• Title/Summary/Keyword: aircraft design

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Propulsion System Modeling and Reduction for Conceptual Truss-Braced Wing Aircraft Design

  • Lee, Kyunghoon;Nam, Taewoo;Kang, Shinseong
    • International Journal of Aeronautical and Space Sciences
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    • v.18 no.4
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    • pp.651-661
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    • 2017
  • A truss-braced wing (TBW) aircraft has recently received increasing attention due to higher aerodynamic efficiency compared to conventional cantilever wing aircraft. For conceptual TBW aircraft design, we developed a propulsion-and-airframe integrated design environment by replacing a semi-empirical turbofan engine model with a thermodynamic cycle-based one built upon the numerical propulsion system simulation (NPSS). The constructed NPSS model benefitted TBW aircraft design study, as it could handle engine installation effects influencing engine fuel efficiency. The NPSS model also contributed to broadening TBW aircraft design space, for it provided turbofan engine design variables involving a technology factor reflecting progress in propulsion technology. To effectively consolidate the NPSS propulsion model with the TBW airframe model, we devised a rapid, approximate substitute of the NPSS model by reduced-order modeling (ROM) to resolve difficulties in model integration. In addition, we formed an artificial neural network (ANN) that associates engine component attributes evaluated by object-oriented weight analysis of turbine engine (WATE++) with engine design variables to determine engine weight and size, both of which bring together the propulsion and airframe system models. Through propulsion-andairframe design space exploration, we optimized TBW aircraft design for fuel saving and revealed that a simple engine model neglecting engine installation effects may overestimate TBW aircraft performance.

Aircraft design and manufacturing for UAV (무인 항공기 기체 설계 및 제작)

  • Hwang, Hyun-Su;Heo, Seop;Kim, Jong-Hyuk;Bae, Jae-Sung
    • Journal of Aerospace System Engineering
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    • v.2 no.4
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    • pp.38-43
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    • 2008
  • Since UAV has been developed, the demand of uav is increasing because of the advantage which are no injury people and less cost. Also, it has easy maintenance and adaptation because it will carry out each mission by only change payload. So, in this study, we performed aircraft design and manufacturing which it could have maximum payload weight when consider each mission has different weight of payload

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Development of the Aircraft Materials Selector Expert System

  • Lim, Kang-Hee;Guan, Zhi-Dong
    • Proceedings of the Korea Inteligent Information System Society Conference
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    • 2005.05a
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    • pp.302-305
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    • 2005
  • To comply to demand for a development requirement of aircraft design part, the expert system builds up standard knowledge-base based on presently maintained expert knowledge and experience in aircraft structure material selection. It also builds up database based on aircraft design open data, and standard calculation module used for present design and analysis method. This system is developed using Visual Basic language. The expert system standardize aircraft structure material selection and can be applied to all type of elementary stage of aircraft structure design. It is working on Windows, which has a friendly interface and is convenient for debugging, maintenance and transplanting. Explanation of the structure and the function of the system was given in this paper.

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Adaptable conceptual aircraft design model

  • Fioriti, Marco
    • Advances in aircraft and spacecraft science
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    • v.1 no.1
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    • pp.43-67
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    • 2014
  • This paper presents a new conceptual design model ACAD (Adaptable Conceptual Aircraft Design), which differs from the other models due to its considerable adaptability to the different classes of aircraft. Another significant feature is the simplicity of the process which leads to the preliminary design outputs and also allowing a substantial autonomy in design choices. The model performs the aircraft design in terms of total weight, weight of aircraft subsystems, airplane and engine performances, and basic aircraft configuration layout. Optimization processes were implemented to calculate the wing aspect ratio and to perform the design requirements fulfillment. In order to evaluate the model outcomes, different test cases are presented: a STOL ultralight airplane, a new commuter with open-rotor engines and a last generation fighter.

How to Use an Optimization-Based Method Capable of Balancing Safety, Reliability, and Weight in an Aircraft Design Process

  • Johansson, Cristina;Derelov, Micael;Olvander, Johan
    • Nuclear Engineering and Technology
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    • v.49 no.2
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    • pp.404-410
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    • 2017
  • In order to help decision-makers in the early design phase to improve and make more cost-efficient system safety and reliability baselines of aircraft design concepts, a method (Multi-objective Optimization for Safety and Reliability Trade-off) that is able to handle trade-offs such as system safety, system reliability, and other characteristics, for instance weight and cost, is used. Multi-objective Optimization for Safety and Reliability Trade-off has been developed and implemented at SAAB Aeronautics. The aim of this paper is to demonstrate how the implemented method might work to aid the selection of optimal design alternatives. The method is a three-step method: step 1 involves the modelling of each considered target, step 2 is optimization, and step 3 is the visualization and selection of results (results processing). The analysis is performed within Architecture Design and Preliminary Design steps, according to the company's Product Development Process. The lessons learned regarding the use of the implemented trade-off method in the three cases are presented. The results are a handful of solutions, a basis to aid in the selection of a design alternative. While the implementation of the trade-off method is performed for companies, there is nothing to prevent adapting this method, with minimal modifications, for use in other industrial applications.

Design Feature-Based Jetfighter Shape Modeling

  • Zang, Jing;Liu, Hu;Liu, Tianping;Ni, Xianping
    • International Journal of Aeronautical and Space Sciences
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    • v.14 no.3
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    • pp.222-228
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    • 2013
  • A jetfighter shape modeling method based on design features is researched, to improve the efficiency of shape modeling in the stage of conceptual aircraft design. The aircraft's general design features and shape parameters, including geometric and position parameters, are described. The coordinate systems of the entire aircraft and its components are defined. As a sample of local shape, a method of inlet intake modeling is introduced. The whole process of the modeling method is proposed. Three examples of different jetfighters are listed, to describe the achievement of basic layout, which includes four main elements. The Fusion of Components can be achieved by regulating the details of the sections of the fuselage. Sample Cases of typical layouts are shown to verify the effectiveness of the proposed method, which provides the basis for further analysis and optimization.

Development of a multidisciplinary design optimization framework for an efficient supersonic air vehicle

  • Allison, Darcy L.;Morris, Craig C.;Schetz, Joseph A.;Kapania, Rakesh K.;Watson, Layne T.;Deaton, Joshua D.
    • Advances in aircraft and spacecraft science
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    • v.2 no.1
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    • pp.17-44
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    • 2015
  • A modular multidisciplinary analysis and optimization framework has been built with the goal of performing conceptual design of an advanced efficient supersonic air vehicle. This paper addresses the specific challenge of designing this type of aircraft for a long range, supersonic cruise mission with a payload release. The framework includes all the disciplines expected for multidisciplinary supersonic aircraft design, although it also includes disciplines specifically required by an advanced aircraft that is tailless and has embedded engines. Several disciplines have been developed at multifidelity levels. The framework can be readily adapted to the conceptual design of other supersonic aircraft. Favorable results obtained from running the analysis framework for a B-58 supersonic bomber test case are presented as a validation of the methods employed.

Tensile performances of single-lap countersunk composite joints with metallic bushing

  • Cheng, Xiaoquan;Du, Xiaoyuan;Chen, Kun;Shu, Maosheng;Liu, Xiaodong;Chen, Gang
    • Steel and Composite Structures
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    • v.40 no.3
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    • pp.421-434
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    • 2021
  • Tensile tests were carried out on the single-lap countersunk composite joints with metallic bushing, and the load-displacement curves, strains and damage morphologies around the bolt hole were measured. A 3D progressive damage finite element model (FEM) was established in ABAQUS/Standard and verified by experimental results. Based on the validated model, tensile performances of the joints were investigated, including damage mechanism analysis of the laminate and the effect discussion of bushing thickness, tightening torque, interference fit size and etc. The results show that metallic bushing can improve ultimate bearing load of the joints. The stress distribution and initial damages caused by assembly around the laminate hole are little affected by bushing thickness. Appropriate tightening torque and interference fit size can improve tensile performances of the joint.

Cost-benefit analysis of public investment on aircraft design assurance infrastructure (중형항공기 설계검증·인프라구축과 인증기개발의 경제적 타당성 분석)

  • Yi, Jae-Kyung;Kim, Myeong-Kyun;Kim, Yong-Min;Lee, Tae-Hee;Kim, Do-Hyeon
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.38 no.9
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    • pp.900-906
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    • 2010
  • We analyse benefits and costs of investment on the assurance of aircraft design and development of related infrastructure. Although the discounted cash flow from the sales of aircrafts is found to be smaller than the amount of required investment, the net present value considering the effects of export increase, import substitution, and the accident cost reduction is very high. This justifies governmental investment, for the effects are not easily appropriated by private investors.

Papers : Transonic Wing Planform Design Using Multidisciplinary Optimization (논문 : 다분야 통합 최적설계 기법을 이용한 날개 기본 형상 설계)

  • Im,Jong-U;Gwon,Jang-Hyeok
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.30 no.1
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    • pp.20-27
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    • 2002
  • Aircraft design requires the intergration of several disciplines, inculding aerodynamics, structures, controls. To achieves advances in performance, each technology, or discipline must be more accurate in analysis and must be more highly intergrated. One of the important interdisciplinary interactions in mordern aircraft design is that of aerodynamics and structures. In this study, for increasing accuracy in each discipline's analysis, CFD for aerodynamic analysis and FEM for structurral analysis was used and, for considering important interdisciplinary interactions, aeroelastic effect was considered. As optimization algorithm, PBIL algorithm was used for global optima and was parallelized to alleviate the computational burden. The efficiency and accuracy of the present method was assesed by range maximiziation of reference of reference wing.