检索结果-内蒙古大学图书馆

International Conference on Noise and Vibration engineering 2006, ISMA 2006

作者： Uyama, Toshiyuki Okuma, Masaaki Oyama, Atsushi System Engineering Research Group Research and Development Center Yanmar Co.Ltd 1600-4Umegahara Maibara Shiga521-8511 Japan Department of Mechanical and Aerospace Engineering Tokyo Institute of Technology 2-12-1-I3-15 O-okayama Meguro-ku Tokyo 152-8552 Japan

ISBN: (纸本)9781629939278

In this paper, the authors present the results of experimental identification of the rigid body properties of an actual engine structure using an experimental spatial matrix identification method. The method identifies a set of spatial matrices using experimentally measured single-input-and-multiple-output frequency response functions within a frequency range of interest including the first natural frequency. The sets of spatial matrices can represent not only dynamic characteristics but also the rigid body properties of test structures. In this paper, an actual three-cylinder diesel engine is tested to verify the method especially focusing on the identification of its rigid body properties. The engine is complex so that many natural modes exist in the frequency range of interest. Nevertheless, the method successfully identified a set of spatial matrices that can represent the dynamic characteristics of the engine. Then, all the rigid body properties are derived from the identified mass matrix with practical accuracy. © (2006) by the Katholieke Universiteit Leuven Department of mechanical engineering All rights reserved.

关键词： Diesel engines

来源：评论

学校读者我要写书评

暂无评论

Application of lifetime PSP imaging method to a cryogenic wind tunnel

Application of lifetime PSP imaging method to a cryogenic wi...

引用

44th AIAA aerospace Sciences Meeting 2006

作者： Kojima, Toshiyuki Nagai, Hiroki Asai, Keisuke Mitsuo, Kazunori Iijima, Yoshimi Sakaue, Hirotaka Department of Aerospace Engineering Tohoku University Sendai Miyagi 980-8579 Japan Institute of Aerospace Technology Japan Aerospace Exploration Agency Chofu Tokyo 182-8522 Japan Department of Mechanical System and Design Tohoku University 6-6-01 Aoba Aramaki-Aza Aoba-ku Sendai Miyagi Department of Aerospace Engineering Tohoku University 6-6-01 Aoba Aramaki-Aza Aoba-ku Sendai Miyagi Aerodynamics Research Group Institute of Aerospace Technology 7-44-1 Jindaiji Higashi-Machi Chofu Tokyo

ISBN: (纸本)1563478072

The intensity-based method is a most common technique to convert Pressure-Sensitive Paint (PSP) images to surface pressure. However, this method is not suitable for a cryogenic wind tunnel because the thermal equilibrium condition cannot be achieved when the tunnel is stopped to take the wind-off reference image. In the present study, we applied the lifetimebased PSP imaging method to a cryogenic wind tunnel. Using this method, surface pressure can be calculated from two images obtained at the wind-on condition. In this experiment, a circular-arc bump model coated with PtTFPP/PTMSP paint was tested in the JAXA 0.1-m Cryogenic Transonic Wind Tunnel and PSP images were acquired using a UV-LED pulse illuminator and a multi-gated CCD camera. As a result, we succeeded in visualizing surface pressure distribution induced by a shock wave on the model by using lifetime imaging technique. However, nonnegligible deviation from pressure tap data was observed for the lifetime-based PSP data in the region of the model leading- and trailing- edges. Also the lifetime-based PSP data showed relatively rapid deterioration. These anomalies were not observed in the intensity-based PSP data in the same experiment. To use lifetime PSP imaging method for quantitative pressure measurement, photo-physical mechanism behind these anomalies should be clarified.

关键词： Image analysis

来源：评论

学校读者我要写书评

暂无评论

Integrated flight control and flow control using synthetic jet arrays

Integrated flight control and flow control using synthetic j...

引用

AIAA Guidance, Navigation, and Control Conference 2006

作者： Yong, Liu Ciuryla, Marcus Amitay, Miki Chiman, Kwan Myatt, James H. Xiaodong, Zhang Zhubing, Ren Casey, John P. Ohio University Athens OH 45701 Rensselaer Polytechnic Institute Troy NY 12180 Intelligent Automation Inc. Rockville MD 20855 Air Vehicles Directorate Air Force Research Laboratory Wright-Patterson AFB OH 45433 School of Electrical Engineering and Computer Science Ohio University Department of Mechanical Aerospace and Nuclear Engineering Rensselaer Polytechnic Institute Intelligent Automation Inc. AIAA

ISBN: (纸本)1563478196

In this paper, a novel integrated flight control and flow control system using synthetic jet arrays is presented. In the proposed system, a novel active flow control actuator, synthetic-jets-instrumented-wingtips were designed to enhance or replace traditional roll control of a specified airplane. Wind tunnel experiments were conducted to obtain the dynamic model of the synthetic-jets-instrumented-wing-tips. A closed-loop active flow control system was developed to reattach the flow at high angle of attacks. A high fidelity dynamic model for the airplane with the designed synthetic-jets-instrumented- wing-tips was developed based on wind tunnel experiments. A nonlinear integrated flight control and flow control system was developed and tested in simulations. Simulation results showed that the synthetic-jets-instrumented-wing-tips, in conjunction with the elevator and rudder, can effectively control the Cessna's attitude.

关键词： Flight dynamics

来源：评论

学校读者我要写书评

暂无评论

Investigation of lift force performance for a fixed wing micro aero vehicle

引用

Hangkong Taikong ji Minhang Xuekan/Journal of Aeronautics, Astronautics and Aviation 2006年第1期38 A卷 11-20页

作者： Tsai, Bor-Jang Zheng, Zhe-Chang Ho, Wu-Chi Graduate School of Mechanical and Aerospace Engineering Chung Hua University Hsin Chu 300 Taiwan Center for Aerospace and System Technology Industrial Technology Research Institute Hsin Chu 310 Taiwan

The objective of this paper is to study the aerodynamic performance of a micro airplane with 16 cm chord length, 20cm wingspan, aspect ratio 1.25, and 200-250 gw weight. The CFD software package was adopted for calculating the 3-D aerodynamic properties and simulating the flow-field of a micro airplane's Clark Y-type wing. This was in order to understand the problems encountered in the low aspect ratio and low Reynolds-number conditions. During this study counter-circulation phenomena;flow will have separation and reattachment to form so called bubble phenomena would occur when the angle of attack reach ±10°. In the 3-D cases, the lift coefficient with a vertical tail's slope will be slightly greater than that without a vertical rudder. The trend of the lift coefficient observed in the water-tunnel experiment matched that of the numerically calculated results. Also in the flow-field visualization, the dye will separate from the airfoil surface at two-thirds of the chord length and counter-circulation phenomena will occur. After the fixed wing design and aerodynamic analysis, a CAD/CAE/CAM module window platform is established as well.

关键词： aerospace vehicles

来源：评论

学校读者我要写书评

暂无评论

H-infinity static output-feedback control for rotorcraft

H-infinity static output-feedback control for rotorcraft

引用

AIAA Guidance, Navigation, and Control Conference 2006

作者： Gadewadikar, J. Lewis, F.L. Subbarao, Kamesh Peng, Kemao Chen, Ben Automation and Robotics Research Institute University of Texas at Arlington Fort-Worth TX 76118 United States Dept. of Mechanical and Aerospace Engineering University of Texas at Arlington Arlington TX 76018 United States Department of Electrical and Computer Engineering National University of Singapore Singapore Automation and Robotics Research Institute University of Texas at Arlington 7300 Jack Newell Blvd. S. Fort Worth TX 76118-7115 United States Automation and Robotics Research Institute Department of Electrical Engineering 7300 Jack Newell Blvd. S. Fort Worth TX 76118-7115 United States Department of Mechanical and Aerospace Engineering Box 19018 500 W. First St 211 Woolf Hall United States AIAA United States Department of Electrical and Computer Engineering National University of Singapore Singapore 117576 Singapore

ISBN: (纸本)1563478196

The problem of stabilization of an autonomous rotorcraft platform in a hover configuration subject to external disturbances is addressed. Necessary and sufficient conditions are presented for static output-feedback control of linear time-invariant systems using the H∞ approach. Simplified conditions are derived which only require the solution of two coupled matrix design equations. It is shown that the static output-feedback H ∞ solution does not generally yield a well-defined saddle point for the zero sum differential game;conditions are given under which it does. This paper also proposes a numerically efficient solution algorithm for the coupled design equations to determine the output-feedback gain. A major contribution is that an initial stabilizing gain is not needed. The efficacy of the control law and the disturbance accommodation properties are shown on a rotorcraft design example. The rotorcraft model is first loop shaped to achieve desired characteristics about the hover operating condition.

关键词： Helicopter rotors

来源：评论

学校读者我要写书评

暂无评论

Evaluation of elastic modulus by resonsce frequency and Euler-Berouilli equation

Evaluation of elastic modulus by resonsce frequency and Eule...

引用

13th International Congress on Sound and Vibration 2006, ICSV 2006

作者： Kang, Kisoo Kim, Koungsuk Choi, Manyong Kang, Youngjune Yang, Seongmo Hong, Dongpyo Korea Research Institute of Standard and Science P.O. Box 102 Yuseong Daejeon 305-600 Korea Republic of Department of Mechanical Design Engineering Chosun University 375 Seosuk-dong Gwangju 501-759 Korea Republic of Division of Mechanical and Aerospace System Engineering Chonbuk National University 664-14 Duckjin-dong Jeonju Jeonbuk 561-756 Korea Republic of

ISBN: (纸本)9781627481502

Various testing technique to determine the properties of film material have been investigated such as Nano indentation test, Bulge test, Micro tensile test and so on. They each have strength and weakness in the preparation of test specimen and the analysis of experimental result. Recently, optical techniques have been developed for measuring mechanical properties. Among these methods, an effective technique is the use of a cantilever beam load by various means. The study proposes the elastic modulus evaluation technique of a cantilever beam by vibration analysis based on time-average electronic speckle pattern interferometry (TA-ESPI) and Euler-Bernoulli equation of cantilever beam. Elastic material properties critically affect the vibration behaviour of structures. The observation can be inverted, leading to the idea that the vibration behaviour of a particular material can be used to determine the material's elastic properties. The principle is the foundation of all vibration-based identification methods which used the Euler-Bernoulli beam theory to link the elastic modulus with the specimen's natural frequency. Copyright© (2006) by the International institute of Acoustics & Vibration.

关键词： Cantilever beams

来源：评论

学校读者我要写书评

暂无评论

A Novel Simple Humidity Sensor Constructed by Sandwiched Cantilever

A Novel Simple Humidity Sensor Constructed by Sandwiched Can...

引用

IEEE SENSORS

作者： Rex Chen Chun-Hsun Chu Chia-Yen Lee Hao-Jen Chen Wood-Hi Cheng Micro-system technology center Industrial Technology and Research Institute Tainan Taiwan Department of Mechanical and Automation Engineering Da-Yeh University Changhua Taiwan Institute of Electro-optical Engineering NSYSU Kaohsiung Taiwan

This paper presents a novel humidity sensing mechanism. A simple sandwiched cantilever fabricated by traditional MEMS (microelectromechanic systems) process is proposed in this study. During the operation of humidity sensing, the polyimide-sensing layer, top layer of the sandwiched micro-cantilever, swells and the induced compressive stress pushes the tip of cantilever to deflect downward. To systematically investigate the performance of humidity sensor, three items were conducted in this study including response curve, time response, and hysteresis. The simple sensing mechanism had been verified and yielded a high average response time of 0.7 second during humidity range from 65%RH to 95%RH.

关键词： Silicon Micromechanical devices Temperature sensors Moisture mechanical sensors Sensor systems Wafer bonding Electrical resistance measurement Humidity measurement Platinum

来源：评论

学校读者我要写书评

暂无评论

Tensile properties and water absorption behavior of bamboo fiber reinforced composites

Tensile properties and water absorption behavior of bamboo f...

引用

作者： Kim, Hyo Jin Seo, Do Won Lim, Jae Kyoo Fujii, Toru Material and Fracture Lab. Dept. of Mechanical Design Chonbuk National University Deokjin 1-664-14 Jeonju JB561-756 Korea Republic of Automobile Hi-Technology Research Institute Faculty of Mechanical and Aerospace System Eng. Chonbuk National University Deokjin 1-664-14 Jeonju JB561-756 Korea Republic of Dept. of Mechanical Engineering and Systems Doshisha University Kyo-tanabe 610-0321 Japan

Bamboo fiber reinforced composites are used to evaluate the tensile properties and water absorption properties on various strain rates. To evaluate water absorption properties, specimens are immersed in pure water during 1 and 3 days at room temperature, and dried in 1 day at 50°C. Two kinds of polymer matrices such as polypropylene and biodegradable resin are used. Fractured surface are taken to study the failure mechanism and fiber/matrix interfacial adhesion. It is shown that it can be enhanced to improve their mechanical performance to reveal the relationship between tensile properties and water absorption according to different polymer matrices. Tensile strength is dramatically reduced by the effect of water absorption. Water-saturated samples present poor mechanical properties such as lower values of maximum strength.

关键词： Fiber reinforced materials

来源：评论

学校读者我要写书评

暂无评论

A comparison of Pose Estimation algorithms for Machine Vision based Aerial Refueling for UAVs

A comparison of Pose Estimation algorithms for Machine Visio...

引用

Mediterranean Conference on Control and automation (MED)

作者： Giampiero Campa Marco Mammarella Marcello R. Napolitano Mario L. Fravolini Lorenzo Pollini Brian Stolarik Department of Mechanical and AeroSpace Engineering West Virginia University Morgantown WV USA Department of Electronic and Information Engineering University of Perugia Perugia Italy Department of Electrical Systems and Automation University of Pisa Pisa Italy Institute of Scientific Research Fairmont WV USA

This paper focuses on the analysis of the performance of specific 'detection and labeling' and 'pose estimation' algorithms within a machine vision (MV)-based approach for the problem of autonomous aerial refueling (AAR) of UAVs. A robust 'detection and labeling algorithm' for the correct identification and sorting of the optical markers is proposed; a sorted list of marker positions is then provided as input to the 'pose estimation' algorithm. A detailed study of the performance of two specific 'pose estimation' algorithms (GLSDC and LHM) is performed with special emphasis on the required computational effort as well as on the robustness and error propagation characteristics. Extensive simulation studies demonstrate the performance of the LHM and GLSDC algorithms and show the importance of a robust 'detection and labeling' algorithm. The simulation effort is performed using a detailed modeling of the AAR maneuver according to the USAF refueling method

关键词： Machine vision Unmanned aerial vehicles Labeling Robustness Global Positioning system aerospace engineering Computational modeling Infrared sensors Laser radar Aircraft

来源：评论

学校读者我要写书评

暂无评论

Small helicon source for electrocleless plasma production and electromagnetic acceleration

Small helicon source for electrocleless plasma production an...

引用

AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference

作者： Toki, Kyoichiro Hashimoto, Takashi Makita, Kenji Shinohara, Shunjiro Hada, Tohru Ikeda, Yasushi Tanikawa, Takao Shamrai, Konstantin P. Funaki, Ikkho Tokyo University of Agriculture and Technology Koganei-city Tokyo 184-8588 Japan Kyushu University Fukuoka Fukuoka 816-8580 Japan Tokai University Hiratsuka Kanagawa 259-1292 Japan Institute for Nuclear Research Kiev 03680 Ukraine Japan Aerospace Exploration Agency Sagamihara Kanagawa 229-8510 Japan Department of Mechanical Systems Engineering Institute of Symbiotic Science and Technology 2-24-16 Naka-cho Koganei-city Tokyo Mechanical Systems Engineering 2-24-16 Naka-cho Koganei-city Tokyo Department of Advanced Energy Engineering Science Interdisciplinary Graduate School of Engineering Sciences 6-1 Kasuga-koen Kasuga Fukuoka Department of Earth System Science and Technology Interdisciplinary Graduate School of Engineering Sciences 6-1 Kasuga-koen Kasuga Fukuoka Research Institute of Science and Technology 1117 Kitakaname Hiratsuka Kanagawa Department of Plasma Theory Institute for Nuclear Research National Academy of Sciences of Ukraine 47 Prospect Nauki Kiev Research Division for Space Transportation Institute of Space and Astronautical Scinece 31-1 Yoshinodai Sagamihara Kanagawa AIAA

ISBN: (纸本)1563478188

A compact helicon source having an inner diameter of 2.5 cm with 46 cm long glass tube was investigated using a Boswell type antenna. Argon gas was fed into the glass tube from the upstream end at inner pressures, 10-40 mTorr corresponding to the mass flow rates, 0.5-2 mg/s. Two apparent jumps were observed with increasing RF power. The first jump took place at about 200 W RF input, from capacitively coupled plasma (CCP) to inductively coupled plasma (ICP), and the second jump was encountered at about 500 W RF input power from ICP to presumably the helicon mode. The maximum applied magnetic field was 800 gauss. The achieved plasma density exceeded 1013 cm-3 at the expected helicon mode. Based upon this result, a few concepts of electrodeless plasma acceleration techniques were suggested and also simulated by analyses. A preliminary experiment of the acceleration for proof-of-concept was conducted.

关键词： Helicons

来源：评论

学校读者我要写书评

暂无评论

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：

请选择收藏分类：

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

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：