Horizontal Tailplane Subjected to Impact Loading
The European Union Research Programme CRAHVI (CRashworthiness of Aircraft for High Velocity Impact) is concerned with the high velocity impact of aircraft due to flying objects, e.g. bird, hailstone, tyre and engine debris as well as concerned with survivable crash landings on different surfaces, e.g. rigid inclined surfaces (slopes) and water with different sea states. The simulation is naturaly a complex task due to the high number of variables involved. Such variables include material characteristics of the impacted media, impactors and surfaces at high strain rate, and the interaction between the aircraft structure and the impactors or surfaces. But with the increase of software and hardware computing power, it is now becoming more realistic to predict the behaviour of aircraft structures subjected to high velocity impact scenarios. Within the CRAHVI-Programme finite element models of a clamped horizontal tailplane (HTP) in an airliner are developed, which are subjected to impact loading with different impactor models. The HTP model composed of advanced composite material has been delivered by the University of Limerick [2],[3] whereas the HTP model representing metallic material was provided by the University of Patras [4]. Based on these models, the National Aerospace Laboratory NLR delivered an input file for the impact of a Lagrangian bird model on the HTP [8]. All files have been provided in form of PAM-CRASH input. It was the task of CAD-FEM to transfer those models into LS-DYNA input files, whereby special attention must be paid on a proper translation of the corresponding material models and the automatic generation of spotwelds. In case of the used composite bi-phase material the *MAT_LAMINATED_COMPOSITE_FABRIC model of LS-DYNA [11] is used. Based on those translated input files selective simulations for the composite and metallic structure are performed including bird strike on the leading edge (LE) of the HTP. For the bird strike simulation a Lagrangian as well as an ALE formulation is used. Additionally LS-OPT [10] was used in the Lagrangian bird strike simulation performing a thickness optimization of the LE. The optimization goal for bird strike is shortly speaking a non- rupture of the LE. The current contribution presents simulation results of rigid pole impact on composite HTP model, bird strike within Lagrangian formulation on metallic HTP model and bird strike within ALE formulation on metallic HTP model. Moreover the results are compared with other numerical results available within the CRAHVI-Programme. Additionally optimization results of the LE obtained from LS-OPT in combination with LS-DYNA are shown, which fulfill the desired optimization criterion of a non-ruptured leading edge.
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Horizontal Tailplane Subjected to Impact Loading
The European Union Research Programme CRAHVI (CRashworthiness of Aircraft for High Velocity Impact) is concerned with the high velocity impact of aircraft due to flying objects, e.g. bird, hailstone, tyre and engine debris as well as concerned with survivable crash landings on different surfaces, e.g. rigid inclined surfaces (slopes) and water with different sea states. The simulation is naturaly a complex task due to the high number of variables involved. Such variables include material characteristics of the impacted media, impactors and surfaces at high strain rate, and the interaction between the aircraft structure and the impactors or surfaces. But with the increase of software and hardware computing power, it is now becoming more realistic to predict the behaviour of aircraft structures subjected to high velocity impact scenarios. Within the CRAHVI-Programme finite element models of a clamped horizontal tailplane (HTP) in an airliner are developed, which are subjected to impact loading with different impactor models. The HTP model composed of advanced composite material has been delivered by the University of Limerick [2],[3] whereas the HTP model representing metallic material was provided by the University of Patras [4]. Based on these models, the National Aerospace Laboratory NLR delivered an input file for the impact of a Lagrangian bird model on the HTP [8]. All files have been provided in form of PAM-CRASH input. It was the task of CAD-FEM to transfer those models into LS-DYNA input files, whereby special attention must be paid on a proper translation of the corresponding material models and the automatic generation of spotwelds. In case of the used composite bi-phase material the *MAT_LAMINATED_COMPOSITE_FABRIC model of LS-DYNA [11] is used. Based on those translated input files selective simulations for the composite and metallic structure are performed including bird strike on the leading edge (LE) of the HTP. For the bird strike simulation a Lagrangian as well as an ALE formulation is used. Additionally LS-OPT [10] was used in the Lagrangian bird strike simulation performing a thickness optimization of the LE. The optimization goal for bird strike is shortly speaking a non- rupture of the LE. The current contribution presents simulation results of rigid pole impact on composite HTP model, bird strike within Lagrangian formulation on metallic HTP model and bird strike within ALE formulation on metallic HTP model. Moreover the results are compared with other numerical results available within the CRAHVI-Programme. Additionally optimization results of the LE obtained from LS-OPT in combination with LS-DYNA are shown, which fulfill the desired optimization criterion of a non-ruptured leading edge.
10-3.pdf
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