An investigation into a non-axisymmetric tension shell decelerator concept via a computational design procedure

Vladimyr M. Gidzak, Graham V Candler

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

The possibility of constructing non-axisymmetric tension cones is examined with the goal of creating a tension cone that naturally trims to a non-zero angle of attack. The shape derivation for axisymmetric tension cones is used to map a design space from which an initial shape for a non-axisymmetric tension shell can be constructed. A version of the US3D flow solver with fluid-structure interaction (FSI) capabilities is used as a tool for both design and evaluation. Variations 011 the degree of non-symmetry are compared in terms of aerodynamic and structural performance. It is found that simple modifications to the basic tension cone design can result in an inflatable decelerator that trims to an angle of attack of at least 28°, with an L/D of 0.49, while still maintaining a state of pure tension in the tension shell.

Original languageEnglish (US)
Title of host publication29th AIAA Applied Aerodynamics Conference 2011
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781624101458
DOIs
StatePublished - Dec 1 2011
Event29th AIAA Applied Aerodynamics Conference 2011 - Honolulu, HI, United States
Duration: Jun 27 2011Jun 30 2011

Publication series

Name29th AIAA Applied Aerodynamics Conference 2011

Other

Other29th AIAA Applied Aerodynamics Conference 2011
CountryUnited States
CityHonolulu, HI
Period6/27/116/30/11

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