Argiris Kamoulakos

COMPutational ASsessment Suite

This paper is a follow-up of the paper titled “Aspects of analysis and simulation of a flaperon ditching scenario” presented in the Aviation Forum 2020, which proposed a modified definition of the added-mass in the Von-Karman-wedge water impact theory. It is again inspired by the recovery of the MH370 Boeing 777 right wing flaperon debris and the a...

In the wake of the disappearance of the MH370 Boeing 777 and the recovery of the right wing flaperon debris, a ditching scenario has been envisaged by the investigating authorities. In this respect, this paper attempts to assess the forces exerted by fluid-structure interaction upon a guided-ditching flaperon both through analytical and numerical m...

Many industrial flow applications, e.g. oil churning, require modelling conjugate heat transfer and having suitable boundary conditions at the walls. In order to avoid resolving the temperature gradients in thin boundary layers with SPH, and, consequently, having very high computational costs, a heat flux boundary condition for SPH in interactions...

Over the last few decades, the Smoothed Particle Hydrodynamics (SPH) method has gained popularity as a mesh-less method to simulate fluid flows. In contrast, the finite element (FE) method remains the preferred tool to simulate structural deformation. This paper presents a coupled SPH-FE software tool useful for a large variety of dynamic fluid flo...

Designing structures located either offshore or onshore , able to withstand loads coming from large impacting waves or for entering water poses a major technological challenge. Virtual prototyping using advanced numerical simulation techniques has become an indispensable tool to meet such a challenge. This paper presents an explicit Finite Element...

The 2011 Tōhoku earthquake showed that even the most sophisticated defenses like the massive Kamaishi bay breakwater were insufficient to prevent catastrophic flooding of the coast line. This paper will deal with the Fluid-Structure Interaction (FSI) simulation of a breaking tsunami induced flooding wave upon a coastal infrastructure. It will exami...

An explicit Finite Element (FE) software package with an embedded and fully coupled Smoothed Particle Hydrodynamics (SPH) solver is used to investigate the dynamic response of a floating (moored) offshore platform subject to strong wave action. The water is modelled using SPH while the platform and anchor cables are modelled using FE. The main body...

In response to the current challenges it is facing, the aeronautical industry is re-examining the autoclave process. Here, we present a simulation-based system that provides decision-making support all the way from design to manufacturing of composite autoclave parts.

This paper presents the implementation and validation of a numerical simulation method that takes into account the air-borne acoustic wavepropagation within the turbulent flow solution at low Mach number, which is so-called weak compressibility, in order to cope with fully coupled aero-acoustics problems in a nonlinear system. An academic single 3D...

Certain facts behind metal rupture prediction are exposed together with the classical ways they have been approached in the past. The limitations of these approaches are highlighted as compared to the capabilities of the EWK model. A novel automatic parameter identification capability for the EWK model is exposed. Pre-industrial application example...

The present paper provides an overview of ESI Group's solutions of high speed flow simulations for aeronautics applications. It addresses the compute models and solution methods for aeronautics applications on basic trans/super/hypersonic aircraft aerodynamics with moving body capability for store separation of sub-munitions or canopy separation. A...

Background The EWK Fracture ModelAcademic ValidationSemi-Industrial ValidationConclusions References

In a collaborative research project, aircraft wing leading edge structures with a glass-based Fibre Metal Laminate (FML) skin have been designed, built, and subjected to bird strike tests that have been modelled with finite element analysis. Fibre Metal Laminates have layers of aluminium alloy and high strength glass fibre composite and have been r...

In a collaborative research project, aircraft wing leading edge structures with a glass-based Fibre Metal Laminate (FML) skin have been designed, built, and subjected to bird strike tests that have been modelled with finite element analysis. In this second part of a two-part paper, a finite element model is developed for simulating the bird strike...

Fibre Metal Laminates with layers of aluminium alloy and high strength glass fibre composite have been reported to possess excellent impact properties and be suitable for aircraft parts likely to be subjected to impacts from objects such as runway debris or birds. In a collaborative research project, aircraft wing leading edge structures with a gla...

Fibre Metal Laminates with layers of aluminium alloy and high strength glass fibre composite have been reported to possess excellent impact properties and be suitable for aircraft parts likely to be subjected to impacts such as runway debris or bird strikes. In a collaborative research project, aircraft wing leading edge structures with a glass-bas...

In a collaborative research project, aircraft wing leading edge structures with a glass-based Fibre Metal Laminate (FML) skin have been designed, built, and subjected to bird strike tests that have been modelled with finite element analysis. In this second part of a two-part paper, a finite element model is developed for simulating the bird strike...

In a collaborative research project, aircraft wing leading edge structures with a glass-based Fibre Metal Laminate (FML) skin have been designed, built, and subjected to bird strike tests that have been modelled with finite element analysis. Fibre Metal Laminates have layers of aluminium alloy and high strength glass fibre composite and have been r...

The use of high performance materials such as high strength steel grades, aluminium and magnesium alloys has raised the difficulty to accurately predict structural crash behaviour: these materials are generally more prone to rupture than mild steel, and predicting rupture is still very difficult to achieve. In this paper certain facts behind metal...

This paper describes recent results of water impact simulations using the Smoothed Hydrodynamic Method (SPH) available in the explicit finite element code PAM-CRASH. In a first part, the principles, on which the SPH method is based, namely the kernel and the particle approximations, are discussed. Secondly, the strategy followed for the next simula...

Composite energy-absorbing structures for use in aircraft are being studied within a European Commission research programme (CRASURV – Design for Crash Survivability). One of the aims of the project is to evaluate the current capabilities of crashworthiness simulation codes for composites modelling. This paper focuses on the computational analysis...

The problems in dealing with the initial transient responses and dynamic failure of explosively loaded aircraft fuselage panels are discussed. The specific aspects of finite element technology for fluid/structure interaction relevant to this problem are addressed as applied to the PAMSHOCK-PAMFLOW coupling. Two application examples from the U.S. Ai...

Published in : Proceedings.Computational Mechanics. New Trends and Applications. E. Onate and S.R. Idelsohn ( Eds.) Barcelona, 1998

The capability of PAM-SHOCK, for studying the transient dynamic responses of a rolling tire impacting a road imperfection ("bump") is presented. An industrial test case, that is, a tire rolling on a spinning drum that contains a cleat, was simulated using PAM-SHOCK. The simulation includes pressurization of the tire, loading the tire against the dr...

The Attitude Control System (ACS) of the future European heavy launcher Ariane 5 is a Hydrazine system including two bladder tanks pressurised by Nitrogen ; depending on the mission, a residual pressure of some 10 to 20 bars may still remain at the end of the mission. In order to avoid any debris generation, the explosion threshold pressure has bee...

In this paper the problem of space debris impact has been approached numerically using the Finite Element (FE) method and the method of Smoothed Particle Hydrodynamics (SPH) through the use of the transient explicit code PAM-SHOCK. Three distinct cases of impacts upon Whipple shields were analyzed, namely a 6.6 km/s speed normal impact, a 11.1 km/s...

In this paper the process of virtual design of space debris shields has been touched with emphasis being given to the virtual prototyping stage of the above process as performed by the PAM-SHOCK family of codes. A selection of numerical results is presented to underline the feasibility of simulating by computer the extreme space environment hyperve...

The problems in dealing with the initial transient responses and dynamic failure of explosively loaded aircraft fuselage panels are discussed. The specific aspects of finite element technology for fluid / structure interaction relevant to this problem are addressed as applied to the PAMSHOCK - PAMFLOW coupling. Two application examples from the U.S...

The history of the problem of inextensional bending of thin shells is briefly introduced. A comparison between Novoshilov's and Sander's shell theories is performed and it is shown that, for a catenoid of revolution, both theories will yield identical results. The problem of inextensional bending is then defined and discussed, with the catenoid of...

The reason for looking in some depth at locking of Mindlin shell elements is introduced. A simple example of straight beam locking is examined in detail. The observations about reduced integration that emerge are subsequently unified with some other facts the writer has come across. A simple curved beam element is then formulated and examined under...

Static vibration and flutter analysis of a straight elastic axis blade was performed based on a finite element method solution. The total potential energy functional was formulated according to linear beam theory. The inertia and aerodynamic loads were formulated according to the blade absolute acceleration and absolute velocity vectors. In vibrati...