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TITLE OF PAPER
Simulation framework for preliminary structural design of aero engines
Simulation-driven design and process automation are key enablers to speed up engineering design processes and improve the quality of the final design. This paper presents an integrated multi-disciplinary simulation framework developed within Rolls-Royce for preliminary structural design of aero engines. The framework enables the application of robust design at system level and fast cross-functional trade studies on novel engine architectures. The paper demonstrates a more efficient integration of structural and thermal analysis simulation capabilities. A link between CAD geometry and FEA tools is established to drive design via analysis and enable multi-disciplinary design optimisation. The implementation of the framework has been driven by aero engine project needs and priorities, following an agile software development approach.
Risk Mitigation for Unmaned Air Vehicles Mission Planning
Giulio Avanzini, University of Salento | Vito Primavera, EnginSoft SpA | Francesco Micchetti, EnginSoft SpA | Silvano Pagone, Aeroporti di Puglia | Angelo Di Martino, EKA srl | Manuela Marra, University of Salento | Claudio Pascarelli, University of Salento
In recent years the use of Unmanned Air Vehicles (UAVs) rapidly expanded from mainly military and research applications to a very wide range of applications in civil activities. At the same time, UAVs became accessible to a wide range of users. Therefore, determination and mitigation of the risk they can represent to people in the event of a ground impact is a key point for the development of UAV regulations in the civil airspace. The present work, conceived and promoted within the Apulian Aerospace Technological Cluster (DTA) and developed into the co-funded project “TAKE-OFF - Test and Knowledge‐based Environment for Operations, Flight and Facility” (in the “Cluster Tecnologici Regionali - SmartPuglia 2020, Regione Puglia” frame program) introduces a path planning methodology where the risk related to UAV operation is reduced by estimating the probability of hitting a person on the ground, assuming a map of the population density in the area interested by the flight is available. The impact area on the ground is evaluated both in a deterministic way – which depends on vehicle dimensions and kinetic energy – and in a statistical way – where uncertainties of the navigation parameters (position and velocity) are introduced. The impact areas are then related to vehicle failure rate and to a real population density map, resulting in a reliable risk evaluation. Once the relation between the nominal vehicle trajectory and corresponding risk level is defined, a suitable multi-objective optimization process is developed, searching for the optimum solutions that minimize path length and risk, the latter being constrained below a prescribed maximum admissible value. Eventually, the candidate optimum paths are visualized and evaluated within a virtual console, developed and addressed in terms of a cloud architecture. The whole path planning methodology has been built according to recognized authority rules.
Tolerance Analysis Techniques for Flexible Components
Manufacturers spend large amounts of money on product quality issues such as parts not fitting together properly, scrap, and rework. Tolerance variation in rigid body assemblies results from three sources: size, form and kinematics. Tolerance analysis software solutions such as CETOL from Sigmetrix, VisVSA from Siemens PLM and 3DCS from Dassault Systemes are effective for rigid body assemblies and are fully integrated within the major CAD tools such as PTC/CREO, NX and CATIA respectively.
Flexible body assemblies exhibit an additional source of variation, such as the deformation of the components due to assembly forces or temperature loading during manufacturing. Flexible assemblies, composed of slender parts or sheet metal components can deform substantially from their nominal geometric shape.
This paper will present techniques that perform tolerance analysis on assemblies with flexible components within the CAD and CAE environments.
Wind tunnel test matrix design using CFD based DOE
Abdullah Emre Cetiner, Aselsan Inc. | İlteris Koc, Aselsan Inc.
In this study, wind tunnel test matrix of a newly developed Air-to-Ground missile is designed utilizing the Design of Experiment method based on Computational Fluid Dynamics simulations for various combinations of input parameters that are angle of attack, side-slip angle, Mach number, and the tail fin deflections. First of all, contributions of input parameters to each output (aerodynamic forces and moments) and the correlation between the inputs are identified. Then, separate Response Surface Model for each output that span the whole design space is generated to investigate the design deeper. Finally, optimal interval values for each input parameters are determined for the wind tunnel test matrix. As a result, number of runs in the test matrix was significantly reduced.
Design optimization of a main landing gear shock absorber hydraulic system
Francesco Scarano, Magnaghi Aeronautica | Vito Primavera, EnginSoft SpA | Francesco Micchetti, EnginSoft SpA
Aim of this job is the design optimization of a MLG shock absorber hydraulic system in order to guarantee the compliance with the customer performance requirements. The case study, developed through a close cooperation between Magnaghi Aeronautica and EnginSoft, allowed to evaluate positively the capacities of the software modeFRONTIER. The optimized solution is resulted to be very close to the current one obtained after a manual iterative optimization process.
Front electric sustainer for gliders, CFD simulations
Simone Bartesaghi, Wind&Water Consultants
The Front Electric Sustainer (FES) has nowadays numerous installations on single seat gliders.
Most common use is as sustainer, but recently gliders of new FAI 13.50m class can take off with it, enhancing the potentiality of this light glider. The simplicity of use is evident, but the most requiring pilots are aware about the performance decay due to the propeller on glider nose. By using CFD tools, a comparison for bare fuselage and FES device installed is done. For the current study two speeds are investigated: 120 km/h (near at the maximum efficiency) and 180 km/h (usual cross country straight speed), with the cabin ventilation closed. From the investigation, the main conclusion is the FES propeller blades destroy the laminar flow and this causes the drag increase.
Non-conventional configurations for small satellites launchers
Elio De Marinis, EnginSoft SpA | Giulio Avanzini, University of Salento
The topic of the work is to evaluate the energetic cost of non-conventional launch systems dedicated for small satellites. Launch configurations such as ground launch, balloon launch and airborne launch to orbit are considered for different class of satellites and for different orbit altitudes; the analysis is focused on minimizing the booster’s initial mass once set the payload.
When considering a balloon, a trade-off is required in order to evaluate properly the altitude to be reached from the balloon and the mass it has to lift off. For the airborne launcher, there is a tradeoff between carrier aircraft’s flight conditions; operational limits are analyzed and discussed.
Moreover a brief cost analysis is performed in order to evaluate properly pros and cons of each configuration.