A validated computational fluid-structure interaction method applied to supersonic parachute inflation is extended to consider a unique, parallel self-contact algorithm, porosity interface conditions on the canopy, improved flow field sampling procedures for obtaining quality loading on the parachute canopy, adaptive mesh refinement, and improved treatment of thin geometries in an immersed boundary framework. These extensions are discussed in detail and demonstrated individually on test problems. Finally, the developments are brought together for demonstration on a sub-scale MSL parachute geometry.
|Title of host publication||AIAA Scitech 2020 Forum|
|Number of pages||25|
|State||Published - 2020|
|Event||AIAA Scitech Forum, 2020 - Orlando, United States|
Duration: Jan 6 2020 → Jan 10 2020
|Name||AIAA Scitech 2020 Forum|
|Conference||AIAA Scitech Forum, 2020|
|Period||1/6/20 → 1/10/20|
Bibliographical noteFunding Information:
This work is partially supported by NASA ARMD’s Transformational Tools and Technologies (T3) project. Gokul Anugrah and Professor Brehm greatly acknowledge funding from the NASA Ames Computational Aerosciences Branch under contract 80NSSC18K0883. Computing resources are provided by NASA Advanced Supercomputing systems.
© 2020 American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
ASJC Scopus subject areas
- Aerospace Engineering