论文(设计)基于层次结构的分布式MAS 作战防御体系17027.doc
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1、2004-5题录英译集*武器装备自动化 基于层次结构的分布式MAS作战防御体系罗天德1 2,孔莲芳2(1. 中国人民解放军75215部队 政治部;2. 华南理工大学,广东 广州 510640)摘要:根据军事作战系统属复杂系统的特点,建构了基于多层分布式MAS的作战防御体系及其框架。其体系结构分最高决策与指挥层Agent、中间处理与操作层Agent、底层(各Weapon Agent)三层。最高层判断战场总体态势,下达总体决策到中间层,监控底层。中间层分解总体决策并分配子任务(指令)给底层,反馈底层态势给最高层。各底层Agent接受上层指令,在指令指导下分析、决策并动作。关键词:防御体系;Agen
2、t;MAS;军事作战系统Distributed MAS Defense System Based on Hierarchy ArchitectureLUO Tian-de1 2, KONG Lian-fang2(1. Dept. of Polity, No.75215 PLA of China; 2. South China University of Technology, Guanzhou 510640, China)Abstract: The distributed MAS defense system based on hierarchy architecture was establ
3、ished according to the peculiarity that the military combat system belongs to complex system. This system architecture was divided into three layers: agent to super decision-making and command layer, agent to intermediate disposal and operation layer, agent to bottom layer (weapon agent). The super
4、layer estimates the situation of the battlefield as a whole, then make notice to the intermediate layer and supervise the bottom layer. The intermediate layer decomposes the holistic command, and assigns those submissions to weapon agent. The intermediate layer also delivers the feedback the situati
5、on that comes from bottom layer to the super layer. Each weapon agents accept to command of the bottom layer, and then analysis those commands, make a decision, at last take action independently or cooperate with the other weapon agents.Key words: Defense system; Agent; MAS; Military combat system*基
6、于神经网络专家系统的炮兵射击指挥系统故障诊断魏长流,敖士奇(中南大学 机电工程学院,湖南 长沙410083)摘要:基于神经网络专家系统的炮兵射击指挥系统故障诊断系统采用多层感知器组建专家知识库,建立激光仪子网、故障子模块,构建合成网络模块及训练样本。将各训练样本输入相应神经网络中训练,得到的权值和阈值存入数据文件。推理模块调用诊断知识库,输入各故障征兆,计算隐含层和输出层的神经元输出。解释模块据给定的法则判定输入神经元的输出是否有故障。关键词:专家系统;神经网络;故障诊断;炮兵射击指挥系统Fault Diagnosis for Artillery Firing Command System B
7、ased on NN Expert SystemWEI Chang-liu, AO Shi-qi(College of Electromechanical Engineering, Central South University, Changsa 410083, China)Abstract: Fault diagnosis system for artillery fire command system based on NN expert system consists of expert knowledge base formed with multi-layer perception
8、s, radar subnet, fault sub-module, integrated net-module and training samples. Each training sample was inputted into corresponding NN to train, gained weights and thresholds were stored into the data file. Reasoning module is used to call diagnosis knowledge base to input fault characters, and acco
9、unt the outputs of hidden layer and output layer. Explaining module is used to judge if the outputs of input neutral node have faults or not according to the rules.Key Words: Expert system; Nneural network; Fault diagnosis; Artillery firing command system*巡航导弹仿真应用中的地形匹配黄鎏鑫,齐欢(华中科技大学 系统工程研究所,湖北 武汉 43
10、0074)摘要:巡航导弹飞行模拟实时仿真系统以VC+ 为开发平台,VEGA视景仿真软件作仿真引擎,选用MultiGen Creator建立导弹实体仿真模型及场景地形模型库,同时将场景数据库地形数据转换成vrml格式供主控制模块调用地形匹配算法。仿真应用中,将地形表面三角离散化形成仿真场景模型,利用地形模型的高程数据,动态改变仿真循环中巡航导弹的方位、姿态等特征,模拟实现巡航导弹飞行过程中的地形匹配。关键词:虚拟仿真;地形匹配;场景数据库;巡航导弹;VRMLTerrain Matching in Cruise Missile Simulation SystemHUANG Liu-xin, QI
11、Huan(Institute of Systems Engineering, Huazhong University of Science & Technology, Wuhan 430074, China)Abstract: Virtual real-time simulation system for flight of cruise missile was developed with VC+. VEGA acts as emulation engine, entity simulation model of cruise missile and scene topographical
12、model base set up with MultiGen Creator. At one time, the topographical data in scene database was converted into vrml file to transfer terrain matching arithmetic for host control module. In simulation, triangles of topographical surfaces are dispersed to form the simulation scene model. The positi
13、on and posture characteristics of the cruising missile in simulation circulation was changed dynamically with the altitude data of topographical model, and the terrain matching simulation of flying process for the cruise missile was realized.Key words: Virtual simulation; Terrain matching; Scene dat
14、abase; Cruise missile; VRML*导弹虚拟操作训练系统中虚拟手的控制谢建华2,马立元1,张睿2(1. 南京理工大学 理学院,江苏 南京 210094;2. 军械工程学院 导弹工程系,河北 石家庄 050003)摘要:基于逆向运动学的操作训练系统虚拟手控制算法,根据手臂末端的位置与方向计算出各关节的角度值。先规定约束条件,得到相对于肘关节的腕关节局部坐标值。用Vega函数得到肘关节初始状态坐标值,测量腕部的空间位置。计算此时肘关节的位置,得到肩部关节点值。判断是否符合约束条件。最后导出手部碰撞检测及数据手套对虚拟手手指间关节夹角的控制方法。关键词:虚拟手;Vega;控制算法
15、;逆向运动学;碰撞检测;数据手套Control of Virtual Arm in Missile Virtual Operation SystemXIE Jian-hua2, MA Li-yuan1, ANANG Rui2(1. College of Science, Nanjing University of Science & Technology, Nanjing 210094, China; 2. Dept. of Missile Engineering, Ordnance Engineering College, Shijiazhuang 050003, China)Abstrac
16、t: According to the position and direction of the bottom of virtual arm, the angle value of every joint of virtual arm is calculated with control algorithm of virtual arm of operation system based on converse kinematics. First, regulated the restrictions, and got local coordinate value of wrist rela
17、tive to the position of joint of elbow. The coordinate value of original state for joint of elbow was computed with Vega function, space position of wrist part was measured. At one time, the position of elbow joint was computed, and gained value of joint node of shoulder, Judged if the positions are
18、 up to restriction condition. In the end, the control method for nip angle between fingers of virtual hand was educed through bump detection of hand and data glove.Key words: Virtual arm; Vega; Control algorithm; Converse kinematics; Bump detection; Data glove*飞机自动着陆控制系统中输入输出的反馈线性化冯江1,王晓燕2,赵书玲2(1. 江
19、西理工大学 信息工程学院,江西 赣州 341000;2. 江西理工大学 机电工程学院,江西 赣州 341000)摘要:飞机着陆自动跟踪控制系统,采用微分几何反馈线性化处理非线性方程输入输出反馈。由设置等效输入,将系统等效解耦为一阶、二阶线性子系统;经设置期望输出轨迹、定义系统跟踪误差、选择控制律,使全部跟踪状态保持有界,系统误差按指数规律收敛于零。仿真表明反馈线性化系统满足纵向着陆无误差要求,具有较强鲁棒性。关键词:反馈线性化;非线性;输入输出;自动着陆控制系统Feedback Linearization of Input/output in Airplane Automatic Landin
20、g Control SystemFeng Jiang1, Wang Xiaoyan2, Zhao Shuling2(1. College of Information Engineering, Jiangxi University of Science & Technology, Ganzhou 341000, China;2. College of Mechanical and Electronic Engineering, Jiangxi University of Science & Technology, Ganzhou 341000, China)Abstract: Input-ou
21、tput nonlinear equation was processed with feedback linearization of differential geometry in airplane automatic landing control system. The system was decoupled into 1 or 2 rank subsystem by setting the equivalent input. All the track statuses were kept in bound and error was converged to 0 accordi
22、ng to exponent rule by setting hope-output locus, defining track error of system and choosing control rule. The simulation shows that feedback linearization system can content 0 error requirement of lengthways automatic landing.Key words: Feedback linearization; Nonlinear; Input/output; Automatic la
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