Improve aircraft fuel efficiency, structural performance, aerodynamics and many other aspects of aircraft design with ESTECO technology, used by major organizations such as Embraer, Leonardo, Gulfstream, EADS and ONERA.
Today’s aerospace and defense industry faces many challenges. Due to the projected growth of air traffic, commercial airplane manufacturers see a strong need to minimize fuel consumption, emissions and noise, in order to satisfy consumer and regulatory constraints.
Since these requirements typically lead to conflicting design objectives across several domains, employing Multidisciplinary Design Optimization (MDO) in the design process is crucial. Military airplane manufacturers on the other hand have an entire different set of challenges to solve, mostly involving aircraft performance, power and thermal management requirements and energy efficiency.
The aerospace industry has traditionally often used conservative design methods with a siloed approach between different disciplines. To meet future challenges however, more innovative technologies are needed, and collaboration will be key, not just among different design departments, but also between OEM and suppliers. ESTECO’s technology is designed to do just that.
Applications of ESTECO technology
in the aerospace industries
modeFRONTIER is used by major companies and institutes in aerospace, such as Embraer, Gulfstream, EADS, and ONERA. Engineers in the field use modeFRONTIER for:
wing design and aerodynamics
aircraft structural components
metal sheet thermal forming
impact damage prediction
This study by Embraer and ITA is intended to present a two step methodology for the structural optimization of a preliminary composite wing based on automatic zone modelling strategy followed by GA iterations.
The main objective of this paper is to study and to propose a methodology in order to obtain an optimized internal wing structure of the UAV aircraft. Such optimization takes into account the static aeroelastic effects of Fluid-Structure Interaction (FSI) through Computation Fluid Dynamics (CFD) techniques coupled with the Finite Element Method (FEM).
This paper describes how the adjoint approach can help the designer to efﬁciently reduce the ﬂow separation onset at wing–fuselage intersection and to optimise the slat and ﬂap positions of a 3D high-lift conﬁguration. The optimisations were performed within a limited number of ﬂow evaluations, emphasising the beneﬁt of the adjoint approach in aircraft shape design.