Fluid-structure interaction simulations of the ASPIRE SR01 supersonic parachute flight test

Boustani, Jonathan; Cadieux, Francois; Kenway, Gaetan K.; Barad, Michael F.; Kiris, Cetin C.; Brehm, Christoph

doi:10.1016/j.ast.2022.107596

Cited by 15 publications

(2 citation statements)

References 18 publications

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“…On the other hand, the sharp-interface IB method represents the fluid-structure interface as a sharp boundary, which offers more accurate tracking and representation of well-defined interfaces. Boustani et al [14,15] developed a high-fidelity FSI solver based on the sharp-interface IB method and the finite element method to simulate the supersonic parachute inflation phase of the ASPIRE SR01 flight test. Nevertheless, application of the IB method to parachute inflation is still rare compared to the ALE and DSD/SST methods.…”

Section: Introductionmentioning

confidence: 99%

Extension of a sharp-interface immersed-boundary method for simulating parachute inflation

Zhang,

Pu,

Jia

et al. 2024

Adv. Aerodyn.

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In this work, the sharp-interface immersed boundary (IB) method proposed by Mittal et al. (J Comput Phys 227(10):4825–4852, 2008) is extended to fluid-structure-interaction (FSI) simulation of parachute inflation by utilizing several open-source tools. The method employs a Cartesian-grid ghost-cell methodology to accurately represent the immersed boundary, and it is suitable for solving moving-boundary flows with arbitrarily complex geometries. The finite-element code CalculiX is employed to solve the structural dynamics of the parachute system. The IB flow solver is coupled with CalculiX in a minimally-invasive manner using the multi-physics coupling library preCICE. The implicit fluid-structure coupling together with the Aitken adaptive under-relaxation scheme is considered to improve the numerical accuracy and stability. The developed approach is validated by a benchmark FSI case. Numerical experiments on the inflation process of several typical parachutes are further conducted. The breathing process, flow structure, canopy displacement and drag coefficient are analyzed to demonstrate the applicability of the present approach for simulating parachute inflation.

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Section: Introductionmentioning

confidence: 99%

Extension of a sharp-interface immersed-boundary method for simulating parachute inflation

Zhang,

Pu,

Jia

et al. 2024

Adv. Aerodyn.

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show abstract

“…To date, relatively little research has been performed regarding stress analyses of MLI components, but other fluid-structure interaction (FSI) calculation methods adopted under similar working conditions were used as references when conducting this research. Boustani et al [22] simulated the descent process of the ASPIRE SR01 supersonic parachute using an FSI model. Yang et al [23] also solved for the flow process of a flexible buffer liquid inside a solid rocket motor using an FSI model.…”

Section: Introductionmentioning

confidence: 99%

Stress Characteristics and Structural Optimization of Spacecraft Multilayer Insulation Components

Sun

Liu

et al. 2023

Aerospace

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Multilayer insulation (MLI) components are important parts of spacecraft, in which thin films are the core elements. The film thicknesses are generally small, between 10 and 30 μm, to reduce the weight of the spacecraft. During the launch of a spacecraft, there is a rapid drop in the internal pressure, which causes the internal gas to flow out rapidly through the component. The resulting fluid force may cause film damage and failure, thereby directly affecting the normal operation of the spacecraft. Therefore, the mechanical characteristics of the thin films under rapid decompression conditions were investigated during this study. Considering the effects of the flow field stress distributions on the films during the rapid decompression, a fluid–structure interaction (FSI) model for a component was first constructed. The results show that the stress is largest in the outlet film, which is the part of the overall structure most vulnerable to failure. Furthermore, the effects of the structural parameters of the component on the stresses in the different film layers were analyzed using the orthogonal experimental method. The results show that the film thickness had the largest influence, followed by the film hole diameter, the number of component layers, and finally the staggered hole distance. Finally, a structurally optimized design scheme for the component is proposed based on a parameter range analysis with respect to the maximum film stress. After optimization, the maximum stress of the thin film decreased by 97.6%. This research has practical engineering value for the structural design and optimization of MLI components.

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Influence of Mechanical Properties on the Dynamic Air Permeability of Woven Fabrics

Sun

et al. 2023

Fibers Polym

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Fluid-structure interaction simulations of the ASPIRE SR01 supersonic parachute flight test

Cited by 15 publications

References 18 publications

Extension of a sharp-interface immersed-boundary method for simulating parachute inflation

Extension of a sharp-interface immersed-boundary method for simulating parachute inflation

Stress Characteristics and Structural Optimization of Spacecraft Multilayer Insulation Components

Influence of Mechanical Properties on the Dynamic Air Permeability of Woven Fabrics

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