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

68 篇 会议
59 篇 期刊文献
4 册 图书

馆藏范围

131 篇 电子文献
0 种 纸本馆藏

日期分布

学科分类号

89 篇 工学
- 44 篇 力学（可授工学、理...
- 41 篇 计算机科学与技术...
- 37 篇 软件工程
- 29 篇 航空宇航科学与技...
- 18 篇 动力工程及工程热...
- 14 篇 机械工程
- 14 篇 土木工程
- 11 篇 电子科学与技术（可...
- 10 篇 电气工程
- 9 篇 材料科学与工程（可...
- 8 篇 化学工程与技术
- 7 篇 控制科学与工程
- 7 篇 生物医学工程（可授...
- 6 篇 生物工程
- 5 篇 仪器科学与技术
- 4 篇 建筑学
- 4 篇 船舶与海洋工程
78 篇 理学
- 44 篇 物理学
- 42 篇 数学
- 13 篇 化学
- 10 篇 生物学
- 8 篇 统计学（可授理学、...
- 4 篇 海洋科学
- 3 篇 系统科学
9 篇 管理学
- 7 篇 管理科学与工程(可...
- 3 篇 图书情报与档案管...
6 篇 医学
- 6 篇 临床医学
- 5 篇 基础医学(可授医学...
- 3 篇 药学(可授医学、理...
2 篇 法学
2 篇 教育学
1 篇 农学
1 篇 军事学

主题

5 篇 computational fl...
4 篇 electronics pack...
4 篇 nasa
4 篇 computational in...
4 篇 artificial intel...
3 篇 design optimizat...
3 篇 soldering
3 篇 computational mo...
3 篇 electronics indu...
3 篇 density function...
2 篇 circuit simulati...
2 篇 temperature
2 篇 interoperability
2 篇 finite volume me...
2 篇 wide band gap se...
2 篇 wind tunnels
2 篇 logic gates
2 篇 lead
2 篇 hemts
2 篇 capacitive senso...

机构

6 篇 research group o...
5 篇 department of th...
5 篇 department of in...
4 篇 faculty of engin...
4 篇 uow malaysia kdu...
4 篇 applied modeling...
4 篇 department of co...
4 篇 department of ap...
4 篇 modeling evoluti...
4 篇 nasa ames resear...
4 篇 department of ma...
3 篇 cetc key laborat...
3 篇 applied modeling...
3 篇 statistics and o...
3 篇 applied simulati...
3 篇 modeling and sim...
3 篇 science and tech...
3 篇 nasa ames resear...
3 篇 research group o...
3 篇 applied modeling...

作者

10 篇 kiris cetin c.
8 篇 ferdows m.
8 篇 housman jeffrey ...
6 篇 aftosmis michael...
6 篇 brehm christoph
5 篇 moini-yekta shay...
5 篇 barad michael f.
5 篇 sozer emre
4 篇 pandian vasant
4 篇 mohammad shamsul...
4 篇 elias munapo
4 篇 k. wyatt
4 篇 rolly intan
4 篇 j. joshua thomas
4 篇 gerhard-wilhelm ...
4 篇 geurts b.j.
4 篇 vladimir panchen...
4 篇 nemec marian
3 篇 yao wei
3 篇 ferdows mohammad

语言

126 篇 英文
5 篇 其他

检索条件"机构=Applied Simulation and Modeling Research"

共 131 条记录，以下是81-90 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 computed and measured vortex evolution for a UH-60A rotor in forward flight 31

Comparison of computed and measured vortex evolution for a U...

引用

31st AIAA applied Aerodynamics Conference

作者： Ahmad, Jasim U. Yamauchi, Gloria K. Kao, David L. NASA Ames Research Center Applied Modeling and Simulation Branch M/S 258-2 Moffett Field CA 94035 United States NASA Ames Research Center Aeromechanics Branch M/S 243-12 Moffett Field CA 94035 United States NASA Ames Research Center Computational Technologies Branch M/S 258-5 Moffett Field CA 94035 United States

A Computational Fluid Dynamics (CFD) simulation using the Navier-Stokes equations was performed to determine the evolutionary and dynamical characteristics of the vortex flowfield for a highly flexible aeroelastic UH-60A rotor in forward flight. The experimental wake data were acquired using Particle Image Velocimetry (PIV) during a test of the fullscale UH-60A rotor in the National Full-Scale Aerodynamics Complex 40- by 80-Foot Wind Tunnel. The PIV measurements were made in a stationary cross-flow plane at 90 deg rotor azimuth. The CFD simulation was performed using the OVERFLOW CFD solver loosely coupled with the rotorcraft comprehensive code CAMRAD II. Characteristics of vortices captured in the PIV plane from different blades are compared with CFD calculations. The blade airloads were calculated using two different turbulence models. A limited spatial, temporal, and CFD/comprehensive-code coupling sensitivity analysis was performed in order to verify the unsteady helicopter simulations with a moving rotor grid system.

关键词： Computational fluid dynamics

来源：评论

学校读者我要写书评

暂无评论

Realistic simulation of IEEE 802.11p channel in mobile Vehicle to Vehicle communication

Realistic simulation of IEEE 802.11p channel in mobile Vehic...

引用

Conference on Microwave Techniques, COMITE

作者： Tarikul Islam Yongchang Hu Ertan Onur Bert Boltjes J.F.C.M de Jongh Faculty of EEMCS Delft University of Technology Delft Netherlands Modeling Simulation & Gaming Delft Netherlands Network Technology Netherlands Organization for Applied Scientific Research Delft Netherlands

Intelligent Transportation Systems (ITS) is becoming an important paradigm, because of its ability to enhance safety and to mitigate congestion on road traffic scenarios. Realizing the fact that data collection scheme from in-situ test beds for large number of vehicles is always expensive and time consuming, before being employed in large scale, such safety critical system should be tested narrowing down the gap between real circumstances and analytical models in a simulation platform. It is evident that underlying radio wave propagation models can comprise the validity of large scale vehicular network simulation results. Vehicle-to-Vehicle (V2V) channels have higher dynamics due to rapidly varying topologies and environments which have significant impact on performance study of upper layer protocols and applications. In spite of the fact that few measurement based empirical channel models are present in the literature, they are not tested for large scale vehicular networks. In this study, we simulate suburban scenarios with hundreds of IEEE802.11p nodes in the OPNET simulation environment with more realistic channel models. The standard OPNET propagation model was replaced by Nakagami-m fading channel. For the sake of modeling, changing relative velocity attribute and separation distance, power spectrum and fading parameter-m were defined as function of velocity and separation distance respectively. Then statistics were collected to evaluate performance of physical and higher layers. Primarily we have found all the vehicles within the standard requirement for Dedicated Short Range Communications (DSRC) range of 1 kilometer may not receive packets, which was also found in several earlier publications.

关键词： Vehicles Channel models Interference Computational modeling Signal to noise ratio Rayleigh channels

来源：评论

学校读者我要写书评

暂无评论

Elastically shaped wing optimization and aircraft concept for improved cruise efficiency

Elastically shaped wing optimization and aircraft concept fo...

引用

51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013

作者： Nguyen, Nhan Trinh, Khanh Reynolds, Kevin Kless, James Aftosmis, Michael Urnes, James Ippolito, Corey NASA Ames Research Center Intelligent Systems Division Moffett Field CA 94035 United States Stinger Ghaffarian Technologies Inc Intelligent Systems Division Moffett Field CA 94035 United States Science and Technology Corp Systems Analysis Branch Moffett Field CA 94035 United States Boeing Research and Technology Platform Systems/Subsystems Technology St. Louis MO 63166 United States Applied Modeling and Simulation Branch United States

ISBN: (纸本)9781624101816

This paper presents the findings of a study conducted in 2010 by the NASA Innovation Fund Award project entitled "Elastically Shaped Future Air Vehicle Concept". The study presents three themes in support of meeting national and global aviation challenges of reducing fuel burn for present and future aviation systems. The first theme addresses the drag reduction goal through innovative vehicle configurations via non-planar wing optimization. Two wing candidate concepts have been identified from the wing optimization: a drooped wing shape and an inflected wing shape. The drooped wing shape is a truly biologically inspired wing concept that mimics a seagull wing and could achieve about 5% to 6% drag reduction, which is aerodynamically significant. From a practical perspective, this concept would require new radical changes to the current aircraft development capabilities for new vehicles with futuristic-looking wings such as this concept. The inflected wing concepts could achieve between 3% to 4% drag reduction. While the drag reduction benefit may be less, the inflected-wing concept could have a near-term impact since this concept could be developed within the current aircraft development capabilities. The second theme addresses the drag reduction goal through a new concept of elastic wing shaping control. By aeroelastically tailoring the wing shape with active control to maintain optimal aerodynamics, a significant drag reduction benefit could be realized. A significant reduction in fuel burn for long-range cruise from elastic wing shaping control could be realized. To realize the potential of the elastic wing shaping control concept, the third theme emerges that addresses the drag reduction goal through a new aerodynamic control effector called a variable camber continuous trailing edge flap. Conventional aerodynamic control surfaces are discrete independent surfaces that cause geometric discontinuities at the trailing edge region. These discontinuities promote vort

关键词： Drag reduction

来源：评论

学校读者我要写书评

暂无评论

Rapid Data Generation (RDG) - Data discovery, access, and enhancement across the M&S data enterprise

Rapid Data Generation (RDG) - Data discovery, access, and en...

引用

Spring simulation Interoperability Workshop 2013, SIW 2013

作者： Scrudder, Roy Carlton, Bruce Gupton, Kevin O'Connell, Ralph Wieckhorst, Robin Hodges, Jeff Cox, Rob Blount, Elaine Applied Research Laboratories University of Texas at Austin 10000 Burnet Rd. Austin TX 78758 United States Joint Staff J6 DD C2I 116B Lake View Parkway Suffolk VA 23435 United States Joint Training Integration and Evaluation Center 12000 Research Parkway Orlando FL 32826 United States Army Modeling and Simulation Office 5801 Hurley Road Fort Belvoir VA 22060 United States PEO Simulation Training and Instrumentation 12350 Research Parkway Orlando FL 32826 United States General Dynamics Information Technology 1030 University Blvd. Suffolk VA 23435 United States

ISBN: (纸本)9781627480192

Obtaining and preparing data for modeling and simulation-based activities is a huge consumer of resources, regardless of the activity supported by M&S (training, testing, acquisition, planning, etc.). Opportunities for leveraging data across efforts employing M&S within a community and across communities also are largely unmet. The US Department of Defense (DoD) M&S Steering Committee established the Rapid Data Generation (RDG) project to address exactly these challenges, and thereby reduce the time and effort required to discover, integrate, and correlate M&S data and enable data sharing. The RDG initial operating capability to be fielded in Fall 2013 will address order of battle data in an unclassified environment. Subsequent capability releases will expand RDG into classified environments and address additional types of data, with environmental representation data being the next to be fielded. This paper will describe the evolution of capabilities and technical approach that the RDG project is using to satisfy requirements across the DoD M&S enterprise. The RDG Common Data Production Environment (CDPE) architecture will be described and data sources to be integrated through the CDPE will be identified. This service-oriented architecture enables the integration of metadata from multiple data providers, facilitates the retrieval of data from foundation data providers and data integrators, and supports the enhancement of data using services. The paper will also describe how open standards and open source software are employed in this architecture to enable data sharing and interoperability.

关键词： Open source software

来源：评论

学校读者我要写书评

暂无评论

Detached eddy simulation of the UH-60 rotor wake using adaptive mesh refinement

Detached eddy simulation of the UH-60 rotor wake using adapt...

引用

68th American Helicopter Society International Annual Forum 2012

作者： Chaderjian, Neal M. Ahmad, Jasim U. Fundamental Modeling and Simulation Branch NASA Ames Research Center Moffett Field CA 94035 United States Applied Modeling and Simulation Branch NASA Ames Research Center Moffett Field CA 94035 United States

ISBN: (纸本)9781622760510

Time-dependent Navier-Stokes flow simulations have been carried out for a UH-60 rotor with simplified hub in forward flight and hover flight conditions. Flexible rotor blades and flight trim conditions are modeled and established by loosely coupling the OVERFLOW Computational Fluid Dynamics (CFD) code with the CAMRAD II helicopter comprehensive code. High order spatial differences, Adaptive Mesh Refinement (AMR), and Detached Eddy simulation (DES) are used to obtain highly resolved vortex wakes, where the largest turbulent structures are captured. Special attention is directed towards ensuring the dual time accuracy is within the asymptotic range, and verifying the loose coupling convergence process using AMR. The AMR/DES simulation produced vortical worms for forward flight and hover conditions, similar to previous results obtained for the TRAM rotor in hover. AMR proved to be an efficient means to capture a rotor wake without apriori knowledge of the wake shape.

关键词： Wakes

来源：评论

学校读者我要写书评

暂无评论

Large scale aeroelastic data for design of rotating blades using Navier-Stokes equations 12

Large scale aeroelastic data for design of rotating blades u...

引用

12th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference and 14th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference

作者： Guruswamy, Guru P. NASA Advanced Supercomputing Division Ames Research Center Applied Modeling and Simulation Branch Moffett Field CA United States

ISBN: (数字)9781600869303

ISBN: (纸本)9781600869303

Bending-torsion flutter boundaries for rotating blades are computed using unsteady aerodynamic data obtained by time accurately solving the Navier-Stokes equations. A modal approach is used for computing the flutter boundary. Flutter speeds are computed by solving eigenvalue equations that track down the system damping to identify flutter point. Aerodynamic data required for the analysis is computed by time accurately integrating aerodynamic equations while the blades are undergoing modal motions at various oscillating frequencies. Validity of the approach is established by comparing the flutter speed results with those measured for a non-rotating blade. Results are demonstrated for a typical rotating blade. Parallel computing resources are utilized to cope with computational costs associated with use of the Navier-Stokes equations.

关键词： Navier Stokes equations

来源：评论

学校读者我要写书评

暂无评论

Fluid/structure interaction modeling of helicopters using Navier Stokes equations

Fluid/structure interaction modeling of helicopters using Na...

引用

AIAA modeling and simulation Technologies Conference 2012

作者： Guruswamy, Guru P. Applied Modeling and Simulation Branch NASA Advanced Supercomputing Division Ames Research Center Moffett Field CA United States

ISBN: (纸本)9781624101830

A time-accurate procedure to model fluid/structure interactions of helicopter blades is presented. The Navier-Stokes equations in conjunction with the one-equation Spalart-Allmaras turbulence model are used to compute the flow. Structural dynamics is modeled using the modal equations. The aerodynamic and structural dynamic equations are coupled time-accurately using the linear acceleration method of Newmark direct integration scheme. Effects of time accuracy on the computed results are investigated. Results are compared with experimental data for a full rotor blade system.

关键词： Structural dynamics

来源：评论

学校读者我要写书评

暂无评论

CFD-based computations of flexible helicopter blades for stability analysis

CFD-based computations of flexible helicopter blades for sta...

引用

52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

作者： Guruswamy, Guru P. NASA Advanced Supercomputing Division Ames Research Center Applied Modeling and Simulation Branch Moffett Field CA United States

ISBN: (纸本)9781600869518

As a collaborative effort among government aerospace research laboratories, an advanced version of a widely used computational fluid dynamics code, OVERFLOW2.1z, was recently released. This latest version includes additions to model multiple flexible, rotating blades. This paper describes how the OVERFLOW code is applied to improve the accuracy of airload computations from the linear lifting line theory that uses displacements from the beam model. In the case used, data transfers required at every revolution are managed through a Unix-based script that runs jobs on large supercluster computers. Results are demonstrated for the 4-bladed UH-60A helicopter, deviations of computed data from flight data are evaluated, and Fourier analysis post-processings suitable for aeroelastic stability computations are performed. Use of airload data for flutter speed computations needed for stability analysis is demonstrated for a typical section of a blade.

关键词： research laboratories

来源：评论

学校读者我要写书评

暂无评论

High-order accurate CFD/CSD simulation of the UH-60 rotor in forward flight

High-order accurate CFD/CSD simulation of the UH-60 rotor in...

引用

29th AIAA applied Aerodynamics Conference 2011

作者： Ahmad, Jasim U. Chaderjian, Neal M. Applied Modeling and Simulation Branch M/S 258-2 NASA Ames Research Center Moffett Field CA 94035 United States Fundamental Modeling and Simulation Branch M/S 258-2 NASA Ames Research Center Moffett Field CA 94035 United States

ISBN: (纸本)9781624101458

Time-dependent Reynolds-averaged Navier-Stokes simulations for a highly flexible aeroelastic UH-60A rotor have been carried out for forward flight. The fluid structure interaction is accomplished by loosely coupling the OVERFLOW Computational Fluid Dynamics (CFD) code with the helicopter comprehensive code CAMRAD II. The latter includes Computational Structural Dynamics (CSD) with rotor trim capability. Computations are performed using spatial differences of 5th-order for inviscid fluxes, 2nd-order accurate viscous fluxes, and 2nd-order time accuracy. Dual time-stepping accuracy is examined and recommendations provided for an appropriate time step and number of subiterations. The predicted sectional normal forces and pitching moments are compared with flight-test data for high-speed and low-speed level-flight conditions. The low-speed case has significant Blade Vortex Interaction (BVI). The current simulations demonstrate a factor of two improvement in state-of-the-art airloads prediction accuracy for CFD/CSD simulations. This is attributed to the use of improved spatial accuracy.

关键词： Computational fluid dynamics

来源：评论

学校读者我要写书评

暂无评论

Aerodynamic database generation for SRB separation from a heavy lift launch vehicle

Aerodynamic database generation for SRB separation from a he...

引用

29th AIAA applied Aerodynamics Conference 2011

作者： Gusman, Marshall R. Barad, Michael F. Kiris, Cetin C. Applied Modeling and Simulation Branch NAS Division MS N258-2 Science and Technology Corporation Moffett Field CA 94035 United States Applied Modeling and Simulation Branch NAS Division MS N258-2 NASA Ames Research Center Moffett Field CA 94035 United States

ISBN: (纸本)9781624101458

An engineering approach is presented for database generation of aerodynamic force and moment coefficients on Solid Rocket Boosters (SRBs) during separation from a Heavy Lift Launch Vehicle. The approach balances accuracy and affordability by generating a steadystate database of solutions using the inviscid flow solver Cart3D with adjoint based adaptive mesh refinement. The procedure also includes point checking the database using the viscous Reynolds Averaged Navier-Stokes solver OVERFLOW. The simulation matrix consists of 3 degrees of freedom by planar translation and rotation of the SRBs from their original attached positions. Good agreement with viscous multi-species simulations has confirmed that the single-species inviscid assumptions are valid for this plume impingement flow. The database provides axial forces, side forces, and yaw moments on the SRBs during separation from the core. This data is to be used for vehicle and trajectory planning to avoid re-contacting the core. © 2011 by the American Institute of Aeronautics and Astronautics, Inc.

关键词： Database systems

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14页 << < 5 6 7 8 9 10 11 12 13 14 > >>

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：