Patent ID: 9330208
Filing Date: 2016-05-03
CPC Classification: G06F,Y02T

Claim Text:
1. A method comprising: identifying data using a processor in communication with a non-transitory computer readable storage medium, the data including data for a plurality of points in an area of a surface of an aircraft or a spacecraft, wherein the data is generated by a computer simulation of a flow of fluid over the surface; identifying, using the processor, a number of sub-areas of the area, each of the number of sub-areas comprising less than all of the area, each of the number of sub-areas centered on corresponding identified node points, wherein the node points are identified based on an aerodynamic heating analysis and wherein identifying the number of sub-areas comprises, for each node point, establishing boundaries for a given sub-area by halfway distances to a next adjacent node point in each X-direction and each Y-direction, or by an edge of the area; responsive to identifying the number of sub-areas, determining by the processor a sub-set of the plurality of points corresponding to each of the number of sub-areas; determining by the processor a corresponding value for each of the number of sub-areas using the data for the sub-set of points corresponding to each of the number of sub-areas, wherein the corresponding value is an average of the data for the sub-set of points corresponding to each of the number of sub-areas, wherein the corresponding value is a corresponding computational fluid dynamics value; performing the aerodynamic heating analysis of the number of sub-areas using each corresponding computational fluid dynamics value; and effecting a repair of a part having the surface based on the aerodynamic heating analysis.