Optimization of air distribution mode coupled interior design for civil aircraft cabin

The airflow distribution and thermal comfort of human beings in civil aircraft cabin are influenced by many factors such as the ventilation mode, ventilation air volume, and supply air temperature and so on. Among these factors, the choice of ventilation mode in the civil aircraft cabin is also restricted by the interior and aesthetic designs.

Multidisciplinary Optimization of Unmanned Aircraft Considering radar signature sensors and trajectory constraints

The optimization problem of the present case study is about improving the radar signature and sensor capabilities of the aircraft while at the same time ensuring that it can perform well in the given mission profile and that it has acceptable flying characteristics.​

Design optimization of a main landing gear shock absorber hydraulic system

The present study describes  the advantages obtained by the usage of the modeFRONTIER software for the design optimization of a Main Landing Gear (MLG) shock absorber hydraulic system to guarantee the compliance with the customer performance requirements. 

Risk Mitigation for Unmanned Air Vehicles Mission Planning

The present work (developed into the co-funded project “TAKE-OFF - Test and Knowledge-based Environment for Operations, Flight and Facility”, whose frame is the “Cluster Tecnologici Regionali - SmartPuglia 2020, Regione Puglia”) 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. 

Crystal Plasticity Modeling and Experimental validation with an orientation distribution function for Ti-7 al alloy

An optimization study is performed to identify the slip system parameters of Ti-Al alloys (Ti-0Al and Ti-7Al) using the available tension and compression experimental data showing the true stress - true strain curves of the alloys.

Knowledge-Based Integrated Aircraft

A multidisciplinary optimization framework connecting the geometric model, aerodynamic model and structural model is performed on a wing shape with predefined loads on the wing. For global optimization, MOGA is used and for local optimization Simplex algorithm is used as the design variables are continuos.

Planform Dependency of Optimum Supersonic Airfoil for Wing-Body-Nacelle Configuration Using Multi-Fidelity Design Optimization

In this paper, supersonic wing design problems for supersonic transport (SST) with integrated engine intake and nacelle was discussed to obtain design knowledge of a supersonic airfoil with respect to wing planform dependency for a realistic configuration. Optimum wing designs were analyzed considering the interference between the engine intake, the nacelle, and the wing for two different planforms using a multi-fidelity design method.

Optimization of High lift device system deployment for takeoff performance

This work presents a proposed framework intended to be used for the optimization of highlift devices, namely Flaps and Slats for the present study. This paper addresses a first phase of a work aimed at a complete tool of high lift devices using modeFRONTIER as the optimizer in the process. The study takes into account the experience of a company inserted in the aeronautical environment and of the databases constituted from old aircraft. 

Development of a Multidisciplinary Design Optimization Framework Applied on UAV Design by Considering Models for Mission, Surveillance, and Stealth Performance

This paper presents a Multidisciplinary Design Optimization (MDO) framework that is intended to be employed in the early design stages of Unmanned Aerial Vehicles (UAVs).  A development approach for modeling the sensor performance and the radar signature is proposed and it is shown that their integration in a framework which also takes into account the geometry, the aerodynamics, the stability, and the mission simulation is feasible.

Aircraft conceptual design of a business jet (category Large) using Multidisciplinary Design Optimization techniques

A Multidisciplinary Design Optimization approach considering closed-loop flight control laws was applied to a conceptual design of a large-cabin business jet.  The optimization algorithm used in this work is the Multi-Objective Genetic Algorithm of second generation (MOGA-II algorithm) using modeFRONTIER. Two types of analysis were done: mono-objective, maximizing the internal rate of return, and multi-objective, maximizing the internal rate of return and minimizing Dubai – London City mission block time.