Italian Aerospace Research Centre

About: Italian Aerospace Research Centre is a other organization based out in Capua, Campania, Italy. It is known for research contribution in the topics: Aerodynamics & Morphing. The organization has 278 authors who have published 400 publications receiving 3563 citations. The organization is also known as: CIRA & Italian Aerospace Research Center.

Illegal Micro-Dumps Monitoring: Pollution Sources and Targets Detection in Satellite Images with the Scattering Transform

Abstract: The identification of contaminated sites is a key application in remote sensing. Major challenges are typically related to the difficulties in the spectral characterization of the targets. The detection performance can be improved by exploiting a suitable spatial description of the scene. In this work, the use of spatial features based on the Scattering Transform for detection of micro-dumps and greenhouses is proposed. These features are jointly exploited with spectral ones to improve the classification accuracy within a multi -class classifier. The obtained results show the relevance of spatial features in the detection of the targets of interest.

Water impact tests and simulations of a steel structure

Abstract: Purpose – The purpose of this paper is to improve knowledge of the water impact phenomenon from both the experimental and numerical points of view.Design/methodology/approach – A drop test campaign on water was carried out on semi‐cylindrical steel structures. Therefore, an experimental database for validation purpose was generated. Subsequently, a finite element model was developed in LS‐DYNA in order to reproduce the tests. The behaviour of water was modeled by using the smoothed particle hydrodynamics (SPH) methods. Numerical simulations were compared to experimental data and the influence of some numerical parameters on the simulations was investigated.Findings – The FE model was found to be able to reproduce the tests, at least in terms of acceleration peak and distribution of plastic deformation. Acceptable prediction was also found for the pressure peak in soft areas.Research limitations/implications – In case of low velocity impact, the water model was found to be too rigid and the acceleration pe...

Preliminary Assessment of Morphing Winglet and Flap Tabs Influence on the Aeroelastic Stability of Next Generation Regional Aircraft

Abstract: Future aircraft wing technology is rapidly moving toward flexible and morphing wing concepts capable to enhance aircraft wing performance in off-design conditions and to reduce operative maneuver and gust loads. However, due to the reduced stiffness, increased mass, and increased degree of freedom (DOF), such mechanical systems require advanced aeroelastic assessments since the early design phases; this appears crucial to properly drive the design of the underlying mechanisms since the conceptual phase by mitigating their impact on the whole aircraft aeroelastic stability. Preliminary investigations have shown that the combined use of adaptive flap tabs and morphing winglets significantly improves aircraft aerodynamic performance in climb and cruise conditions by the order of 6%. Additionally, by adapting span-wise lift distributions to reduce gust solicitations and alleviate wing root bending moment at critical flight conditions, significant weight savings can also be achieved. Within the scope of Clean Sky 2 Airgreen 2 project, flutter and divergence characteristics of a morphing wing design integrating adaptive winglets and flap tabs are discussed. Multi-parametric flutter analyses are carried out in compliance with CS-25 airworthiness requirements (paragraph 25.629, parts (a), (b), (c) and (d)) to investigate static and dynamic aeroelastic stability behavior of the aircraft. The proposed kinematic systems are characterized by movable surfaces, each with its own domain authority, sustained by a structural skeleton and completely integrated with EMA-based actuation systems. For that purpose, a sensitivity analysis was performed taking into account variations of the stiffness and inertial properties of the referred architectures. Such layouts were reduced to a stick-equivalent model which properties were evaluated through MSC-NASTRAN-based computations. The proprietary code SANDY 4.0 was used to generate the aero-structural model and to solve the aeroelastic stability equations by means of theoretical modes association in frequency domain. Analyses showed the presence of critical modal coupling mechanisms in nominal operative conditions as well as in case of system malfunctioning or failure. Design solutions to assure clearance from instabilities were then investigated. Trade-off flutter and divergence analyses were finally carried out to assess the robustness of the morphing architectures in terms of movable parts layout, mass balancing and actuators damping.

A CFD Method for Simulation of Mixing and Combustion in High-Pressure LOx Methane Rocket Engines

Abstract: The industrial and scientific communities are devoting major research efforts to identify and assess critical technologies for new advanced propulsive concepts: combustion at high pressure, as well as the replacement of hydrogen with a hydrocarbon, has been assumed as a key issue to achieve better propulsive performances and lower environmental impact and to reduce the costs related to ground operations (propellant handling infrastructure and procedures) and increase flexibility. Starting from this background, the present work describes a CFD analysis (based on the numerical solution of RANS equations for chemically reacting flows) performed to evaluate the effects of different thermo-chemical modeling assumptions on the performances of a high-pressure LOx/CH4 rocket thrust chamber.