short supply. This invention is about the design of laminated materials, which has traditionally been an iterative event between the designer and the analysis tool. These iterations, if they occur at all, are often the most time consuming aspect of design. The fundamental premise of this invention is that tensor invariants of constituent material properties coupled with a tensor description of the specified material requirements can be used together to design laminated materials. The results of this invention can be used as a stand-alone design tool or as a value-added module in finite element codes. Specifically, by specifying material requirements, designers will use the method to select from a catalog of available materials a set that will satisfy their requirements. The designer is aided in the choice of materials, how much of each material to use, the layup angle orientation of the materials, and the sequencing of those materials in the composite laminate.

US Patent:

61374547, Oct 24, 2000

Filed:

Sep 8, 1999

Appl. No.:

9/392081

Inventors:

Scott O. Peck - Palo Alto CA

Assignee:

Space Systems/Loral, Inc. - Palo Alto CA

International Classification:

H01Q 1520

US Classification:

343912

Abstract:

An unfurlable reflector antenna system having one or more unfurlable arms that are each shaped in the form of a parabolic right cylinder when it is unfurled. Each arm comprises an RF reflecting membrane or a thin shell as the reflector structure. Each arm is coupled by way of a line feed to a receiver. The system is specifically designed for use on a spacecraft. Each arm may be stowed by flattening the parabolic membrane or shell, and then rolling up the arm, which is accomplished without stretching. The sparse reflector antenna array system is thus stowable in a compact configuration, yet easily unfurls to provide a very large diameter lightweight reflector.

US Patent:

6311769, Nov 6, 2001

Filed:

Nov 8, 1999

Appl. No.:

9/435664

Inventors:

W. Scott Bonneville - Cupertino CA
John E. Cooney - Mountain View CA
Scott O. Peck - Palo Alto CA

Assignee:

Space Systems/Loral, Inc. - Palo Alto CA

International Classification:

H05K 720

US Classification:

165185

Abstract:

Thermal interface materials for use in space applications. The thermal interface materials comprise a plurality of graphitized thermally conductive (carbon based) fibers 6 that are contained, immersed, or embedded, in one or more substantially non-outgassing polymer matrix materials. Both relatively stiff and relatively stiff and compliant polymer matrix materials may be used to secure the thermally conductive fibers. The thermally conductive fibers and non-outgassing polymer matrix material may be additionally cured to improve their conductive properties. The polymer matrix materials contain volatile condensable material of less than 0. 1 percent and exhibit a total mass loss of less than 1. 0 percent per an ASTM E595 procedure.

US Patent:

60084480, Dec 28, 1999

Filed:

Oct 15, 1998

Appl. No.:

9/173019

Inventors:

Scott Owen Peck - Palo Alto CA

Assignee:

Space Systems/Loral, Inc. - Paco Alto CA

International Classification:

H01L 2500

US Classification:

136245

Abstract:

A series of solar panels are assembled into an array for use as a source of solar power for a satellite. The panels are designed with diminishing thickness from the yoke to the tip to obtain a constant stress distribution.

US Patent:

60812443, Jun 27, 2000

Filed:

Dec 14, 1998

Appl. No.:

9/210967

Inventors:

Scott Owen Peck - Palo Alto CA

Assignee:

Space Systems/Loral, Inc. - Palo Alto CA

International Classification:

H01Q 1520

US Classification:

343915

Abstract:

An antenna reflector comprising a single membrane antenna reflector surface and means for supporting said antenna reflector surface are disclosed wherein a shape of said antenna reflector is reconfigured to assume a stowed position. The shape of the stowed reflector allowing a large, single piece antenna reflector to be stowed efficiently inside a minimum payload area of the space vehicle. The method and apparatus of this invention ensure that both the deployed and stowed surfaces of the membrane antenna reflector are isometric, or length preserving, mappings of one another. The circumferential dimension of the antenna reflector is decreased having the effect of rolling up the paraboloid so that its surface is similar to a cone. Additionally, the method and apparatus are employed such that when the antenna reflector surface is deployed the antenna reflector membrane unrolls without stretching.

US Patent:

20190178505, Jun 13, 2019

Filed:

Dec 13, 2017

Appl. No.:

15/841071

Inventors:

- Denver CO, US
Scott K. Peck - Superior CO, US

Assignee:

RK Mechanical, Inc. - Denver CO

International Classification:

F24F 1/00
F24F 1/04
F24F 1/26
F24F 11/84
F24F 11/85

Abstract:

The present disclosure involves a free cooling temperature conditioning system having an air handling assembly having a first cooling coil. The first cooling coil includes an intake port receiving coolant at a first temperature and further includes an output port for the coolant at a second temperature. The air handing assembly receives return air flow from a space being temperature conditioned, where the return air flows over the first cooling coil to condition the return air to supply air. The air handing assembly delivers the supply air into the space being temperature conditioned. The conditioning system also includes a controller configured to maintain a temperature difference between the second temperature and the first temperature.