Separation dynamics of large-scale fairing section: a fluid–structure interaction study

Abstract

The separation dynamics of a large-scale fairing section in ground test is investigated numerically using a fluid-structure interaction method. The commercial finite element software MSC/Dytran is adopted to establish the dynamic fluidstructure coupling model of the fairing. Two coupling surfaces are constructed for the inner and outer surfaces of the fairing section. The coupling equations are solved using the sequenced-coupling method, in which the fluid and structural problems are examined by the finite volume method and the finite element method, respectively. A comparison between fluid-structure interaction and dynamical response analysis is performed under the conditions with and without atmosphere effect. Results shown that the consideration of atmosphere effect will attenuate the vibration frequency and slow down the center of mass velocity. The effect of aerodynamic interference on the displacement response indicates that a maximum of 13.3% relative displacement can be induced, which may cause collision between the lower trailing portion of fairing section and the core vehicle. Therefore, it can be concluded that the fluid-structure interaction analysis is essential for evaluating and validating the reliability of separation mechanisms in ground tests.

Calculation of Rocket Nose Fairing Shells Aerodynamic Characteristics

“…1). Анализ литературы [2][3][4] показал, что аэродинамика тонкостенных тел мало изучена. Аэродинамические характеристики этих конструкций можно получить, во-первых, эксперимен-тально, во-вторых, с использованием инженерных методик, а также при помощи численного моделирования.…”

A Brief Introduction to the Bird Strike Numerical Simulation

“…Several works can be found in literature dealing with bird strike events and showing the effects on the most critical structural components, which can experience this phenomenon: The windshield (Plassard et al, 2015;Lu et al, 2015;Ugrcic et al, 2015) and the leading edge (Sun et al, 2010;Guida et al, 2008;Smojver and Ivancevic, 2010;Wang and Yue, 2010;Hanssen et al, 2006;Airoldi and Cacchione, 2006;Johnson and Cook, 1983;1985;Johnson and Cook, 1985;Liu et al, 2013a;Liu and Sun, 2014;Lavoie et al, 2007a;Liu et al, 2013b;Jain and Ramachandra, 2003;Guida et al, 2011).…”

“…Since impact experimental tests, representative of bird strike events, can be very costly and time consuming, it becomes mandatory to develop numerical Finite Element Models able to predict the high velocity impact phenomena on the aircraft structure (Guida et al, 2008;Smojver and Ivančević, 2010;Wang and Yue, 2010). In the frame of the numerical simulations, several interacting aspects have to be considered, such as damage initiation and accumulation (Johnson and Cook, 1983;1985;Xue and Wierzbicki, 2009;Liu et al, 2013a;Liu and Sun, 2014), contact behavior (Johnson and Cook, 1983;1985) and bird modelling approaches (Lavoie et al, 2007a;Liu et al, 2013b;Jain and Ramachandra, 2003;Guida et al, 2011;Liu et al, 2008).…”