Aircraft Design最新文献_第5页

Range and endurance of turboprop, turbofan, or piston–propeller aircraft having wings with or without camber 有或无弧度机翼的涡轮螺旋桨、涡扇或活塞螺旋桨飞机的航程和续航能力

Aircraft Design Pub Date : 1999-12-01 DOI: 10.1016/S1369-8869(99)00013-0

C. Bert

引用次数: 16

Range and endurance of turboprop, turbofan, or piston–propeller aircraft having wings with or without camber 有或无弧度机翼的涡轮螺旋桨、涡扇或活塞螺旋桨飞机的航程和续航能力

Aircraft Design Pub Date : 1999-12-01 DOI: 10.1016/S1369-8869(99)00013-0

Charles W Bert

引用次数: 16

Sensitivity analysis method for aeroelastic aircraft models 气动弹性飞机模型的灵敏度分析方法

Aircraft Design Pub Date : 1999-12-01 DOI: 10.1016/S1369-8869(99)00016-6

Anthony A. Giunta

{"title":"Sensitivity analysis method for aeroelastic aircraft models","authors":"Anthony A. Giunta","doi":"10.1016/S1369-8869(99)00016-6","DOIUrl":"10.1016/S1369-8869(99)00016-6","url":null,"abstract":"<div>A novel method has been developed for calculating gradients of aerodynamic force and moment coefficients for an aeroelastic aircraft model. This method is intended for use in preliminary-level aircraft design which typically involves computationally expensive aerodynamic and structural analyses. This method uses the global sensitivity equations (GSE) to express the aero-structural coupling in an aircraft model. In addition, a reduced-order modal analysis approach is employed to condense the coupling bandwidth between the aerodynamic and structural models. Coarse-grained parallel computing is applied to reduce the wall-clock computational time of the expensive aerodynamic analysis needed in this sensitivity analysis method. A supersonic transport aircraft model is examined in this study, subject to Mach 2.4 cruise flight conditions. Aerodynamic analysis is performed using a NASA-developed Euler/Navier-Stokes solver, and structural analysis is performed using commercial finite element analysis software. The GSE/modal analysis method is used to compute the sensitivity of the aerodynamic performance of the aircraft subject to perturbations in the angle-of-attack, wing sweep angle, and wing thickness. Good agreement is obtained between gradients computed with the GSE/modal analysis approach and the same quantities computed using a traditional, computationally expensive, finite difference approach. A cost analysis demonstrates that the GSE/modal analysis method is more computationally efficient than the traditional approach if gradients are needed for two or more aircraft design parameters.</div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"2 4","pages":"Pages 207-230"},"PeriodicalIF":0.0,"publicationDate":"1999-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(99)00016-6","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90219846","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 9

Aluminum structural member component weight as a function of wing loading 铝结构构件重量随机翼载荷的变化

Aircraft Design Pub Date : 1999-12-01 DOI: 10.1016/S1369-8869(99)00019-1

Charlie Svoboda

引用次数: 5

Aircraft configuration and flight profile optimization using simulated annealing 利用模拟退火技术优化飞机结构和飞行轮廓

Aircraft Design Pub Date : 1999-12-01 DOI: 10.1016/S1369-8869(99)00020-8

Rajkumar Pant , J.P. Fielding

引用次数: 16

Aerodynamic characteristics of multi-surface aircraft configurations 多面飞机构型气动特性研究

Aircraft Design Pub Date : 1999-12-01 DOI: 10.1016/S1369-8869(99)00015-4

Z. Pátek, L. Smrcek

引用次数: 8

Aerodynamic characteristics of multi-surface aircraft configurations 多面飞机构型气动特性研究

Aircraft Design Pub Date : 1999-12-01 DOI: 10.1016/S1369-8869(99)00015-4

Z Pátek , L Smrcek

{"title":"Aerodynamic characteristics of multi-surface aircraft configurations","authors":"Z Pátek , L Smrcek","doi":"10.1016/S1369-8869(99)00015-4","DOIUrl":"https://doi.org/10.1016/S1369-8869(99)00015-4","url":null,"abstract":"<div>This paper describes the wind tunnel testing of a specially designed aircraft model allowing systematic variation of geometric parameters related to overall aircraft configurations. The experiment work was carried out in the 1.8 m low-speed wind tunnel at VZLU, Aeronautical Research and Test Institute in Prague. The resultant data created an aerodynamic database for numerical modelling and verification. In addition, numerical validation of CFD package FLUENT was performed in the computerised fluid dynamic laboratory at the Department of Aerospace Engineering, University of Glasgow as a part of the ongoing research collaboration between both institutions. The wind-tunnel test program had two aims<ul><li>•to provide basic aerodynamic data effects of multi-surface aircraft configurations with a view to assessing the degree to which specific design features such as a combination of canard, wing and tail plane are beneficial to aircraft aerodynamic performance</li><li>•to provide an aerodynamic database for numerical validation.</li></ul>\u0000The aerodynamic data for different geometrical aircraft configurations with the same wing, fuselage, horizontal tail and canard surfaces were compared. The results show the magnitude of lift, drag and pitching moment depending on the angle of attack and various positions of canard, wing and horizontal tail with respect to one another. They have been compared with studied references. The experimental results are in accordance with theoretical predictions.</div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"2 4","pages":"Pages 191-206"},"PeriodicalIF":0.0,"publicationDate":"1999-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(99)00015-4","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"91754927","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 7

Launch vehicles conceptual design and structural analysis: an integrated approach via FEM 运载火箭概念设计与结构分析:基于有限元的综合方法

Aircraft Design Pub Date : 1999-09-01 DOI: 10.1016/S1369-8869(99)00011-7

Sergio Chiesa, Marco Di Sciuva, Luca Testore

引用次数: 6

A new numerical design tool for concept evaluation of propeller aircraft 一种新的螺旋桨飞机概念评估数值设计工具

Aircraft Design Pub Date : 1999-09-01 DOI: 10.1016/S1369-8869(99)00012-9

X Xie, Ch Haberland

{"title":"A new numerical design tool for concept evaluation of propeller aircraft","authors":"X Xie, Ch Haberland","doi":"10.1016/S1369-8869(99)00012-9","DOIUrl":"10.1016/S1369-8869(99)00012-9","url":null,"abstract":"<div>Besides the conceptual configuration development of an aircraft, a modern design tool should cover the evaluation of competitor aircraft, allow the assessment of technological and operational scenarios, and thus should have the potential to `right first time design'. For that purpose, the design system VisualCAPDA was developed on the basis of the former CAPDA system by evolutionarily introducing modern software standards under the premise of maximum reusability of existing FORTRAN coded methods. The new system plays the role of a workbench, which has to provide the analysis methods and necessary data. Through a graphical user interface the application of the system comes along as comfortable for the user as possible. In order to cover also turboprop aircraft, new modules with respect to cabin layout, propeller aerodynamic and acoustic analysis, propeller slip stream, engine modeling, geometry modeling are integrated into the design tool. The flexibility of the new system is demonstrated by applying it to the configurational development of propeller aircraft, investigating actual problems such as `Twin or Quad', `Turboprop or Turbofan', and finally, dealing with typical optimization problems.</div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"2 3","pages":"Pages 147-165"},"PeriodicalIF":0.0,"publicationDate":"1999-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(99)00012-9","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"72985433","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 8

Preliminary design of a low speed, long endurance remote piloted vehicles (RPV) for civil applications 一种低速、长航时民用遥控飞行器的初步设计

Aircraft Design Pub Date : 1999-09-01 DOI: 10.1016/S1369-8869(99)00014-2

Rodrigo Martı́nez-Val, Carlos Hernández

{"title":"Preliminary design of a low speed, long endurance remote piloted vehicles (RPV) for civil applications","authors":"Rodrigo Martı́nez-Val, Carlos Hernández","doi":"10.1016/S1369-8869(99)00014-2","DOIUrl":"10.1016/S1369-8869(99)00014-2","url":null,"abstract":"<div>The present paper describes the major features of an unmanned air vehicle, designed under very severe safety and performance requirements for missions of surveillance of borders and coasts, fire detection, and search and rescue. Because of safety reasons, two engines are mandatory for the aircraft. Additionally, the mission requirements can be translated into initial specifications in the following terms: payload not less than 42kg, cruise speed between 120 and 150km/h, maximum speed higher than 200km/h, cruise altitude of 3000m, service ceiling higher than 4000m, autonomy around 15h, gliding distance covered after full engine failure greater than 100<!--> km, and conventional take-off and landing in short unprepared runways. The design covers all common areas: configuration and sizing, aerodynamics, performance, stability and control, airworthiness, and initial structural design. Following suggestions from scholars and authorities, and taking into account the peculiar operational conditions of the vehicle, JAR 22 (Powered sailplanes, Utility category) are used as the basis for airworthiness certification.</div>","PeriodicalId":100070,"journal":{"name":"Aircraft Design","volume":"2 3","pages":"Pages 167-182"},"PeriodicalIF":0.0,"publicationDate":"1999-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1016/S1369-8869(99)00014-2","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"83704625","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 16