Development of a Hypersonic Aircraft Design Optimization Tool

2014 ◽  
Vol 553 ◽  
pp. 847-852 ◽  
Author(s):  
Benjamin J. Morrell ◽  
David J. Munk ◽  
Gareth A. Vio ◽  
Dries Verstraete
Keyword(s):  
Structural Design ◽  
Current Practice ◽  
Thermal Stresses ◽  
Aircraft Design ◽  
Material Strength ◽  
Aircraft Structure ◽  
Aerodynamic Loads ◽  
Design And Optimization ◽  
Hypersonic Aircraft ◽  
Strength And Stiffness

The design and optimization of hypersonic aircraft is severely impacted by the high temperatures encountered during flight as they can lead to high thermal stresses and a significant reduction in material strength and stiffness. This reduction in rigidity of the structure requires innovative structural concepts and a stronger focus on aeroelastic deformations in the early design and optimisation of the aircraft structure. This imposes the need for a closer coupling of the aerodynamic and structural design tools than is current practice. The paper presents the development of a multi-disciplinary, closely coupled optimisation suite for hypersonic aircraft. An overview of the setup and structure of the optimization suite is given and the integration between the Tranair solver, used to determine the aerodynamic loads and temperatures, and MSC/NASTRAN, used for the structural sizing and design, will be given.

A Hypersonic Aircraft Optimization Tool with Strong Aerothermoelastic Coupling

2016 ◽  
Vol 846 ◽  
pp. 494-499 ◽  
Author(s):  
David J. Munk ◽  
Gareth A. Vio ◽  
Dries Verstraete
Keyword(s):  
Structural Design ◽  
Thermal Stresses ◽  
Equilibrium Analysis ◽  
Material Strength ◽  
Preliminary Design ◽  
Time Varying ◽  
Design And Optimization ◽  
Hypersonic Aircraft ◽  
Design Cycle ◽  
Strength And Stiffness

The design and optimization of hypersonic aircraft is severely impacted by the high temperatures encountered during flight as they can lead to high thermal stresses and a significant reduction in material strength and stiffness. This reduction in rigidity of the structure requires innovative structural concepts and a stronger focus on aerothermoelastic deformations in the early design and optimization phase of the design cycle. This imposes the need for a closer coupling of the aerodynamic, thermal and structural design tools than is currently in practice. The paper presents a multi-disciplinary, closely coupled optimization suite that is suitable for preliminary design in the hypersonic regime. The time varying temperature distribution is applied through an equilibrium analysis, and is coupled to the aerodynamics through the Tranair® solver. An analysis of the effect that the aerothermodynamic coupling has on the sizing of the aircraft is given, along with the effect of skin buckling. It is shown that the coupling of the aerothermodynamics drives the sizing of the structure and therefore must be considered for hypersonic applications.

Temperature Effects on Flutter of a Mach 5 Transport Aircraft Wing

2012 ◽  
Author(s):  
Dries Verstraete ◽  
Gareth A. Vio
Keyword(s):  
High Temperatures ◽  
Structural Design ◽  
Thermal Stresses ◽  
Material Strength ◽  
Aircraft Structure ◽  
Transport Aircraft ◽  
Hypersonic Aircraft ◽  
Structural Rigidity ◽  
Temperature Distributions ◽  
Strength And Stiffness

The high temperatures encountered during flight severely impact the structural design of hypersonic aircraft. They can lead to high thermal stresses and a significant reduction in material strength and stiffness. This reduction in structural rigidity requires innovative structural concepts and a stronger focus on aero-elastic deformations in the design and optimisation of the aircraft structure. This article investigates the effects of high temperatures on the flutter behavior of the wing of the A2 aircraft, a Mach 5 transport aircraft designed as part of the European Commission Framework VI LAPCAT program. The article presents results for various simplified temperature distributions. These temperature distributions were imposed to look at the fundamental trends in the flutter velocity and frequency with both temperature and temperature distribution. The results for the A2 wing are compared with other wing models to identify effects of geometry variations. The analysis shows that the flutter velocity drops by about 20% when a uniform temperature of 500 °C is applied to the wings. When temperature gradients are applied, a drop of 5–10% is found, which is in line with findings in literature.

Temperature Effect on the Structural Design of a Mach 8 Vehicle

2014 ◽  
Vol 553 ◽  
pp. 249-254
Author(s):  
Nicholas F. Giannelis ◽  
Gareth A. Vio ◽  
Dries Verstraete ◽  
Johan Steelant
Keyword(s):  
Dynamic Response ◽  
Material Properties ◽  
Structural Design ◽  
Structural Strength ◽  
Aircraft Design ◽  
Structural Performance ◽  
Temperature Changes ◽  
Hypersonic Aircraft ◽  
Temperature Distributions ◽  
Compound Effect

Hypersonic aircraft design is a pressing area of research. The motivation to create aircraft that can cross the globe in only a few hours is driving this forward but there are a number of challenges that need to be overcome. One of the principle challenges is the effect that temperature has on the structure. Temperature changes cause heating of the structure as well as changing the material properties of the affected structure. This has a compound effect in that the structures gets geometrically deformed, stiffness is reduced, and this will have an impact on the aerodynamic and structural performance of the vehicle. This article investigates the effect of two different structural concepts: a conventional rib-spar configuration and a pillow tank. A number of different structural options in terms of number of ribs / spars will be investigated. The structure will be optimised based on critical loading conditions. Results for various temperature distributions will be investigated, while looking at change on structural strength, in-flight static deformation and dynamic response. Keywords: Aeroelasticity, Hypersonics, Design.

Structural design and optimization of large cable–rib tension deployable antenna structure with dynamic constraint

2018 ◽  
Vol 151 ◽  
pp. 160-172 ◽  
Author(s):  
Ruiwei Liu ◽  
Hongwei Guo ◽  
Rongqiang Liu ◽  
Hongxiang Wang ◽  
Dewei Tang ◽  
...  
Keyword(s):  
Structural Design ◽  
Antenna Structure ◽  
Design And Optimization ◽  
Dynamic Constraint

scholarly journals Applying Artificial Neural Networks In Construction

2020 ◽  
Vol 143 ◽  
pp. 01029
Author(s):  
Anna Doroshenko
Keyword(s):  
Neural Networks ◽  
Pattern Recognition ◽  
Artificial Neural Networks ◽  
Construction Industry ◽  
Structural Design ◽  
Soil Mechanics ◽  
Construction Materials ◽  
Construction Engineering ◽  
Design And Optimization ◽  
Artificial Neural

Currently, artificial neural networks (ANN) are used to solve the following complex problems: pattern recognition, speech recognition, complex forecasts and others. The main applications of ANN are decision making, pattern recognition, optimization, forecasting, data analysis. This paper presents an overview of applications of ANN in construction industry, including energy efficiency and energy consumption, structural analysis, construction materials, smart city and BIM technologies, structural design and optimization, application forecasting, construction engineering and soil mechanics.

scholarly journals Conceptual Advanced Transport Aircraft Design Configuration for Sustained Hypersonic Flight

Aerospace ◽  
2018 ◽  
Vol 5 (3) ◽  
pp. 91 ◽  
Author(s):  
Can Alkaya ◽  
Ashish Alex Sam ◽  
Apostolos Pesyridis
Keyword(s):  
Aircraft Design ◽  
Combined Cycle ◽  
Cfd Analysis ◽  
Conceptual Approach ◽  
Transport Aircraft ◽  
Hypersonic Flight ◽  
Hypersonic Aircraft ◽  
Conceptual Aircraft Design

The conceptual aircraft design and its integration with a combined cycle engine for hypersonic cruise at Mach 8 is documented in this paper. The paper describes the process taken to develop a hypersonic aircraft from a conceptual approach. The discussion also includes the design and CFD analysis of the integrated combined cycle engine. A final conceptual hypersonic transport aircraft with an integrated combined cycle engine was achieved through this study. According to the analysis carried out, the aircraft is able to take-off and land at the airports it is intended to be used and will be able to generate enough thrust to sustain hypersonic cruise at an altitude of 30 km.

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