The presented paper's goal is to give a brief overview of recent numerical and experimental developments performed for ten years by the ONERA/DMSE/RCS, aiming at improving structures conception with respect to crashworthiness, ditching, impact or explosion hardening considerations. One of ONERA Research goals is to improve the material characteristics and,...
The proposed paper presents hard landing simulations of large aeronautical structures using explicit F.E. codes, such as RADIOSS. The main technical difficulties arise from the dimensions and the complexity of the structures to model on the one hand, and from the complexity of the very local ruin phenomena on the...
This paper aim at developing methodologies to design crashworthy composite commercial aircraft fuselages, a 2 frames section based on the A321 AIRBUS standard dimensions was manufactured by AIRBUS France, in order to be crash-tested at the Toulouse Aeronautical Test Centre. Though most p re-test numerical analyses confirmed this expected rupture...
Uncertainty effects on the stability of fluid-structure coupled systems have been investigated at ONERA for more than a decade. This paper focuses on stability of the coupled system aircraft /aerodynamics which is a key issue in civil airplane manufacturing. During the design stage of an airplane, many structural parameters are...
Drag reduction is one of the main objectives of the transport aircraft manufacturers. This is why researches devoted to the development of new technologies aiming at drag reduction were initiated. The drag breakdown of a transport aircraft at cruise shows that the skin friction drag and the lift-induced drag constitute...
At the beginning of 2000, ONERA launched an internal project aimed at investigating a few aerodynamic problems linked to the future supersonic aircraft. Five topics are studied: laminar-turbulent transition and laminar flow control; development of a "quiet" supersonic wind tunnel; turbulent flows at high values of Reynolds number; shock wave/boundary...
In aerospace engineering, interception problems are often dealt with by separating guidance and autopilot design. Guidance law can be obtained using optimal control theory and autopilot design is performered on a linearised system. This paper introduces a new approach that determines a global guidance and autopilot law, based on direct...
The paper provides an overview of the tools which are currently available for delaying the onset of transition. Distinction is made between techniques which modify the mean flow field and techniques acting on the unstable wave's birth and development, without any action on the mean flow field. Applications of the...
In this paper, an Automatic Lightning System Detection and Recording ALISDAR have been developed. The characterization of the lightning strike to an aircraft is done by electrical and magnetic field measurements. A prototype of ALISDAR sensors have been installed on metallic dummy windows. The system was in operation during an...
The purpose of this paper is to investigate the very near field zone of a circular surface with different aperture illuminations. In this zone, which is an unusual part of the near field zone, the radiated fields, the wave impedance and the power density present a specific behavior. It developed...
Future aerospace applications require materials with ever increasing temperature and load-bearing capabilities. Continuous SiC fiber-reinforced titanium metal matrix composites TMCs exhibit the potential for meeting these requirements and are particularly attractive for use in aircraft gas turbine engines owing to their specific mechanical properties at high temperature. Changing conventional titanium...
In this paper major results and findings of the numerical work package of the high lift programme EUROLIFT are outlined. The main objective of these studies is to validate and test numerical methods for the prediction of high lift flows for transport aircraft configurations. The activities comprise the assessment of...
Predicting the aeroelasticity stability of aircraft requires computing the unsteady generalized aeroelastic forces on the structural modal base of the aircraft. Introducing the viscous effects is a decisive step for representing the shocks correctly, notably as concerns their amplitudes and positions. In this paper Linearization of the discretized Reynolds Average...
This paper presents the experimental developments implemented by ONERA, dealing with some specific measurements for the wind milling post Fan Blade Out purpose, related to the new certification items of the Airbus A340-500 and performed during the Ground Vibration Test. Part of the success factor of operating modern large civil...
In transonic flow, the shock wave / turbulent boundary layer interaction and flow separations on wing upper surface of a civil aircraft, which induce "buffet", and then structure vibrations, "buffeting", can greatly influence the aerodynamic behavior. The objectives of this study are to decrease the aerodynamic instabilities by control systems,...
During the lightning strike to an aircraft in flight, the lightning channel gets deformed in the aerodynamic flow and displaced along the aircraft, a so-called swept stroke. To be able to correctly determine the different levels of hazards on an aircraft zoning, the physical behavior of the lightning swept stroke...
During lightning strikes to aircraft in flight, the lightning channel gets deformed in the airflow and displace along the aircraft, a so-called wept stroke. In this paper a model of the thermodynamic evolution of lightning channels during their continuous current phase is developed and numerically solved. In this model, the...
More and more, inhabitants in the vicinity of airports and air force bases complain about aircraft annoyance. Therefore noise reduction becomes a major issue in aeronautics. A possible way of reduction to investigate is to develop acoustic liners which are directly introduced into aircraft engines; this has already be tried...
This paper describes a new step in the development of a Computational AeroAcoustics CAA process whose general long term objective is the numerical prediction of the aerodynamic sound radiated by the airframe of large aircraft at approach, and especially the noise generated by deployed high lift devices such as slats...
This paper presents the application of the CANARI flow solver to the computation of unsteady effects in the aerodynamic interaction of a high speed propeller with the aircraft. The method is first validated on the APIAN isolated propeller test case by comparison with experiment at M=0.7. The method is then...
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