Space--Time Computation of a Ringsail Parachute With Model Thickness

The Team for Advanced Flow Simulation and Modeling specializes in computational analysis of geometrically complex parachutes. In earlier computations, the parachutes modeled by our team did not include the fabric thickness in the fluid domain, as doing so would require a large number of elements, which is computationally costly. However, by resolving the thickness, we expect to represent the boundary layer separation better. Thanks to the Space–Time Slip Interface (ST-SI) method and recent advances in the ST-Isogeometric Analysis (ST-IGA), we can greatly reduce the number of elements. The ST-SI method, at an interface between two mesh zones, removes the matching requirement between the meshes on the two sides of the interface without losing solution accuracy. Recent advances in the ST-IGA allow the use of knot removal to reduce the number of control points, thus converting NURBS to a T-spline representation. This study begins with, for a single gore of an Orion spacecraft parachute, a flow comparison between the models with and without fabric thickness. It concludes with, for the full-canopy Orion spacecraft parachute, flow computation with the ST-SI, ST-IGA, and T-splines.

Name thesis:degree_name

Master of Science

Level thesis:degree_level

Masters

Discipline thesis:degree_discipline

Engineering

Grantor

Rice University

Year dc:date.issued

2021

Author dc:creator

• Barrios, Dino

Advisor dc:contributor.advisor

• Tezduyar, Tayfun E.

• CFD
• Space-Time
• NURBS
• T-spline

Statement dc:rights

• Copyright is held by the author, unless otherwise indicated. Permission to reuse, publish, or reproduce the work beyond the bounds of fair use or other exemptions to copyright law must be obtained from the copyright holder.

Language dc:language.iso

eng

Handle dc:identifier.uri

https://hdl.handle.net/1911/111767

OAI identifier oai:identifier

oai:repository.rice.edu:1911/111767