The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Mar. 22, 2011

Filed:

Oct. 17, 2005
Applicants:

Jim C. Narramore, Bedford, TX (US);

Stacey Kelly, Argyle, TX (US);

Robert Milliken, North Richland Hills, TX (US);

Inventors:

Jim C. Narramore, Bedford, TX (US);

Stacey Kelly, Argyle, TX (US);

Robert Milliken, North Richland Hills, TX (US);

Assignee:

Textron Innovations Inc., Providence, RI (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
G06F 17/50 (2006.01); G06F 7/48 (2006.01); G09B 9/08 (2006.01);
U.S. Cl.
CPC ...
Abstract

A method for designing a flight vehicle includes determining a preferred aerodynamic shape of a structure of the vehicle; modifying the preferred aerodynamic shape based upon constraints; and determining, using aerodynamic computational fluid dynamics, limit loading conditions for the modified aerodynamic shape. A computer-implemented system for designing a flight vehicle includes at least one computer operable to determine a preferred aerodynamic shape of a structure of the vehicle; modify the preferred aerodynamic shape based upon constraints; and determine, using aerodynamic computational fluid dynamics, limit loading conditions for the modified aerodynamic shape. Software for designing a flight vehicle, embodied in a computer-readable medium, is operable to, when executed, determine a preferred aerodynamic shape of a structure of the vehicle; modify the preferred aerodynamic shape based upon constraints; and determine, using aerodynamic computational fluid dynamics, limit loading conditions for the modified aerodynamic shape.


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