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Design and Simulation of Controller for Hyper Velocity Kinetic Energy Missile 被引量:2
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作者 康长赓 雷成 刘藻珍 《Journal of Beijing Institute of Technology》 EI CAS 2000年第1期107-112,共6页
The controller design and digital simulation for the hyper velocity kinetic energy missile is investigated. A mathematical model of the trajectory deviation from the line of sight was established, the guidance closed ... The controller design and digital simulation for the hyper velocity kinetic energy missile is investigated. A mathematical model of the trajectory deviation from the line of sight was established, the guidance closed loop was compensated with a phase advance lag corrective network, a selecting algorithm of the attitude control motors used to steer the missile's attitude was presented. In the presence of a wide variety of disturbances the results of digital simulation are satisfactory to circular error probability(CEP) being less than 0 5?m. The steering scheme utilizing attitude control motors as actuators to control the attitude of the missile is feasible. 展开更多
关键词 hyper velocity missile guidance missile control attitude control motor simulation
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Missile flight simulation and attitude display
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作者 刘莉 李祖博 +1 位作者 王欢 陆真 《Journal of Measurement Science and Instrumentation》 CAS 2014年第4期5-9,共5页
Simulation has become an important method for missile flight research to reduce cost and improve accuracy. This paper concerns missile flight trajectory and attitude calculation. As a result, mechanical analysis and m... Simulation has become an important method for missile flight research to reduce cost and improve accuracy. This paper concerns missile flight trajectory and attitude calculation. As a result, mechanical analysis and modeling are done, the characteristics of missile flight decoding algorithm and attitude parameters are analyzed, the missile trajectory is dynamically simulated in a vertical plane and the missile attitude is real-time displayed. The description of missile flight process in a labo- ratory has provided a basis for actual missile flight. 展开更多
关键词 missile flight simulation ATTITUDE
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An operation optimization method of a fully mechanized coal mining face based on semi-physical virtual simulation 被引量:8
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作者 Hengbo Shi Jiacheng Xie +2 位作者 Xuewen Wang Juanli Li Xing Ge 《International Journal of Coal Science & Technology》 EI 2020年第1期147-163,共17页
A mathematical hydraulic support self-tracking model for three-machine cooperative mining is proposed to address low efficiency and difficulties in strategy evaluation of a fully mechanized coal face.The proposed mode... A mathematical hydraulic support self-tracking model for three-machine cooperative mining is proposed to address low efficiency and difficulties in strategy evaluation of a fully mechanized coal face.The proposed model uses the coordinates and traction speed of the shearer to calculate the frequency of the circular hydraulic support and realize the coordinated operation of the three-machine mining technology.A unity3d hardware-in-the-loop simulation experimental hearer and hydraulic support platform was used to validate the model of autonomous follow-up.The results indicate that collaborative control of coal mining allowed for an efficiency 3.76%higher than under automatic operation mode and 46.03%higher than under manual control;thus,The mathematical model provided an improved production efficiency of the fully mechanized mining face.The mathematical model also provides a more intelligent and reliable security support,and improves the intelligent level of hydraulic support follow-up control. 展开更多
关键词 semi-physical simulation Virtual reality UNITY3D Human-computer interaction Shearer traction speed
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Improved S Surface Controller and Semi-physical Simulation for AUV 被引量:2
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作者 吕翀 庞永杰 +1 位作者 李晔 张磊 《Journal of Marine Science and Application》 2010年第3期301-306,共6页
S surface controllers have been proven to provide effective motion control for an autonomous underwater vehicle (AUV).However, it is difficult to adjust their control parameters manually.Choosing the optimum parameter... S surface controllers have been proven to provide effective motion control for an autonomous underwater vehicle (AUV).However, it is difficult to adjust their control parameters manually.Choosing the optimum parameters for the controller of a particular AUV is a significant challenge.To automate the process, a modified particle swarm optimization (MPSO) algorithm was proposed.It was based on immune theory, and used a nonlinear regression strategy for inertia weight to optimize AUV control parameters.A semi-physical simulation system for the AUV was developed as a platform to verify the proposed control method, and its structure was considered.The simulation results indicated that the semi-physical simulation platform was helpful, the optimization algorithm has good local and global searching abilities, and the method can be reliably used for an AUV. 展开更多
关键词 S surface controller AUV MPSO semi-physical simulation
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Trajectory design and simulation in injection phase for hyper-velocity kinetic energy missile 被引量:1
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作者 于剑桥 梅跃松 韩朝 《Journal of Beijing Institute of Technology》 EI CAS 2011年第1期18-22,共5页
A movement law of laser beam facula is designed for the injection trajectory of hyper-ve- locity kinetic energy missile to eliminate the influence of motor exhaust smoke on laser signal trans mission. Taking guidance... A movement law of laser beam facula is designed for the injection trajectory of hyper-ve- locity kinetic energy missile to eliminate the influence of motor exhaust smoke on laser signal trans mission. Taking guidance loop of hyper velocity kinetic energy missile as plant, a closed loop control system with desired step response characteristics is constructed and the movement law of laser beam facula for the missile injection trajectory is designed based on the output signal of the closed loop controller under a step input. Six degree of freedom trajectory simulations show that by the guidance of the laser beam facula moving with designed law, the missile can finish transition from the initial trajectory to a stable tracking trajectory without overshoot within the required time. 展开更多
关键词 trajectory design trajectory simulation missile control hyper velocity kinetic energymissile
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Semi-physical simulation of AUV pipeline tracking 被引量:1
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作者 李晔 庞永杰 +1 位作者 张磊 张鸿皓 《Journal of Central South University》 SCIE EI CAS 2012年第9期2468-2476,共9页
Before the task of autonomous underwater vehicle(AUV) was implemented actually,its semi-physical simulation system of pipeline tracking had been designed.This semi-physical simulation system was used to test the softw... Before the task of autonomous underwater vehicle(AUV) was implemented actually,its semi-physical simulation system of pipeline tracking had been designed.This semi-physical simulation system was used to test the software logic,hardware architecture,data interface and reliability of the control system.To implement this system,the whole system plan,including interface computer and the methods of pipeline tracking,was described.Compared to numerical simulation,the semi-physical simulation was used to test the real software and hardware more veritably.In the semi-physical simulation system,tracking experiments of both straight lines and polygonal lines were carried out,considering the influence of ocean current and the situation of buried pipeline.The experimental results indicate that the AUV can do pipeline tracking task,when angles of pipeline are 15°,30°,45° and 60°.In the ocean current of 2 knots,AUV could track buried pipeline. 展开更多
关键词 autonomous underwater vehicle semi-physical simulation underwater pipeline tracking underwater sensor simulation underwater optical vision
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Simulation of Control and Guidance System for the Spinning Missile
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作者 Meng Daikui (China Changfeng System Engineering Corporation, P.O.Box 142-30, Beiging 100854, China) 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 1994年第3期49-56,共8页
Adopted for some small-size short range surface-to-air missiles and antitank guided missiles is a single-channel control method of making missile rotating around its longitudinal axis. In hardware-in-the-loop simulati... Adopted for some small-size short range surface-to-air missiles and antitank guided missiles is a single-channel control method of making missile rotating around its longitudinal axis. In hardware-in-the-loop simulations of the guidance and control system for these kinds of spinning missiles, improper use of special simulation equipment and test method will cause significant errors, even lead to failure of the simulation. In this article, the author gives an analysis of the causes of significant errors and failure of the simulation, and puts forward a solution, which is improved workable in making the hardward-in-the-loop simulation successful. 展开更多
关键词 Computer simulation Error analysis Computer system recovery missiles
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Modeling and Simulation for Gliding Missile with Large Aspect Ratio
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作者 杨黔龙 周凤岐 《Defence Technology(防务技术)》 CAS 2012年第2期92-97,共6页
An improved STT (skid to turn) autopilot was developed to solve the problem of roll control saturation for the gliding missile with large aspect ratio. A lateral acceleration feedback was introduced in the roll channe... An improved STT (skid to turn) autopilot was developed to solve the problem of roll control saturation for the gliding missile with large aspect ratio. A lateral acceleration feedback was introduced in the roll channel of the autopilot to ensure that the roll angle could closely follow the lateral acceleration,so that the sideslip angle and the roll rudder deflection could be reduced,and the roll control saturation was avoided. A six-DOF ( degree of freedom) nonlinear simulation model was set up. The simulation results indicate that the model and the control scheme are effective. 展开更多
关键词 control and navigation technology of aircraft six-DOF simulation gliding missile aspect ratio STT
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Ballistic Model and Simulation of a Light Anti-tank Missile Replication Hitting on Top of Tank at Terminal Trajectory
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作者 宋振铎 徐文旭 刁青 《Defence Technology(防务技术)》 SCIE EI CAS 2006年第3期184-190,共7页
关键词 导弹 数字模拟 弹道 脉冲控制
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Design and Implementation of One Missile Visual Simulation System Based on OpenGL
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作者 高颖 张普照 +1 位作者 彭宇馨 黄建国 《Defence Technology(防务技术)》 SCIE EI CAS 2007年第3期226-229,共4页
The implementation of a missile's visual simulation system is explained that is developed with OpenGL(open graphic library) and the flight path and flight carriage in different stages of the missile are displayed.... The implementation of a missile's visual simulation system is explained that is developed with OpenGL(open graphic library) and the flight path and flight carriage in different stages of the missile are displayed. The establishment problems of the 3D scene are circumstantiated including the construction and redeployment of the model, creation of the virtual scene, setting of the multi-viewports and multi-windows etc. The missile's data driver, system flow, the modules and their mutual relations of the missile visual simulation system are discussed. The missile flight simulation results and effect of the scenes are given. 展开更多
关键词 计算机应用 可视化 导弹 图像模拟
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Dynamic Simulation for Missile Erection System
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作者 姚晓光 郭晓松 +1 位作者 冯永保 高钦和 《Defence Technology(防务技术)》 SCIE EI CAS 2007年第4期262-267,共6页
In order to study the dynamic characteristics of the missile erection system,it can be considered as a rigid-flexible coupling multi-body system.Firstly,the actual system is abstracted as an equal and simplified one a... In order to study the dynamic characteristics of the missile erection system,it can be considered as a rigid-flexible coupling multi-body system.Firstly,the actual system is abstracted as an equal and simplified one and then the forces applied to it are analyzed.Secondly,the rigid-flexible coupling dynamic simulation for erection system is accomplished by use of the system simulation software,for example Pro/E,ADAMS,ANSYS,MATLAB/Simulink,etc.Finally,having the aid of simulation results,the kinetic and dynamic characteristics of the flexible bodies in erection system are analyzed.The simulation considering the erection system as a rigid-flexible coupling system can provide valuable results to the research of its kinetic,dynamic and vibrational characteristics. 展开更多
关键词 力学 导弹直立系统 刚柔耦合 系统模拟
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Cross Spectral Estimation and Its Application in Missile Systems 被引量:1
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作者 魏华梁 刘藻珍 张天桥 《Journal of Beijing Institute of Technology》 EI CAS 1996年第1期80-84,共5页
A new method based on cross-spectrum estimation for the verification and validation of computer simulation models is expounded in accordance with the characteristics of missile systems. The new method can expose the d... A new method based on cross-spectrum estimation for the verification and validation of computer simulation models is expounded in accordance with the characteristics of missile systems. The new method can expose the differences between two time processes in several aspects and can also give quantitative analysis results about the statistical consistence between them. An application to an actual anti-tank missile system simulation is presented and the calculated results confirm the effectiveness of the method. The approach can also be employed to verify the simulation models of other dynamic systems. 展开更多
关键词 guided missile system simulation model verification cross-spectrum estimation
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Studies on aeroservoelasticity semi-physical simulation test for missiles 被引量:15
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作者 WU ZhiGang CHU LongFei +2 位作者 YUAN RuiZhi YANG Chao TANG ChangHong 《Science China(Technological Sciences)》 SCIE EI CAS 2012年第9期2482-2488,共7页
Missiles may be damaged when aeroservoelastic problem occurs,which is caused by the interaction of structure flexibility and flight control system.Because of the limit of wind tunnel test condition,numerical methods a... Missiles may be damaged when aeroservoelastic problem occurs,which is caused by the interaction of structure flexibility and flight control system.Because of the limit of wind tunnel test condition,numerical methods are mostly used in previous aeroservoelastic studies.However,series of assumptions and simplification on structures,aerodynamics and flight control systems are unavoidably introduced,and various nonlinear factors are also ignored,therefore,they result in considerable errors.A novel method called aeroservoelasticity semi-physical simulation test is proposed in this paper,which takes the flexible missile with control system as the test object.Vibration signals at several locations of the missile are measured by accelerometers,then corresponding unsteady aerodynamics is computed based on the fact that airflow at high Mach is nearly quasi-steady,and finally unsteady aerodynamics is exerted simultaneously by shakers at certain locations of the missile.The aeroservoelasticity semi-physical simulation test system can be constructed after the control system is closed.Open loop transfer function test and closed loop stability test are carried out in sequence.The test principle and method proposed in this paper are verified by the concordance between the results of numerical simulation and experiment. 展开更多
关键词 aeroservoelasticity semi-physical simulation unsteady aerodynamic aerodynamic derivative method SHAKER missile
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A METHOD IN SYSTEM DESIGN OF EJECTING DEVICES OF MISSILES 被引量:8
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作者 DaiLongcheng XuanYimin 《Transactions of Nanjing University of Aeronautics and Astronautics》 EI 2002年第1期44-52,共9页
Anew method in system design of ejecting devices of missiles is first presented.Some important points are dis-cussed,which guid the research and development of new ejecting devices of missileg,amd provid the foundatio... Anew method in system design of ejecting devices of missiles is first presented.Some important points are dis-cussed,which guid the research and development of new ejecting devices of missileg,amd provid the foundation flr thw design of mew ejecting device is provided.The system design includes the distribution of techmology specifica-tion,3-D solid modeling of ejecting devices of missiles im-ported from abroad,the design of pmeumatic device sys-tem,the design of ejecting mechanism system,the predic-tion of reliability and the experimental analysis,etc. 展开更多
关键词 WORDS ejecting DEVICES of missile system design dynamic simulation WAVELET optimization 导弹 发射装置 总体设计 动态仿真 小波优化
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A Calculation Method of Rolling Characteristics of Canard Missile with Free-Spinning Tails 被引量:1
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作者 Ping’an Liu Mingyuan Liu 《Journal of Harbin Institute of Technology(New Series)》 EI CAS 2019年第6期62-68,共7页
The steady flow field of a canard missile on different angles of attack and Mach numbers were studied. Based on analysis, a method was proposed to reduce the calculation for the rolling characteristics of the canard m... The steady flow field of a canard missile on different angles of attack and Mach numbers were studied. Based on analysis, a method was proposed to reduce the calculation for the rolling characteristics of the canard missile with free-spinning tails, and was tested to obtain the relations between rolling moment coefficient, Mach number, and angle of attack. All the computed rolling moment coefficients obtained from the proposed method greatly agreed with the experimental results of FD-06 wind tunnel in CAAA, which proved that the method can not only reduce the calculation cost but also keep precision in calculating the rolling characteristics of canard missiles. 展开更多
关键词 numerical simulation canard missile free-spinning tail wind tunnel test rolling characteristics
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Research on the Hardware-in-the-loop Simulation of Guidance System
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作者 Shan, Jiayuan Li, Zhongwu 《Journal of Systems Engineering and Electronics》 SCIE EI CSCD 1994年第3期41-48,共8页
In this paper, the composition of the hardware-in-the-loop simulation system of missile guidance system and the characteristic and function of every equipment in this simulation system are discussed. Then the principl... In this paper, the composition of the hardware-in-the-loop simulation system of missile guidance system and the characteristic and function of every equipment in this simulation system are discussed. Then the principle of this system is discussed in terms of theory, and the resemblance of prototype system with simulation system is analyzed. Also, many key problems such as equipment interface, equipment installation, modelling and software design are dealt with. At the end, the error source of simulation system is analyzed, and a strong base is built for the study of simulation system precision. 展开更多
关键词 ANIMATION Computer simulation Computer software Data acquisition Error analysis INSTALLATION Interfaces (computer) missiles
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Trajectory optimization of a deflectable nose missile
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作者 Zhi-yong Zhang Qi-zhong Tang +1 位作者 Xiao-hui Sun Zhi-hua Chen 《Defence Technology(防务技术)》 SCIE EI CAS CSCD 2017年第3期158-163,共6页
The deflectable nose missile has a longer range by deflecting its nose to improve its aerodynamic feature.Based on detached eddy simulation(DES), the supersonic flow fields of a missile with deflectable nose are simul... The deflectable nose missile has a longer range by deflecting its nose to improve its aerodynamic feature.Based on detached eddy simulation(DES), the supersonic flow fields of a missile with deflectable nose are simulated numerically and its aerodynamic force coefficients are calculated under the condition of the deflection angles vary from 0° to 8°, angles of attack, 0°-8°, and mach numbers, 2 to 5. Coupling these aerodynamic coefficients with the plumb plane ballistic equations, the extended flight range has been calculated. Furthermore, the genetic algorithm(GA) is employed for the solution of maximum range of the deflected missile. 展开更多
关键词 偏转角度 导弹 弹道优化 弹头 流场数值模拟 最大射程 动力学特征 气动力系数
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Aeroheating CFD analysis of missile slots
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作者 Kai Yang Xiaowei Gao 《Theoretical & Applied Mechanics Letters》 2012年第1期59-61,共3页
This paper develops a hypersonic aerothermal simulation method for missile slot flow. The finite volume method of structure grid solver is developed for solving Euler and Navier-Stokes equations. The solver includes P... This paper develops a hypersonic aerothermal simulation method for missile slot flow. The finite volume method of structure grid solver is developed for solving Euler and Navier-Stokes equations. The solver includes Park's two temperature model and the air multi-species reaction model. The second-order accuracy TVD numerical method was deduced to compute the hypersonic aeroheating which improves the computational efficiency. Computational results are given to show the high accuracy comparing to the existing experimental data. 展开更多
关键词 missile slot aeroheating environment numerical simulation
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China's HN-5A Air Defense Missile System
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作者 Zeng Qingbin 《Aerospace China》 1993年第1期29-32,共4页
This paper describes the HN-5Aman-portable air defense missilesystem which contains the HN-5Aweapon,test equipment and train-ing simulator.Compared with simi-lar missiles,it has more powerfulwarhead,its seeker reticle... This paper describes the HN-5Aman-portable air defense missilesystem which contains the HN-5Aweapon,test equipment and train-ing simulator.Compared with simi-lar missiles,it has more powerfulwarhead,its seeker reticle is coatedwith optical filter film,and its de-tector is equipped with cooling de-vices.Moreover,the paper alsopoints out the trends of the im-provement and development of HN-5A system. 展开更多
关键词 PORTABLE missile DEFENSE simulATOR TRAIN instrument ENGAGE fitted aiming instead
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基于Simulink和C/C++混合编程的战术导弹稳定控制系统仿真 被引量:9
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作者 董锡君 罗志军 洪兴昌 《系统仿真学报》 CAS CSCD 2002年第9期1229-1231,共3页
在战术导弹稳定控制系统的仿真研究中,为了方便数学模型的建立,利用已有的程序资源,提高编程的效率,本文通过利用Simulink和C/C++混合编程技术完成仿真系统的建立,这样可以充分融合Simulink和C/C++语言各自的优点和长处,实现高度可视化... 在战术导弹稳定控制系统的仿真研究中,为了方便数学模型的建立,利用已有的程序资源,提高编程的效率,本文通过利用Simulink和C/C++混合编程技术完成仿真系统的建立,这样可以充分融合Simulink和C/C++语言各自的优点和长处,实现高度可视化和高运行效率的全数字仿真试验。该方法不但适用于系统的全数字仿真,而且通过增加适当的配套软件和硬件,可以推广至战术导弹稳定控制系统的半实物仿真试验,有着良好的工程实用价值和推广意义。 展开更多
关键词 simulINK 混合编程 战术导弹 稳定控制系统 仿真 C语言 C++语言
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