Multidisciplinary Integrated Preliminary Design Applied to Unconventional Aircraft Configurations

2008 ◽  
Vol 45 (2) ◽  
pp. 581-590 ◽  
Author(s):  
Christian Werner-Westphal ◽  
Wolfgang Heinze ◽  
Peter Horst
Keyword(s):  
Preliminary Design ◽  
Unconventional Aircraft ◽  
Aircraft Configurations

scholarly journals Aero-Structural Optimization of Joined-Wing Aircraft

2017 ◽  
Vol 2017 (4) ◽  
pp. 48-63
Author(s):  
Miłosz Kalinowski
Keyword(s):  
Structural Optimization ◽  
Search Algorithm ◽  
Optimization Methods ◽  
Global Search ◽  
Preliminary Design ◽  
Electric Aircraft ◽  
Modular Algorithm ◽  
Lifting Surfaces ◽  
Joined Wing ◽  
Aircraft Configurations

Abstract Joined-wing aircraft due to its energy characteristics is a suitable configuration for electric aircraft when designed properly. However, because of the specific for this aircraft phenomenons (e.g. static indeterminacy of structure, aerodynamic interference of lifting surfaces) it demands more complicated methods to model its behavior than a traditional aircraft configurations. For these reasons the aero-structural optimization process is proposed for joined-wing aircrafts that is suitable for preliminary design. The process is a global search, modular algorithm based on automatic geometry generator, FEM solver and aerodynamic panel method. The range of aircraft was assumed as an objective function. The algorithm was successfully tested on UAV aircraft. The improvement of 19% of total aircraft range is achieved in comparison to baseline aircraft. Time of evaluation of this global search algorithm is similar to the time characteristic for local optimization methods. It allows to reduce the time and costs of preliminary design of joined-wing.

scholarly journals Noise shielding surrogate models using dynamic artificial neural networks

2021 ◽  
Vol 263 (1) ◽  
pp. 5216-5224
Author(s):  
Francesco Centracchio ◽  
Lorenzo Burghignoli ◽  
Giorgio Palma ◽  
Ilaria Cioffi ◽  
Umberto Iemma
Keyword(s):  
Optimal Design ◽  
Surrogate Models ◽  
Machine Learning Techniques ◽  
Learning Techniques ◽  
Computing Effort ◽  
Noise Shielding ◽  
Self Tuning ◽  
Artificial Neural ◽  
Unconventional Aircraft ◽  
Aircraft Configurations

The optimal design methodologies in aeronautics are known to be constrained by the computational burden required by direct simulations. Due to this reason, the development of efficient metamodelling techniques represents nowadays an imperative need for the designers. In fact, surrogate models has been demonstrated to significantly reduce the number of high-fidelity evaluations, thus alleviating the computing effort. Over the last years, the aeronautical designers community has switched from a design approach predominantly based on direct simulations to an extensive use of metamodels. Recently, to further improve the efficiency, several dynamic approaches based on parameters self-tuning have been developed to support the metamodel construction. This work deals with the use of surrogate models based on Artificial Neural Network for the noise shielding of unconventional aircraft configurations. Here, the insertion loss field of the a Blended Wing Body is reproduced by means of advanced machine learning techniques. The relevant framework is the calculation of the noise emitted by innovative aircraft configurations by means of suitable corrections of existing well-assessed noise prediction tools. The self-tuning algorithm has demonstrated to be accurate and efficient, and the observed performance discloses the possibility to implement numerical strategies for the reliable and robust unconventional aircraft optimal design

A model for solar powered aircraft preliminary design

2008 ◽  
Vol 112 (1128) ◽  
pp. 57-78 ◽  
Author(s):  
E. Rizzo ◽  
A. Frediani
Keyword(s):  
Mathematical Model ◽  
Great Emphasis ◽  
Preliminary Design ◽  
Research Activities ◽  
Solar Powered ◽  
Flying Wings ◽  
Long Endurance ◽  
Near Future ◽  
Aircraft Configurations ◽  
Aerodynamic Configuration

Abstract Solar powered aircraft are becoming more and more interesting for future long endurance missions at high altitudes, because they could provide Earth monitoring, telecommunications, etc. without any atmospheric pollution and, hopefully in the near future, with competitive costs compared with satellites. The research activities carried out till now have been mainly focused on flying wings or conventional aircraft configurations, with a great emphasis on the technological aspects. The present paper aims to define a mathematical model for solar powered aircraft preliminary design, valid independently of the aerodynamic configuration. A preliminary analysis is carried out in order to simulate Helios and the results are compared with those available from the flights of this aircraft. The proposed mathematical model is used also to compare four different aircraft configurations, namely: a flying wing, a conventional aircraft, a twin boom aircraft and a biplane aircraft. The results obtained are discussed in the paper and an optimum aircraft is analysed.

scholarly journals Coupling Mid-Fidelity Aerodynamics and Multibody Dynamics for the Aeroelastic Analysis of Rotary-Wing Vehicles

Energies ◽  
2021 ◽  
Vol 14 (21) ◽  
pp. 6979
Author(s):  
Alberto Savino ◽  
Alessandro Cocco ◽  
Alex Zanotti ◽  
Matteo Tugnoli ◽  
Pierangelo Masarati ◽  
...  
Keyword(s):  
Multibody Dynamics ◽  
Particle Method ◽  
Computational Effort ◽  
Preliminary Design ◽  
Vortex Particle Method ◽  
Aeroelastic Analysis ◽  
Tiltrotor Aircraft ◽  
Aircraft Configurations ◽  
Rotary Wing ◽  
Vortex Particle

A mid-fidelity aerodynamic solver based on the vortex particle method for wake modeling, DUST, is coupled through the partitioned multi-physics coupling library preCICE to a multibody dynamics code, MBDyn, to improve the accuracy of aeroelastic numerical analysis performed on rotary-wing vehicles. In this paper, the coupled tool is firstly validated by solving simple fixed-wing and rotary-wing problems from the open literature. The transient roll maneuver of a complete tiltrotor aircraft is then simulated, to show the capability of the coupled solver to analyze the aeroelasticity of complex rotorcraft configurations. Simulation results show the importance of the accurate representation of rotary wing aerodynamics provided by the vortex particle method for loads evaluation, aeroelastic stability assessment, and analysis of transient maneuvers of aircraft configurations characterized by complex interactional aerodynamics. The limited computational effort required by the mid-fidelity aerodynamic approach represents an effective trade-off in obtaining fast and accurate solutions that can be used for the preliminary design of novel rotary-wing vehicle configurations.

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