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.

AN OPTIMIZATION MODEL FOR PRELIMINARY STABILITY AND CONFIGURATION ANALYSES OF SEMI-SUBMERSIBLES

2021 ◽  
Vol 159 (A3) ◽  
Author(s):  
G D Gosain ◽  
R Sharma ◽  
Tae-wan Kim
Keyword(s):  
Optimization Model ◽  
Design Method ◽  
Optimization Techniques ◽  
Design Approach ◽  
Preliminary Design ◽  
Design Environment ◽  
Preliminary Stage ◽  
Steel Weight ◽  
Motion Characteristics ◽  
Almost All

In the modern era of design governed by economics and efficiency, the preliminary design of a semi-submersible is critically important because in an evolutionary design environment new designs evolve from the basic preliminary designs and the basic dimensions and configurations affect almost all the parameters related to the economics and efficiency (e.g. hydrodynamic response, stability, deck load and structural steel weight of the structure, etc.). The present paper is focused on exploring an optimum design method that aims not only at optimum motion characteristics but also optimum stability, manufacturing and operational efficiency. Our proposed method determines the most preferable optimum principal dimensions of a semi-submersible that satisfies the desired requirements for motion performance and stability at the preliminary stage of design. Our proposed design approach interlinks the mathematical design model with the global optimization techniques and this paper presents the preliminary design approach, the mathematical model of optimization. Finally, a real world design example of a semi-submersible is presented to show the applicability and efficiency of the proposed design optimization model at the preliminary stage of design.

Aerodynamic Loads Prediction in an Integrated Computer-Based Conceptual Design Environment

2003 ◽  
Author(s):  
M. W. Goldstraw ◽  
C. Bil ◽  
C. Nicholson
Keyword(s):  
Conceptual Design ◽  
Aircraft Design ◽  
Automated System ◽  
Aerodynamic Load ◽  
Design Environment ◽  
Design Data ◽  
Conceptual Design Phase ◽  
Design Changes ◽  
Computer Based ◽  
Step Over

An important aspect of successful aircraft design is the concept of ‘right first time’, as any design changes downstream can be costly and may cause project delays. This is most applicable to the conceptual design phase. However, in the early stages of aircraft design, data is limited and prone to inaccuracies. Consequently, a design will typically traverse through a number of iterations, improving and refining with each step. Over the past 15 years, computer-based tools have become commonplace in aircraft design [1]. In general, most computer-based tools have been developed for the more advanced stages of the design process. For these tools to be useful in conceptual design, they must be user-friendly, interactive, and provide quick return times. A classic example is the aerodynamic load data required for structural design. Both are dependent on geometric parameters, which may still be subject to change. To complete the analysis within practical time constraints, a highly integrated and automated system is required [2, 3]. This paper presents such a system, developed using industry accepted software components including AutoCAD, VSAERO and MSC Nastran. This system allows an automatic, structured topology mesh to be generated from a basic three-view aircraft drawing, which inputs directly into VSAERO for loads calculations. The loads are subsequently transferred to MSC Patran as a pre-processor for structural analysis using MSC Nastran. If the result is unsatisfactory, the geometry or placement of structural components can easily be changed and the process repeated. The design environment was developed using FORTRAN90. The results of an application of this system to a simple wing, as well as a regional transport aircraft, are also presented.

Design Optimization of Rigid Body Mechanism Topology

2007 ◽  
Author(s):  
Kai Sedlaczek ◽  
Peter Eberhard
Keyword(s):  
Rigid Body ◽  
Development Process ◽  
Combinatorial Problem ◽  
Optimization Techniques ◽  
Dimensional Synthesis ◽  
Ground Structure ◽  
Overall Design ◽  
Modern Computer ◽  
Gradient Based ◽  
Computer Based

Despite modern computer based design tools, the development process of new mechanisms is still based on the engineer’s experience, intuition and ingenuity. The goal of this work is to find a combination of linkage topology and joint types that represent the most suitable mechanism layout for a particular task. Optimization techniques are hardly used for this design problem except for the task of dimensional synthesis of a given mechanism type. This study presents and compares two different approaches to topology or type optimization of planar rigid body mechanisms that can be used to improve the overall design process. The first approach is based on a truss-like ground structure that represents an over-determined system of rigid bars where the most appropriate topology can be extracted from this ground structure by means of gradient based optimization algorithms. In the second approach, we use a genetic algorithm for the intrinsically combinatorial problem of topology synthesis. We explain both approaches and show their capabilities, their advantages and drawbacks.

scholarly journals Conceptual design of sonic boom stealth supersonic transports

2022 ◽  
Author(s):  
Yicheng Sun ◽  
Howard Smith
Keyword(s):  
Conceptual Design ◽  
Aircraft Design ◽  
Design Model ◽  
Sonic Boom ◽  
Volume Distribution ◽  
Design Environment ◽  
Supersonic Aircraft ◽  
Business Jet ◽  
Multidisciplinary Perspective ◽  
Aircraft Conceptual Design

AbstractThis paper introduces a supersonic transport aircraft design model developed in the GENUS aircraft conceptual design environment. A conceptual design model appropriate to supersonic transports with low-to-medium-fidelity methods are developed in GENUS. With this model, the authors reveal the relationship between the sonic boom signature and the lift and volume distributions and the possibility to optimise the lift distribution and volume distribution together so that they can cancel each other at some region. A new inspiring design concept—sonic boom stealth is proposed by the authors. The sonic boom stealth concept is expected to inspire the supersonic aircraft designers to design low-boom concepts through aircraft shaping and to achieve low ground impacts. A family of different classes of supersonic aircraft, including a single-seat supersonic demonstrator (0.47 psf), a 10-passenger supersonic business jet (0.90 psf) and a 50-seat supersonic airliner (1.02 psf), are designed to demonstrate the sonic boom stealth design principles. Although, there are challenges to balance the volume with packaging and control requirements, these concepts prove the feasibility of low-boom low-drag design for supersonic transports from a multidisciplinary perspective.

An Optimization Model for Preliminary Stability and Configuration Analyses of Semi-submersibles

2017 ◽  
Vol Vol 159 (A3) ◽  
Author(s):  
G D Gosain ◽  
R Sharma ◽  
Tae-wan Kim
Keyword(s):  
Optimization Model ◽  
Design Method ◽  
Optimization Techniques ◽  
Design Approach ◽  
Preliminary Design ◽  
Design Environment ◽  
Preliminary Stage ◽  
Steel Weight ◽  
Motion Characteristics ◽  
Almost All

In the modern era of design governed by economics and efficiency, the preliminary design of a semi-submersible is critically important because in an evolutionary design environment new designs evolve from the basic preliminary designs and the basic dimensions and configurations affect almost all the parameters related to the economics and efficiency (e.g. hydrodynamic response, stability, deck load and structural steel weight of the structure, etc.). The present paper is focused on exploring an optimum design method that aims not only at optimum motion characteristics but also optimum stability, manufacturing and operational efficiency. Our proposed method determines the most preferable optimum principal dimensions of a semi-submersible that satisfies the desired requirements for motion performance and stability at the preliminary stage of design. Our proposed design approach interlinks the mathematical design model with the global optimization techniques and this paper presents the preliminary design approach, the mathematical model of optimization. Finally, a real world design example of a semi-submersible is presented to show the applicability and efficiency of the proposed design optimization model at the preliminary stage of design.

PERANCANGAN SISTEM PEMBELAJARAN MOBILE (M-LEARNING) BERBASIS ANDROID PADA MATERI BANGUN DATAR DAN BANGUN RUANG

2018 ◽  
Vol 1 (2) ◽  
pp. 1-17
Author(s):  
Tedi Budiman
Keyword(s):  
Mobile Learning ◽  
Design Method ◽  
Case Study Method ◽  
Application Development ◽  
Software Application ◽  
Rapid Application Development ◽  
User Design ◽  
Design Software ◽  
Application Programs

One example of the growing information technology today is mobile learning, mobile learning which refers to mobile technology as a learning medium. Mobile learning is learning that is unique for each student to access learning materials anywhere, anytime. Mobile learning is suitable as a model of learning for the students to make it easier to get an understanding of a given subject, such as math is pretty complicated and always using formulas.The design method that I use is the case study method, namely, learning, searching and collecting data related to the study. While the development of engineering design software application programs that will be used by the author is the method of Rapid Application Development (RAD), which consists of 4 stages: Requirements Planning Phase, User Design Phase, Construction Phase and Phase Cotuver.

A new jig-shape optimization method for the high aspect ratio wing

2018 ◽  
Vol 91 (1) ◽  
pp. 124-133
Author(s):  
Zhe Yuan ◽  
Shihui Huo ◽  
Jianting Ren
Keyword(s):  
Aspect Ratio ◽  
Shape Optimization ◽  
High Aspect Ratio ◽  
Optimization Design ◽  
Design Method ◽  
Aircraft Design ◽  
Optimization Method ◽  
Attack Angle ◽  
Structural Deformation ◽  
Content Type

Purpose Computational efficiency is always the major concern in aircraft design. The purpose of this research is to investigate an efficient jig-shape optimization design method. A new jig-shape optimization method is presented in the current study and its application on the high aspect ratio wing is discussed. Design/methodology/approach First, the effects of bending and torsion on aerodynamic distribution were discussed. The effect of bending deformation was equivalent to the change of attack angle through a new equivalent method. The equivalent attack angle showed a linear dependence on the quadratic function of bending. Then, a new jig-shape optimization method taking integrated structural deformation into account was proposed. The method was realized by four substeps: object decomposition, optimization design, inversion and evaluation. Findings After the new jig-shape optimization design, both aerodynamic distribution and structural configuration have satisfactory results. Meanwhile, the method takes both bending and torsion deformation into account. Practical implications The new jig-shape optimization method can be well used for the high aspect ratio wing. Originality/value The new method is an innovation based on the traditional single parameter design method. It is suitable for engineering application.

The Influence of Hierarchical Decisions on Ship Design

1987 ◽  
Vol 24 (02) ◽  
pp. 131-142
Author(s):  
Warren F. Smith ◽  
Saiyid Kamal ◽  
Farrokh Mistree
Keyword(s):  
Decision Support ◽  
Design Method ◽  
System Optimization ◽  
Ship Design ◽  
Valuable Insight ◽  
Engineering Systems ◽  
Traditional Design ◽  
Computer Based ◽  
Effectiveness And Efficiency ◽  
Insight Into

The design of engineering systems involves the design of dependent subsystems and the integration of these into a whole. A typical system has the characteristics of being multileveled, multidimensional, and multidisciplined in nature. It is this complexity which causes problems for the designer in making well-founded decisions. A decision support technique has been developed which offers a structured facility for the design of the subsystems and for the modeling of the interaction which is present between subsystems. The method, employing optimization procedures, allows all aspects of the system design to be considered concurrently, to produce the "best" solution, as defined by the specifications. This is in contrast to the traditional design method, which is iterative and cyclic in nature, involving sequential reevaluation and refinement. In this paper, the effectiveness and efficiency of the decision support problem approach is demonstrated using the hierarchical characteristics of a design for a barge. The barge problem, though basic in form, is comprehensive in concept and tutorial in nature. As a formulation for "system" optimization, it uses a computer-based method for solution and illustrates the virtues of a multilevel/multidisciplinary approach to design and decision-making. It also exhibits the same characteristics and provides valuable insight into the solution of the more complex problems encountered in practical ship design.

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