检索结果-内蒙古大学图书馆

您好，读者！请登录

内蒙古大学图书馆

首页
概况
党建
资源
服务
科研支持
- 论文收录引用证明
- 科技查新
知识产权
档案馆
帮助

咨询与建议

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

您的常用邮箱：*

您的手机号码：*

问题描述：

当前已输入0个字，您还可以输入200个字

全部搜索
期刊论文
图书
学位论文
标准
纸本馆藏
外文资源发现
数据库导航
超星发现

高级检索

时间限定

出版年份：

文献类型

图书期刊文献学位论文多媒体

馆藏选择

电子馆藏纸本馆藏

核心期刊

全部期刊 SCI 收录期刊 SSCI 收录期刊 EI 收录期刊 CSCD 收录期刊 CSSCI 收录期刊

语言

中文英文

文献类型

期刊文献图书学位论文标准纸本馆藏

帮助

文字说明：

T=题名（书名、题名），A=作者（责任者），K=主题词，P=出版物名称，PU=出版社名称，O=机构（作者单位、学位授予单位、专利申请人），L=中图分类号，C=学科分类号，U=全部字段，Y=年（出版发行年、学位年度、标准发布年）

检索规则说明：

AND代表“并且”；OR代表“或者”；NOT代表“不包含”；(注意必须大写,运算符两边需空一格)

检索范例：

范例一：(K=图书馆学 OR K=情报学) AND A=范并思 AND Y=1982-2016
范例二：P=计算机应用与软件 AND (U=C++ OR U=Basic) NOT K=Visual AND Y=2011-2016

分类表

所选分类

>> <<

限定检索结果

文献类型

54 篇 会议

馆藏范围

54 篇 电子文献
0 种 纸本馆藏

日期分布

学科分类号

53 篇 工学
- 48 篇 航空宇航科学与技...
- 45 篇 力学（可授工学、理...
- 35 篇 土木工程
- 16 篇 计算机科学与技术...
- 15 篇 软件工程
- 12 篇 控制科学与工程
- 5 篇 机械工程
- 5 篇 材料科学与工程（可...
- 4 篇 动力工程及工程热...
- 2 篇 电气工程
- 2 篇 化学工程与技术
- 1 篇 光学工程
- 1 篇 仪器科学与技术
- 1 篇 电子科学与技术（可...
- 1 篇 信息与通信工程
- 1 篇 建筑学
- 1 篇 船舶与海洋工程
44 篇 理学
- 29 篇 物理学
- 26 篇 数学
- 5 篇 系统科学
- 3 篇 大气科学
- 2 篇 化学
- 2 篇 统计学（可授理学、...
4 篇 管理学
- 4 篇 管理科学与工程(可...

主题

17 篇 aeroelasticity
11 篇 structural dynam...
3 篇 structural optim...
2 篇 wind tunnels
2 篇 aerodynamics
1 篇 research aircraf...
1 篇 shape optimizati...
1 篇 inverse problems
1 篇 computational fl...
1 篇 dynamic loads
1 篇 electromechanica...
1 篇 wings
1 篇 vortex flow
1 篇 flight envelopes
1 篇 flight simulator...
1 篇 natural frequenc...
1 篇 fuselages
1 篇 fluid structure ...
1 篇 time domain anal...
1 篇 finite element m...

机构

4 篇 delft university...
3 篇 zhukovsky
1 篇 bauman state tec...
1 篇 msc. software 26...
1 篇 prodera enclos d...
1 篇 garnaeva street ...
1 篇 1 zhukovsky str....
1 篇 aeroelasticity d...
1 篇 aeroelasticity b...
1 篇 central aerohydr...
1 篇 dassault aviatio...
1 篇 aviation design ...
1 篇 av. roraima 1000...
1 篇 school of aerona...
1 篇 psc tupolev 17 a...
1 篇 model design and...
1 篇 delft university...
1 篇 airbus group - a...
1 篇 delft university...
1 篇 aerospace centre...

作者

3 篇 werter noud p.m.
3 篇 climent h.
3 篇 de breuker roela...
2 篇 lepage arnaud
2 篇 cooper jonathan ...
2 篇 ishmuratov fanil...
2 篇 chedrik vasily v...
2 篇 arévalo f.
2 篇 karkle petr g.
2 篇 govers y.
2 篇 abdalla mostafa ...
1 篇 leonteva regina ...
1 篇 de souza carlos ...
1 篇 lemmens y.
1 篇 rodríguez jiméne...
1 篇 bykov artyom v.
1 篇 cooper j.e.
1 篇 romm aviv
1 篇 shanygin a.
1 篇 kalabuchov serge...

语言

54 篇 英文

检索条件"任意字段=16th International Forum on Aeroelasticity and Structural Dynamics, IFASD 2015"

共 54 条记录，以下是1-10 订阅

全选清除本页清除全部题录导出标记到"检索档案"

详细简洁

排序：

Comparison of EKF and Neural Network based wing shape estimation of a flexible wing demonstrator 19

Comparison of EKF and Neural Network based wing shape estima...

引用

19th international forum on aeroelasticity and structural dynamics, ifasd 2022

作者： Hadlaczky, Bence Zs. Friedman, Noémi Takarics, Béla Vanek, Bálint Institute for Computer Science and Control Eötvös Lóránd Research Network Kende u. 13-17 Budapest1111 Hungary

ISBN: (纸本)9788409423538

structural flexibility of advanced, large-wingspan aircrafts is a crucial factor which has huge influence on the dynamics and stability of these vehicles. In case of a highly flexible wing structure, there is a need for an efficient observer to measure and predict the structural changes and dynamics of the wing. However, the modal coordinates of the wing cannot be measured directly so designing a state observer is necessary. Since the flexible aircraft model is nonlinear, the classical Kalman filter approach can have limited performance. Instead, two state observer approaches are investigated in the paper. First, we present a model-based method for designing an extended Kalman filter (EKF) when only a linear parameter-varying model (LPV) is available to describe the behaviour of the real aircraft. Second, we present a data-driven approach for this problem which is based on the new KalmanNet architecture. Finally, the results of the two methods are evaluated on the T-Flex model of the FLiPASED H2020 project. © Proceedings of the international forum of aeroelasticity and structural dynamics 2022, ifasd 2022.

关键词： aeroelasticity

来源：评论

学校读者我要写书评

暂无评论

Design of an innovative wing tip device 17

Design of an innovative wing tip device

引用

17th international forum on aeroelasticity and structural dynamics, ifasd 2017

作者： Toffol, F. Fonte, F. Ricci, S. Dipartiment of Aerospace Science and Technology Politecnico of Milano via La Masa 34 Milano20156 Italy

ISBN: (纸本)9788897576280

this paper describes the design of an active wing tip for a regional transport aircraft is presented. the device is designed with the double purpose of increase the aircraft efficiency and to alleviate gust loads by means of an actively controlled control surface included in it. the control system used for the actuation uses a Static Output Feedback (SOF) architecture, and it is computed by optimizing a quadratic norm (H2) of the closed loop system. © 2017 international forum on aeroelasticity and structural dynamics (ifasd). All rights reserved.

关键词： aeroelasticity

来源：评论

学校读者我要写书评

暂无评论

CFD model of the transonic dynamics tunnel with applications 17

CFD model of the transonic dynamics tunnel with applications

引用

17th international forum on aeroelasticity and structural dynamics, ifasd 2017

作者： Chwalowski, Pawel Silva, Walter A. Wieseman, Carol D. Heeg, Jennifer Aeroelasticity Branch NASA Langley Research Center HamptonVA23681 United States

ISBN: (纸本)9788897576280

this paper presents the Computational Fluid dynamics (CFD) model of the flow in the NASA Langley Research Center Transonic dynamics Tunnel (TDT) with some recent applications. the TDT is a continuous-flow, closed circuit, slotted-test-section wind tunnel with a 16- by 16-foot test section with cropped corners. the tunnel was originally built as the 19-ft Pressure Tunnel in 1938, but it was converted to the current transonic tunnel in the 1950s, with capabilities to use either air or heavy gas at pressures from atmosphere down to near vacuum. In this study, experimental data acquired in the empty tunnel using R-134a as the test medium was used to calibrate the computational data. Experimental data from a recent TDT test of a full-span fighter configuration in air was then selected for comparison with the numerical data. During this test, the configuration experienced a flutter event in the transonic flow regime. Numerically, the flutter event is simulated both inside the CFD model of the TDT and in a classical free-air model. the preliminary results show that the wind-tunnel walls do affect the response of the tested vehicle but do not affect overall flutter prediction. © 2017 international forum on aeroelasticity and structural dynamics (ifasd). All rights reserved.

关键词： Wind tunnels

来源：评论

学校读者我要写书评

暂无评论

Flight testing using fast online aeroelastic identification techniques with dlr research aircraft halo 17

Flight testing using fast online aeroelastic identification ...

引用

17th international forum on aeroelasticity and structural dynamics, ifasd 2017

作者： Sinske, J. Govers, Y. Jelicic, G. Buchbach, R. Schwochow, J. Handojo, V. Böswald, M. Krüger, W.R. Institute of Aeroelasticity Göttingen Germany

ISBN: (纸本)9788897576280

the research aircraft HALO (High Altitude and Long Range Research Aircraft) of the German Aerospace Center (DLR) can be equipped with under-wing stores at different wing positions to transport scientific instruments for atmospheric research. the PMS (Particle Measurement System) carrier is one example of such an external store which can carry three instruments at the same time per wing to detect and count particles of different size (ice, carbon, dust, etc.) in different layers of the atmosphere. Any modification on an aircraft must be investigated numerically and experimentally to ensure the structural integrity and safe operation of the aircraft for all flight conditions. For loads and flutter analyses, flight test data is the essential means for validation. In preparation of the flight test, the airframe and the under-wing stores must be instrumented with acceleration sensors and strain gauges. In order to reduce flight test time and to maintain safety it is important to have tools available that indicate relevant safety margins to support the flight test engineers in making decisions for continuation of cancellation of a flight test. the DLR Institute of aeroelasticity in Göttingen (Germany) has developed a real-time analysis procedure for online identification of modal parameters like eigenfrequencies, damping ratios and mode shapes. these parameters vary with flight conditions, payload and fuel configuration and must be monitored to assess the aeroelastic stability margin of the system. In a joined flight test campaign, the department of Loads Analysis and Aeroelastic Design and the department of structural dynamics and System Identification of the DLR-Institute of aeroelasticity have tested the newly developed flight test procedure in 14 flight hours using the HALO research aircraft. A network of three distributed data acquisition modules enabled the recording of the flight test instrumentation with 51 accelerometers and 16 strain gauges integrated in Wheatst

关键词： Research aircraft

来源：评论

学校读者我要写书评

暂无评论

international forum on aeroelasticity and structural dynamics, ifasd 2015

International Forum on Aeroelasticity and Structural Dynamic...

引用

16th international forum on aeroelasticity and structural dynamics, ifasd 2015

the proceedings contain 142 papers. the topics discussed include: static aeroelastic analysis including geometric nonlinearities based on reduced ordered model (ROM);aeroelastic modeling and simulation of flexible jet transport aircraft with high-aspect-ratio wings;asymmetric limit cycle oscillations in systems with symmetric Freeplay;flight mechanical modeling and analysis of multi-body aircraft;a high-efficiency aeroelastic optimization method;multiobjective optimization for servoelastic response predictions of a fly-by-wire aircraft;flight loads and cumulative fatique damages monitoring for each aircraft during service life;on the validity range of piston theory;flutter and buffeting of long span suspension bridges in fully erected and partially erected conditions;unsteady viscous-inviscid coupling simulations of separated laminar flows around 2D airfoils;and a parametric and topological study on the use of viscoelastic material for flutter suppression.

关键词：

来源：评论

学校读者我要写书评

暂无评论

Evolutionary approach to structural design of wing under stress, buckling and aeroelasticity requirements 16

Evolutionary approach to structural design of wing under str...

引用

16th international forum on aeroelasticity and structural dynamics, ifasd 2015

作者： Chedrik, Vasily V. Tuktarov, Sergey A. Central Aerohydrodynamic Institute Russia

An evolutionary approach to synthesis of optimal aircraft component layouts has been developed. It is based on combined application of topology optimization, an engineering interpretation and optimum sizing of load-bearing structural elements. the developed approach gives possibility to include stress, buckling and aeroelasticity constraints altogether in unified design procedure and to get an optimal wing structure.

关键词： structural optimization

来源：评论

学校读者我要写书评

暂无评论

Experimental identification of the flexibility influence matrix of the aircraft engine mounted on pylon under the wing 16

Experimental identification of the flexibility influence mat...

引用

16th international forum on aeroelasticity and structural dynamics, ifasd 2015

作者： Grigoriev, Alexei Malyutin, Victor Chizhov, Alexei Gubernatenko, Andrei Zhukovsky Russia

In this paper there is a description of the approach of the experimental definition of Elastic influence coefficients' matrix (ECM) using a number of linear displacements sensors and automated system of load application. Using the definition of the ECM of the engine mounted on wing of the dynamically-scaled model of the passenger aircraft as an example, the key characteristics of its realization are shown, which allow to minimize the main methodological inaccuracies.

关键词： structural dynamics

来源：评论

学校读者我要写书评

暂无评论

Gyroscopic forces influence on aeroelasticity characteristics of an airplane with engines on pylons under the wing 16

Gyroscopic forces influence on aeroelasticity characteristic...

引用

16th international forum on aeroelasticity and structural dynamics, ifasd 2015

作者： Kuznetsov, A. Kuzmina, S. Ishmuratov, F. Mosunov, V. Zhukovsky Russia

the paper is devoted to development of a new method for aeroelasticity analysis with taking into account gyroscopic forces. the developed mathematical model is applicable for computation of dynamic aeroelasticity characteristics (eigenfrequencies and vibration forms, flutter, dynamic response in the frequency and time domain) in dependents on angular momentum of rotating rotor including case of elastic attachment of an engine on a pylon under the wing. the example of destabilizing influence of gyroscopic forces on flutter and aeroservoelasticity characteristics of an airplane with engines on pylons under the wing is described and analyzed.

关键词： Time domain analysis

来源：评论

学校读者我要写书评

暂无评论

Cror blade deformation, part 2: Aeroelastic computations and comparison with experiments 16

Cror blade deformation, part 2: Aeroelastic computations and...

引用

16th international forum on aeroelasticity and structural dynamics, ifasd 2015

作者： Mauffrey, Y. Geeraert, A. Verley, S. ONERA French Aerospace Lab. Châtillon92322 France

the present paper is dedicated to the numerical prediction of contra-rotating open rotors, CROR, blade deformations and the correlations with experimental data, in cruise conditions. the major challenge of this study lies in the nonlinear nature of the CROR blades aeroelastic behavior. Aerodynamic and centrifugal loadings on CROR blades may result in large deflection at blade tip and geometric nonlinearities have to be taken into account. In this paper we investigate the impact of these kinds of nonlinearities in static deformation numerical predictions.

关键词： aeroelasticity

来源：评论

学校读者我要写书评

暂无评论

Development of flight paramenters simulation technology for an aircraft with complex control system on flight simulators for more precise definition of in-service loads to solve the strength structural and life problems effectively 16

Development of flight paramenters simulation technology for ...

引用

16th international forum on aeroelasticity and structural dynamics, ifasd 2015

作者： Turchannikov, G.I. 1 Zhukovsky Street Moscow region Zhukovsky140180 Russia

the current work highlights the issues associated with the use of the unified computer model of an aircraft for multidisciplinary design, certification, and the structural monitoring during operation. the technology of using flight simulators for definition of structural loads of an aircraft had been developed and implemented. the database structure for storing and processing information had been formed.

关键词： Flight simulators

来源：评论

学校读者我要写书评

暂无评论

没有更多数据了...

全选清除本页清除全部题录导出标记到“检索档案”

共6页 << < 1 2 3 4 5 6 > >>

检索报告对象比较合并检索0

隐藏清空

合并搜索

回到顶部

执行限定条件

内容：

评分：

请选择保存的检索档案：

请选择收藏分类：

订阅名称：

通借通还

温馨提示：

图书名称：

借书校区：

取书校区：

手机号码：

邮箱地址：

一卡通帐号：

电话和邮箱必须正确填写，我们会与您联系确认。

联系人：

所在院系：

联系邮箱：

联系电话：

内蒙古自治区呼和浩特市赛罕区大学西街235号邮编: 010021

建议与咨询 留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

时间限定

文献类型

馆藏选择

核心期刊

语言

文献类型

帮助

文字说明：

检索规则说明：

检索范例：

分类表

所选分类

限定检索结果

文献类型

馆藏范围

日期分布

学科分类号

主题

机构

作者

语言

请选择保存的检索档案： 新增检索档案 确定 取消

请选择收藏分类： 新增自定义分类 确定 取消

通借通还

建议与咨询留下您的常用邮箱和电话号码，以便我们向您反馈解决方案和替代方法

请选择保存的检索档案：

请选择收藏分类：