检索结果-内蒙古大学图书馆

A Design of Prototype 1C2M Railway Vehicle propulsion control system Considering Slip Reduction of Traction Motor

JOURNAL OF ELECTRICAL ENGINEERING & TECHNOLOGY 2015年第1期10卷 429-435页

作者： Chang, Chin-Young Kim, Jae-Moon Kim, Yoon-Ho Chung Ang Univ Dept Elect & Elect Engn Seoul South Korea Korea Natl Univ Transportat Dept Transportat Syst Engn Chungju Si Chungcheongbuk South Korea

This study proposes a re-adhesion algorithm that has stable traction effort for rolling stock slip/slide minimization when deliverable traction decreases by slip. The proposed scheme estimates appropriate reference speed using two encoders for reducing slip and controls traction effort stably and has stable control characteristics for disturbance. The algorithm which uses the maximum adhesive effort by instantaneous estimation of adhesion force stably controls traction effort and gives rolling stock excellent acceleration and deceleration characteristics. And a slip sensing element that can quickly detect slip is used. Load motor and inverter were checked in various slip conditions for creating various line conditions.

关键词： Railway vehicle propulsion control system Adhesion effort Slip

来源：评论

学校读者我要写书评

暂无评论

Simulation Research on Intelligent control for propulsion system of Large Ship

Simulation Research on Intelligent Control for Propulsion Sy...

引用

MTS/IEEE OCEANS Conference

作者： Wang, Yuanhui Chen, Bofei Li, Shijie Bian, Xinqian Harbin Engn Univ Coll Automat Harbin Peoples R China

ISBN: (纸本)9780933957398

In recent years, with the great progress in maritime transport, ships have increasingly tended to be more large and rapid. Thus, single engine and single-propeller large cannot meet the requirements of the various performances, multi-engine multi-propeller able to meet a variety of different sailing ship maneuvering characteristics of working conditions, and gradually adopted by the people. With the complicated of the propulsion requirements of the control system also will increase, large ship propulsion control systems have been paid more and more attention. The variability during the operation of the ship operating condition also increases the difficulty of controlling the propulsion system. It is an important problem to control the ship propulsion system in order to make the large ship keep speed being constant or changing quickly. In order to solve the problem, some work are carried out for a large ship with four engines and four propellers as an example in this paper. Firstly, a four degree of freedom motion mathematical model of large ship is established based on MMG method. Secondly, Steam turbine model, propeller model and sea environment model are established separately. Then, fuzzy theory is used to solve the propulsion system control problem, and a Fuzzy-PID controller for the ship propulsion system is designed. Finally, computer simulation with C++ program design is carried out to validate the modeling and control method. The simulation tests include the ship maneuvering motion in calm water and sea state four conditions. The simulation results show that the designed propulsion control system of large ship is perfect in performance.

关键词： large ship fuzzy PID propulsion control system simulation

来源：评论

学校读者我要写书评

暂无评论

Advanced instrumentation for next-generation aerospace propulsion control systems

引用

JOURNAL OF propulsion AND POWER 1996年第1期12卷 205-206页

作者： Barkhoudarian, S Cross, GS Lorenzo, CF NASA LEWIS RES CTRDIV INSTRUMENTAT & CONTROLS TECHNOLCLEVELANDOH 44135

New concepts for the control of jet and rocket engines and the new hybrid engines have introduced new instrumentation requirements. These control concepts are analyzed to determine their required measurands. Following this, advanced measurement technologies from recent major NASA/Department of Defense (DOD)/industry-sponsored measurement technology development program are compiled and, matched with the corresponding measurands. This is followed by a ranking of the sensor technologies based on the number of their applications. Thus, a list is provided of advanced measurement technologies suggested for further development and use in advanced aerospace propulsion control systems.

关键词： propulsion control system Space Shuttle Main Engine Projectiles control Rocket Temperature Sensors propulsion system Jet Engines Laser Induced Breakdown Spectroscopy Planar Laser Induced Fluorescence Sensor Technology

来源：评论

学校读者我要写书评

暂无评论

INTEGRATED FLIGHT/propulsion control - SUBsystem SPECIFICATIONS

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 1994年第1期17卷 201-208页

作者： ROCK, SM EMAMINAEINI, A NEIGHBORS, K INTEGRATED SYST INC ADV SYST GRPSANTA CLARACA

In many systems it is required or desirable to implement a control law in a partitioned or decentralized architecture comprised of subsystems. This paper presents a technique for deriving specifications for each subsystem that, if met, guarantee that total system performance (e.g., stability) goals will be met when the subsystems are combined. The approach is based on the concepts of robust control theory and generates results that are expressed in the frequency domain as allowed error envelopes about nominal requirements. Although emphasis is placed on generating specifications that guarantee only the stability of the combined system, extensions that would guarantee performance are also discussed. The focus of the paper is the integrated flight/propulsion control problem in which specifications on the propulsion system are derived based on the mission-level requirements of the aircraft. However, the results are generally applicable. A numerical example demonstrating the application of the procedure is included.

关键词： propulsion control system Closed Loop Transfer Function propulsion system Frequency Domain Nonlinear systems Flight control Design Handling Qualities Short Takeoff and Vertical Landing control system Design Fixed Wing Aircraft

来源：评论

学校读者我要写书评

暂无评论

DESIGN AND PILOTED SIMULATION OF INTEGRATED FLIGHT propulsion controlS FOR STOVL AIRCRAFT

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 1993年第6期16卷 993-998页

作者： FRANKLIN, JA ENGELLAND, SA NASA Ames Research Center Moffett Field CA

An integrated flight/propulsion control system has been designed for operation of short takeoff and vertical landing (STOVL) fighter aircraft over the low-speed, powered-lift flight envelope. The control system employs command modes for attitude, flightpath angle, and nightpath acceleration during transition, and translational velocity command for hover and vertical landing. In this paper, only the longitudinal modes of control are discussed. Piloted evaluations of the control system have been conducted on Ames Research Center's Vertical Motion Simulator. Results indicate that level 1 flying qualities are achieved during transition and vertical landing over a wide range of wind, atmospheric turbulence, and visibility conditions.

关键词： propulsion control system Short Takeoff and Vertical Landing Powered Lift Aircraft Vertical Landing Flying Qualities Flight Path Angle Blended Wing Body Configurations Ames Research Center Fighter Aircraft Atmospheric Turbulence

来源：评论

学校读者我要写书评

暂无评论

Optimal shock wave parameters for supersonic inlets

引用

JOURNAL OF propulsion AND POWER 1996年第1期12卷 202-205页

作者： Safarik, P Polak, A UNIV CINCINNATI DEPT AEROSP ENGN & ENGN MECHCINCINNATIOH 45221

This work considers optimization tasks all using the same optimization criterion. These tasks produce substantially different results. Sample calculations are presented to demonstrate these tasks.

关键词： Shock Waves Supersonic Inlets Space Shuttle Main Engine Mach Number control Rocket Oblique Shock Integrated High Performance Turbine Engine Technology Conservation of Mass Sensor Technology propulsion control system

来源：评论

学校读者我要写书评

暂无评论

propulsion control of superconducting linear synchronous motor vehicle

引用

IEEE TRANSACTIONS ON MAGNETICS 1997年第5期33卷 3460-3462页

作者： Sakamoto, T Shiromizu, T Laboratory of Chromatography DEPg.Fac.Quimica Universidad Nacional Autonoma de Mexico Circuito interior Cd Universitaria/CP 04510 Mexico D.F.Mexico

The armature current of a superconducting Linear Synchronous Motor (LSM) for a maglev vehicle is controlled to produce a suitable propulsion force so that the vehicle follows the reference speed signal sent from a control station. Besides the power is supplied from some inverters to the LSM armature sections where the vehicle exists. This paper shows an exact mathematical modeling of the propulsion control system to treat the system analytically, which is used for, designing controllers and performance computer simulations. The calculated results include the simulations when the vehicle goes through power feeder section borders and tunnels that have a large aerodynamic drag force with taking account of an inverter failure.

关键词： vehicle propulsion control system linear synchronous motors control station propulsion Motor Vehicles Linux Security Module propulsion control armature current Magnetic levitation vehicles Superconductivity Inventors

来源：评论

学校读者我要写书评

暂无评论

control of a miniducted-fan unmanned aerial vehicle using active flow control

引用

JOURNAL OF AIRCRAFT 2002年第4期39卷 561-571页

作者： Fung, PHY Amitay, M Georgia Inst Technol Sch Mech Engn Atlanta GA 30332 USA Georgia Tech Res Inst Aerosp Transportat & Adv Syst Lab Smyrna GA 30080 USA

An experimental study of the control of the flowfield around the stator vanes of a new miniducted-fan unmanned aerial vehicle (UAV) using synthetic jet actuators is presented. As a result, a new control approach of the UAV is proposed in which active flow control can be used instead of moving control surfaces and articulated rotor blade. Therefore, the UAV's propulsion and control systems are reduced to a single moving part, a fixed pitch propeller. This mechanical simplicity makes the active How control application particularly attractive for development of mini- and micro-UAVs. The directional and rotational control of the UAV (0.5 m in diameter and 0.15 m in height) can be obtained by controlling the flow within the duct. This can be achieved by the activation of surface fluidic actuators based on synthetic jet technology that are located downstream from a miniature passive obstruction. The synthetic jets are Hush mounted on a set of four fixed stators located downstream from the propeller. In the present work the flowfield around the stator vanes is studied using particle image velocimetry at different radial locations, where the geometrical angle of attack of the stator vanes is fixed at 10 deg and the propeller rotational speed is either 4300 or 6200 rpm. Velocity measurements in the near wake are also obtained, and the data show that as a result of the Actuation the cross-stream extent of the wake and its velocity deficit are significantly reduced and the How is quasi-steady.

关键词： UAV Active Flow control Propellers Actuators Aerodynamic Performance Particle Image Velocimetry Articulated Rotor propulsion control system control Surfaces Vortex Sheet

来源：评论

学校读者我要写书评

暂无评论

DEPLOYMENT control OF A CABLE CONNECTING A SHIP TO AN UNDERWATER VEHICLE

引用

JOURNAL OF GUIDANCE control AND DYNAMICS 1994年第6期17卷 1327-1332页

作者： BANERJEE, AK DO, VN Lockheed Missiles & Space Company Sunnyvale California 94089

This paper describes the development of an underwater cable dynamics model and a realistic control system that allows deployment, regulation, and retrieval of an unmanned underwater vehicle tethered to a ship. An order-n algorithm for a variable-mass cable subject to hydrodynamic forces and motion constraints is used to simulate the dynamics of the system. The dynamics of the underwater vehicle is separately given with the cable tension nonlinearly affecting the vehicle speed. This creates a constraint on the cable motion that depends nonlinearly on the constraint force, a problem that is iteratively solved using constraint stabilization. The cable dynamics model and the controller presented in this paper can be used to answer many design questions relating to tethered underwater vehicles.

关键词： Unmanned Underwater Vehicles control system Design Finite Element Modeling Free Body Diagram Vortex Shedding Friction Coefficient Hydrodynamic Analysis Drag Coefficient Computer Programs propulsion control system

来源：评论

学校读者我要写书评

暂无评论

Fli-Bi UAV: A Unique Surveying VTOL for Overhead Intelligence

Fli-Bi UAV: A Unique Surveying VTOL for Overhead Intelligenc...

引用

AIAA SciTech Forum

作者： Baube, Calvin Downs, Charlotte Goodstein, Maxwell Labrador, David Liebergall, Erik Molloy, Oren Embry Riddle Aeronaut Univ Mech Engn Daytona Beach FL 32114 USA

ISBN: (数字)9781624107115

ISBN: (纸本)9781624107115

Vertical takeoff and landing (VTOL) systems have expanded the applications of unmanned aerial vehicles significantly. Combining the deployability of a vertically capable multirotor with the efficiency and flight speed of a fixed wing is desirable for mapping and surveying. The customer required a VTOL to conduct large-scale magnetometer surveys in Canadian forests, also seen as locations that are inaccessible by foot. No platforms on the market currently meet their requirements, so a unique solution has been developed. Weight is a massively limiting factor for aerial vehicles. With a payload requirement of 2.2 pounds, the all-up weight of the vehicle was targeted to be 20 pounds. Lightweight PLA filament was used for the wings and empennage, reducing the weight by almost 50% compared to regular PLA. Key structural components, such as the twin booms and wing spars, are constructed from carbon for airframe rigidity. With an emphasis on propulsion redundancy, the Fli-Bi UAV has an X8 configuration, employing eight motors for full control in vertical and horizontal flight. This provides enough redundancy to maintain flight if there was a failure at any single point in the propulsion system. Each motor is angled relative to the ground to provide supplemental lift in horizontal flight and assist the transition between flight modes. This provides enough thrust and lift to meet the 60-knot speed requirement. By eliminating servo-actuated control surfaces, motors and electronic speed controllers are the only points of failure in the propulsion and control system. The number and configuration of motors makes this a viable solution to fix the customer's need for a redundant surveying VTOL. Many worst-case scenario assumptions were made when calculating payload capability, forward drag, and required thrust, which should pave the way for successful flight. There are multiple research opportunities available that this platform could be the basis for in the future.

关键词： Vertical Takeoff and Landing Beyond Visual Line of Sight Aircraft Configurations Multicopter control Surfaces propulsion system Magnetometers propulsion control system Aerodynamic Stability Autopilot

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：