1,720,972 research outputs found
NeOPT: an Optimization Suite for the Aeroelastic Preliminary Design
Full text linkThe paper describes the new optimization feature of the NeoCASS suite, which allows to size a general wing box structure considering the aeroelastic effects. During the conceptual phase of the design the aircraft is represented by a stick model with steady/unsteady aerodynamics (VLM/DLM), a link between the stiffness and mass matrices of the 1D elements and the 3D world is provided by a meta-model of the wing box. The optimization is performed considering the maneuvers which define the load envelope of the aircraft compliant with CS25 regulation, analytical constraints on failure and buckling of the components are imposed
A Meta-Model for composite wingbox sizing in aircraft conceptual design
Full text linkThis works describes the implementation of a semi-analytical representation of the wingbox structure in the conceptual and preliminary design phases, it manages different analysis and design models with different levels of detail and complexity. Starting from the description of the wing with macro-parameters, e.g. airfoils position, spars location, ribs and stringers pitch, the wing is geometrically identified and divided into its components. By providing the structural and material properties to the components, it is possible to realize different FEM models to be used for different analyses.The introduction of the Meta-Model in conceptual design phases improves the description of the wing, providing more realistic models for the weight estimation procedure through physically based aero-servo-elastic sizing and optimization.This approach initializes the aero-structural Digital Twin of the aircraft, which can be used for the health monitoring and maintenance planning of existing aircraft
Gust Load Passive Alleviation by Means on Nonlinear, Buckling Driven, Structural Response
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Design of an Innovative Wing Tip for Aeroelastic Control: from Scratch to Flight Test
Full text linkThis paper resumes the activities done in the framework of the Clean Sky 2 AIRGREEN2 project, where an Innovative Wing Tip (IWT) device was designed, built, and tested. The IWT is equipped with an actively controlled movable surface for the active load reduction of the gust and maneuver load alleviation (MLA/GLA). The design involved several disciplines like aerodynamics, structure, actuation, sensing and control. Intermediate wind tunnel models and ground demonstrator provided experimental evidence of the reliability of the concept. The aim of this paper is to illustrate the process that led to the manufacturing of the IWT, which will be tested in flight by the end of 2023
Development of an Active Wingtip for Aeroelastic Control
Full text linkThis paper presents the design of an innovative wingtip device actively actuated to control the aeroelastic loads, with a focus on the gust load alleviation. It summarizes the work carried out in the Clean Sky 2 AIRGREEN2 project, where the device was developed from scratch and reached a relevant technology readiness level with the full-scale prototype manufacturing and testing, compulsory to obtain the permit to fly. This paper describes the overall design of the devices, covering the structure, the aero-servo-elasticity characteristics of the whole aircraft, the actuation system design, the scaled wind tunnel testing, and the full-scale structural qualification tests. The paper proves how the development of a new item involves several disciplines simultaneously, remarking on the importance of an integrated approach to the new generation aircraft design
Preliminary Aero-Elastic Optimization of a Twin-Aisle Long-Haul Aircraft with Increased Aspect Ratio
Full text linkThis paper presents a preliminary study on the improvement of the fuel efficiency of a civil transport aircraft, focusing on the aero-elastic optimization of an increased aspect ratio wingbox. The wing is stretched, increasing its aspect ratio, and a trade-off between the improved aerodynamic efficiency and the structural mass identifies an optimal aspect ratio for such aircraft. The aeroelastic optimization is performed with NeOPT, a structural optimizer for conceptual and preliminary design phases. The analysis considers different materials and structural solutions for the wingbox and tackles aeroelastic constraints, such as flutter and aileron efficiency, from the preliminary design phases. The fuel consumption of the sized aircraft is evaluated with a simplified approach that provides an indication of the fuel efficiency. The results show how a composite wing with increased aspect ratio can save up to 6.9% of fuel burnt with respect to the baseline aluminum wing. The results are extended at fleet level, achieving a 2-million-ton cut in CO2 emissions and a saving of USD 1.28 million on fuel-related costs
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