Preliminary Aircraft Design in a Collaborative Multidisciplinary Design Environment

2011 ◽  
Author(s):  
Thomas Zill ◽  
Daniel Böhnke ◽  
Bjoern Nagel
Keyword(s):  
Aircraft Design ◽  
Multidisciplinary Design ◽  
Design Environment ◽  
Preliminary Aircraft Design

scholarly journals The Effect of Sub-systems Design Parameters on Preliminary Aircraft Design in a Multidisciplinary Design Environment

2018 ◽  
Vol 29 ◽  
pp. 135-145 ◽  
Author(s):  
Marco Fioriti ◽  
Luca Boggero ◽  
Sabrina Corpino ◽  
Prajwal Shiva Prakasha ◽  
Pier Davide Ciampa ◽  
...  
Keyword(s):  
Systems Design ◽  
Aircraft Design ◽  
Multidisciplinary Design ◽  
Design Parameters ◽  
Design Environment ◽  
Preliminary Aircraft Design

Method for Estimation of Electrical Wiring Interconnection Systems in Preliminary Aircraft Design

2019 ◽  
Vol 56 (3) ◽  
pp. 1259-1263 ◽  
Author(s):  
Francesca Tomasella ◽  
Marco Fioriti ◽  
Luca Boggero ◽  
Sabrina Corpino
Keyword(s):  
Aircraft Design ◽  
Preliminary Aircraft Design ◽  
Electrical Wiring

Multiobjective Collaborative Optimization

1997 ◽  
Author(s):  
Ravindra V. Tappeta ◽  
John E. Renaud
Keyword(s):  
System Design ◽  
Systems Design ◽  
Collaborative Optimization ◽  
Multidisciplinary Design ◽  
Accurate Estimation ◽  
Successful Implementation ◽  
Design Environment ◽  
Comprehensive Overview ◽  
Design Problems ◽  
Multidisciplinary Systems

Abstract This investigation focuses on the development of modifications to the Collaborative Optimization (CO) approach to multidisciplinary systems design, that will provide solution capabilities for multiobjective problems. The primary goal of this research is to provide a comprehensive overview and development of mathematically rigorous optimization strategies for MultiObjective Collaborative Optimization (MOCO). Collaborative Optimization strategies provide design optimization capabilities to discipline designers within a multidisciplinary design environment. To date these CO strategies have primarily been applied to system design problems which have a single objective function. Recent investigations involving multidisciplinary design simulators have reported success in applying CO to multiobjective system design problems. In this research three MultiObjective Collaborative Optimization (MOCO) strategies are developed, reviewed and implemented in a comparative study. The goal of this effort is to provide an in depth comparison of different MOCO strategies available to system designers. Each of the three strategies makes use of parameter sensitivities within multilevel solution strategies. In implementation studies, each of the three MOCO strategies is effective in solving two multiobjective multidisciplinary systems design problems. Results indicate that these MOCO strategies require an accurate estimation of parameter sensitivities for successful implementation. In each of the three MOCO strategies these parameter sensitivities are obtained using post-optimality analysis techniques.

scholarly journals The GENUS aircraft conceptual design environment

2018 ◽  
Vol 233 (8) ◽  
pp. 2932-2947 ◽  
Author(s):  
H Smith ◽  
D Sziroczák ◽  
GE Abbe ◽  
P Okonkwo
Keyword(s):  
Practical Reasoning ◽  
Design Method ◽  
Aircraft Design ◽  
Theoretical Background ◽  
Optimization Techniques ◽  
Design Environment ◽  
Modern Computer ◽  
Computer Based ◽  
Design Software ◽  
Aircraft Conceptual Design

The design of aircraft has evolved over time from the classical design approach to the more modern computer-based design method utilizing multivariate design optimization. In recent years, aircraft concepts and configurations have become more diverse and complex thus pushing many synthesis packages beyond their capability. Furthermore, many examples of aircraft design software focus on the analysis of one particular concept thus requiring separate packages for each concept. This can lead to complications in comparing concepts and configurations as differences in performance may originate from different prediction toolsets being used. This paper presents the GENUS Aircraft Design Framework developed by Cranfield University’s Aircraft Design Group to address these issues. The paper reviews available aircraft design methodologies and describes the challenges faced in their development and application. Following this, the GENUS aircraft design environment is introduced, along with the theoretical background and practical reasoning behind the program architecture. Particular attention is given to the programming, choice of methodology, and optimization techniques involved. Subsequently, some applications of the developed methodology, implemented in the framework are presented to illustrate the diversity of the approach. Three special classes of aircraft design concept are presented briefly.

scholarly journals Impact of mission requirements on the design of low observable UCAV configurations

2019 ◽  
Vol 91 (10) ◽  
pp. 1295-1307
Author(s):  
Eduardo Sepulveda Palacios ◽  
Howard Smith
Keyword(s):  
Low Cost ◽  
Leading Edge ◽  
Aircraft Design ◽  
Considerable Proportion ◽  
Design Environment ◽  
Sweep Angle ◽  
Content Type ◽  
Aerial Warfare ◽  
And Performance ◽  
Excess Power

Purpose The purpose of this paper is to characterise the effects of mission and performance parameters on the design space of low observable subsonic unmanned combat aerial vehicles (UCAVs) operating in typical Hi-Lo-Hi ground strike missions. Design/methodology/approach Conceptual design methodologies appropriate to low observable, tailless UCAVs have been integrated into a multidisciplinary aircraft design environment, GENUS, developed at Cranfield University’s aircraft design group. A basic Hi-Lo-Hi mission is designed and a baseline configuration is established through the GENUS framework. Subsequently, an evolutionary optimiser and a robust gradient-based optimiser are used to obtain convergent design solutions for various leading edge sweep angles, mission ranges, cruise Mach numbers and other operational constraints. Findings The results indicate that performance constraints, specifically in the form of specific excess power (SEP), have a large influence on the overall sizing of subsonic tailless UCAVs. This requirement drives the engine sizing, which represents a considerable proportion of the empty and gross mass of the vehicle. Cruise Mach number studies show that no significant advantages exist for operating at low speeds while maintaining performance requirements consistent with combat missions. There is a drastic increase in the vehicle’s mass and thrust requirements for flight speeds above Mach 0.8, with low sweep configurations showing a more pronounced effect. Increases in the range are not overly dependent on the leading edge sweep angle. Top-level radar cross section (RCS) results also favour configurations with higher leading edge sweep angles, especially from the nose-on aspect. Finally, research and development costs are shown to be directly linked to engine size. Originality/value This research shows the use of an integrated aircraft design environment that incorporates aerodynamics, performance, packaging and low observability aspects into the optimisation loop. Through this methodology, this study supports the efforts towards characterising and establishing alternate visions of the future of aerial warfare through the use of low cost, survivable unmanned platforms in network-centric cooperative tasks.

A distributed toolbox for multidisciplinary preliminary aircraft design

2011 ◽  
Vol 2 (1-4) ◽  
pp. 57-68 ◽  
Author(s):  
Carsten M. Liersch ◽  
Martin Hepperle
Keyword(s):  
Aircraft Design ◽  
Preliminary Aircraft Design
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