Advanced passive safety systems for aircraft: a numerical simulation of parachute inflation

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F00216305%3A26210%2F26%3A0199232" target="_blank" >RIV/00216305:26210/26:0199232 - isvavai.cz</a>

Výsledek na webu

<a href="https://doi.org/10.1108/AEAT-12-2024-0370" target="_blank" >https://doi.org/10.1108/AEAT-12-2024-0370</a>

DOI - Digital Object Identifier

<a href="http://dx.doi.org/10.1108/AEAT-12-2024-0370" target="_blank" >10.1108/AEAT-12-2024-0370</a>

Jazyk výsledku

angličtina

Název v původním jazyce

Advanced passive safety systems for aircraft: a numerical simulation of parachute inflation

Popis výsledku v původním jazyce

Purpose - The rapid expansion of urban air mobility demands advanced passive safety systems specifically designed for vertical take-off and landing (VTOL) aircraft. Traditional parachute recovery systems, effective for fixed-wing aircraft, face significant challenges when adapted to a VTOL due to their unique flight dynamics. This study aims to establish methods for analyzing parachute aerodynamic properties and inflation behavior, providing critical insights to optimize parachute recovery systems for VTOL aircraft and enhance their safety and reliability. Design/methodology/approach - This paper uses fluid-structure interaction (FSI) simulations using ANSYS LS-DYNA with an incompressible computational fluid dynamics (ICFD) solver and an implicit structural solver in a two-way strong coupling. A detailed infinite mass analysis workflow predicts parachute inflation under constant descent velocities. Canopy and suspension lines are modeled with realistic material properties to accurately simulate dynamic interactions and deployment behavior. Findings - This paper demonstrated that the use of LS-DYNA FSI analysis can accurately predict parachute inflation from semi-inflated geometry. The geometry used for simulation was based on a parachute prototype developed at the Aerospace Institute, BUT FME. The simulation results showed a strong agreement with experimental testing, particularly in terms of the drag coefficient and inflated shape. Originality/value - This paper verifies the capabilities and accuracy of FSI analysis using LS-DYNA ICFD solver for parachute inflation.

Název v anglickém jazyce

Advanced passive safety systems for aircraft: a numerical simulation of parachute inflation

Popis výsledku anglicky

Purpose - The rapid expansion of urban air mobility demands advanced passive safety systems specifically designed for vertical take-off and landing (VTOL) aircraft. Traditional parachute recovery systems, effective for fixed-wing aircraft, face significant challenges when adapted to a VTOL due to their unique flight dynamics. This study aims to establish methods for analyzing parachute aerodynamic properties and inflation behavior, providing critical insights to optimize parachute recovery systems for VTOL aircraft and enhance their safety and reliability. Design/methodology/approach - This paper uses fluid-structure interaction (FSI) simulations using ANSYS LS-DYNA with an incompressible computational fluid dynamics (ICFD) solver and an implicit structural solver in a two-way strong coupling. A detailed infinite mass analysis workflow predicts parachute inflation under constant descent velocities. Canopy and suspension lines are modeled with realistic material properties to accurately simulate dynamic interactions and deployment behavior. Findings - This paper demonstrated that the use of LS-DYNA FSI analysis can accurately predict parachute inflation from semi-inflated geometry. The geometry used for simulation was based on a parachute prototype developed at the Aerospace Institute, BUT FME. The simulation results showed a strong agreement with experimental testing, particularly in terms of the drag coefficient and inflated shape. Originality/value - This paper verifies the capabilities and accuracy of FSI analysis using LS-DYNA ICFD solver for parachute inflation.

Druh

J_imp - Článek v periodiku v databázi Web of Science

CEP obor

—

OECD FORD obor

20304 - Aerospace engineering

Projekt

—

Návaznosti

S - Specificky vyzkum na vysokych skolach

Rok uplatnění

2025

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů

Název periodika

Aircraft Engineering and Aerospace Technology

ISSN

1748-8842

e-ISSN

1758-4213

Svazek periodika

97

Číslo periodika v rámci svazku

9

Stát vydavatele periodika

GB - Spojené království Velké Británie a Severního Irska

Počet stran výsledku

12

Strana od-do

1095-1106

Kód UT WoS článku

001575402600001

EID výsledku v databázi Scopus

2-s2.0-105016853450