第9章 DWRR应用分析
麦塔分析报告
麦塔分析报告1. 简介麦塔（Meta）是一种数据分析工具，通过对用户的行为数据进行统计和分析，帮助企业深入了解用户行为和需求。
本报告将介绍麦塔的功能和使用方法，并提供一些常用的数据分析指标和技巧。
2. 功能和使用方法2.1 数据采集与导入麦塔支持多种数据导入方式，包括手动导入、API导入和批量导入。
用户可以按照自己的需求选择最适合的导入方式，并将数据导入到麦塔的数据仓库中。
2.2 数据清洗与处理在数据导入完成后，麦塔提供了一系列数据清洗和处理的功能，用于清理和转换原始数据。
用户可以通过简单的配置和操作，将原始数据清洗成符合分析要求的格式。
2.3 数据分析与可视化麦塔提供了丰富的数据分析和可视化工具，用户可以根据自己的需求选择相应的分析方法，并生成直观的图表和报告。
麦塔支持常见的数据分析方法，包括趋势分析、关联分析、聚类分析等。
2.4 指标计算与分析除了提供常用的数据分析方法外，麦塔还支持用户自定义指标的计算和分析。
用户可以根据自己的业务需求，定义自己所关注的指标，并进行相应的计算和分析。
3. 常用数据分析指标和技巧3.1 用户活跃度用户活跃度是衡量用户参与程度的重要指标，通常使用以下指标进行分析：•日活跃用户数（DAU）：统计每天的活跃用户数量。
•月活跃用户数（MAU）：统计每月的活跃用户数量。
•用户留存率：衡量用户的粘性，统计在某一时间段内留存的用户比例。
3.2 用户行为路径分析用户行为路径分析可以帮助企业了解用户在产品中的行为轨迹和习惯，常用的方法有：•转化漏斗分析：通过分析用户在不同阶段的转化率，找出转化率低的环节并优化。
•流量分析：统计用户的来源和去向，帮助企业优化营销策略和用户引流。
•页面分析：分析用户在不同页面的停留时间和转化率，优化页面设计和内容布局。
3.3 用户行为关联分析用户行为关联分析可以帮助企业了解用户的偏好和需求，常用的方法有：•协同过滤推荐：通过分析用户的行为数据，预测用户可能感兴趣的商品或内容。
DWR技术总结
DWR技术总结目录1DWR入门 (3)1.1DWR(Direct Web Remoting)概述 (3)1.2DWR使用入门 (3)2web.xml的配置 (7)3dwr.xml的配置 (8)3.1创建dwr.xml文件 (8)3.2<init>标签 (8)3.3<allow>标签 (8)3.3.1Creators构造器 (9)3.3.2Converters转换器 (10)3.3.3Filters过滤器 (11)3.4<signatures>标签 (12)4engine.js功能 (12)5util.js功能 (13)6DWR中的javascript (13)6.1DWR的远程调用——使用回调函数处理Ajax的异步特性 (13)6.2创建一个与Java对象相匹配的JavaScript对象 (14)1DWR入门1.1DWR(Direct Web Remoting)概述DWR是一种AJAX(Asynchronous JavaScript and XML)的JAVA实现，是一个能够使运行在服务器上java和运行在浏览器中的JavaScript交互，并能简单的相互调用的Java库。
官方网站：最新版本：3.0.rc2稳定版本：2.0.7DWR包括两个主要部分：*运行在服务器上的Java Servlet，用以处理请求和向浏览器发回响应。
*运行在浏览器上的JavaScript，用以发送请求，并可以动态的更新网页。
DWR的工作原理是动态生成基于Java类的JavaScript。
生成的代码具有ajax 功能，使效果看起来就好像在浏览器上执行的一样，实际上是，代码调用发生在服务器端，DWR负责数据的传递和转换。
这种从java到javascript的运程调用功能的方式使DWR用起来有种非常像RMI或者SOAP的常规RPC机制，而且DWR 的优点在于不需要任何的网页浏览器插件就能够运行在网页上。
RWF动作要素分析
很短的 短 的 中等程度 长 的 很长的
0～10 10～25 25～50 50～75 75～100
2.抓起动作(Gr)
抓起是指手伸向物体后，从手指开始展开时刻起，一 直到确实握住目的物体的时点为止的动作。 （1）抓起动作分四种：简单抓起、技巧性的抓起、复 杂抓起、特殊抓起。 （2）抓起动作的预定时间标准如表9-15所示。
RWF时间表上的时间单位：Ru(Ready Time Unit)。
1Ru=0.001分钟=0.06秒
RWF的标准要素
所有的操作 都是由标准 要素组合而 成。 标准要素 WF记号 1、移动（到达、搬运）———————R、M 2、抓 ———————————————Gr 3、放 ———————————————Rl 4、前置 ——————————————PP 5、组立 ——————————————Asy 6、使用 ——————————————Use 7、分解 ——————————————Dsy 8、精神作用(检查等) ————————MP
（3）抓起动作分析表达式为：动作难度数——可见性 符号——增额条件符号。
表9-15 抓起的预定时间标准 （动作难度）分类 简单抓取 O l 很容易 容 易 指尖抓取 卷绕抓取 2 一般 3 4 困难 很困难
技巧抓取
主要尺寸/m m 复 杂 抓 取 直 厚 可见性区分 可 见 不可见 代 号 V B 径/m m 度/m m
表9-26 步行与身体方向变换的预定时间标准
步 行 1步=750mm 普通步行 困难步行
步行开始之前/之 后身体回转120° 以下 12+8×步数 12+10×步数
步行开始之前/之 后身体回转 120°以上 22+8×步数 22+10×步数
DWR详解
DWR（Direct Web Remoting）是一个开源的类库,可以帮助开发人员开发包含AJAX技术的网站.它可以允许在浏览器里的代码使用运行在WEB服务器上的JA V A函数,就像它就在浏览器里一样.它包含两个主要的部分:允许JavaScript从WEB服务器上一个遵循了AJAX原则的Servlet(小应用程序)中获取数据.另外一方面一个JavaScript库可以帮助网站开发人员轻松地利用获取的数据来动态改变网页的内容.DWR采取了一个类似AJAX的新方法来动态生成基于JA V A类的JavaScript代码.这样WEB 开发人员就可以在JavaScript里使用Java代码就像它们是浏览器的本地代码(客户端代码)一样;但是Java代码运行在WEB服务器端而且可以自由访问WEB 服务器的资源.出于安全的理由,WEB开发者必须适当地配置哪些Java类可以安全的被外部使用.这个从JA V A到JavaScript的远程功能方法给DWR的用户带来非常像传统的RPC机制,就像RMI或者SOAP一样,而且拥有运行在WEB上但是不需要浏览器插件的好处.DWR不认为浏览器/WEB服务器协议是重要的,而更乐于保证编程界面的简单自然.对此最大的挑战就是把AJAX的异步特性和正常JA V A方法调用的同步特性相结合.在异步模式下,结果数据在开始调用之后的一段时间之后才可以被异步访问获取到.DWR允许WEB开发人员传递一个回调函数,来异步处理Java函数调用过程.其配置如下:1.1、dwr.xml的配置<dwr><allow><create creator="new" javascript="testClass" ><param name="class" value="com.dwr.TestClass" /><include method="testMethod1"/></create></allow></dwr><allow>标签中包括可以暴露给javascript访问的东西。
08 AJAX框架应用入门-DWR
果输入正确则显示一个正确的小图标。
8
DWR学习示例
导入类库包和log4j.properties ：
DWR使用Log4j作为日志记录工具， log4j.properties是log4j的 标准配置文件，将配置文件拷 贝到工程的src目录中。
将dwr和log4j目录中的所有jar文 件拷贝到WEB工程的WEBINF/lib目录，dwr.jar是DWR的 Java类库，其它的jar文件是 log4j的类库和依赖类库。
23
DWR学习示例
<script type="text/javascript" language="JavaScript"> // 测试用户输入的登录名是否存在 function testUserName(){ var name = DWRUtil.getValue("userName"); if(name.length == 0){ $("userNameResult").innerHTML = "<font color='red'>请填写用户名</font>"; return; } TestUserName.test(name, setUserNameResult); } // 将测试结果显示到页面中 function setUserNameResult(data){ if(data){ $("userNameResult").innerHTML = "<img src='images/ok.gif' />"; }else{ $("userNameResult").innerHTML = "<font color='red'>该用户名未注册</font>"; } } </script>
Rwf资料下载(doc50)
The ReadyWork-factor Munual目录第1部序论第1章Ready Work Factor 法概要 (3)第2章Work Factor 的标准要素 (11)第2部[拿取] 与[放置]第3章移动 (17)第4章抓取 (37)第5章放 (55)第6章预置 (59)第7章[拿取] 与[放] (67)第3部组装、使用、分解第8章组装 (73)第9章使用 (101)第10章分解 (103)第4部其它第11章精神作用 (111)第12章全身运动 (121)第13章特殊运动 (127)(1) 圆周运动(2) 笔记(3) 打锤子(4) 反复动作第5部Ready Work Factor 分析实例第14章Ready Work Factor 分析 (135)第1部序论第一章Ready Work Factor 法概要ⅠWork Factor 法历史ⅡReady Work Factor 法ⅢReady Work Factor 法特征ⅣWork Factor 时间第二章Work Factor 标准要素第1章Ready Work Factor 法概要1 Work Factor 法的历史以前，标准时间的设定是以以往的实际的实际记录，估量值，秒表测量结果等实际时间为基础进行的。
之后又出现了根据观测者的判断来对作业时间实测值进行标准化的方法。
秒表测量法引入后一种方法后，在将实测时间换算为许可时间方面有了非常大的改善，但是由于此种方法还是以人的主观判断为基础的，所以在精度和稳定性上还有很大的不足。
而且，工场或事务所一定要在实际工作进行之后方能设定出标准时间。
一般被人所熟知的是，A.B.Segur（西格）在19世纪20年代开始以预定的每一要素动作的时间值为基础，设定标准时间值，从科学的角度来对待作业时间测试问题。
根据他的研究可知，动作所需时间是受移动距离以及所用身体部位等因素影响的。
1934年Joseph.H.Quick（奎克）领导的生产工学小组的研究成果就是现在被称为Work Fac tor法的统计方法。
gwr模型用法-概述说明以及解释
gwr模型用法-概述说明以及解释1.引言1.1 概述概述部分的内容可以参考如下：引言是一篇文章的开端，用于引起读者的兴趣并提供背景信息。
在本文中，我们将探讨GWR模型的用法。
GWR模型（Geographically Weighted Regression，地理加权回归模型）是一种空间统计模型，用于研究地理空间数据的非均质性和异质性。
GWR模型是基于回归分析的方法，它考虑了数据的空间相关性和异变性，从而提供了更加准确的模型拟合和预测能力。
传统的全局回归模型假设数据的统计关系在整个地理空间范围内是稳定不变的，这忽略了地理空间上异质性的存在。
GWR模型通过引入地理加权矩阵，将回归模型的参数与空间位置相关联。
这意味着模型的每个位置都可以有不同的参数值，因此能够更好地捕捉地理空间上的变化。
这种地理加权的方式使得GWR模型在处理非均质性数据时比传统模型更为有效。
本文将首先介绍GWR模型的基本原理和假设，然后探讨其应用场景。
我们将重点讨论GWR模型在城市规划、交通规划、环境科学等领域的应用，并展示其在实际研究中取得的成果。
最后，我们将总结GWR模型的优点和局限性，并展望其未来的发展方向。
通过本文的阐述，读者将能够了解GWR模型的基本概念和原理，并对其在实际应用中的潜力有一定的了解。
无论是从学术研究的角度还是实际问题的解决，GWR模型都具有重要的意义和应用价值。
让我们一起深入探索GWR模型的奥秘吧！1.2文章结构文章结构部分主要介绍了本文的组织结构和各个章节的内容安排。
本文按照以下结构进行组织：第一部分是引言，包括概述、文章结构以及目的。
在概述部分，将简要介绍GWR模型的概念和应用背景，引起读者对该模型的兴趣。
在文章结构部分，将说明本文的整体组织结构，包括引言、正文和结论部分。
在目的部分，将明确本文撰写的目的和意义。
第二部分是正文，主要包括GWR模型介绍和GWR模型的应用场景。
在GWR模型介绍部分，将详细解释GWR模型的概念、原理和算法，并介绍该模型在地理空间分析中的应用。
DWR介绍
DWR介绍⏹简介DWR(Direct Web Remoting)是一个可以允许你去创建AJAX WEB 站点的JAVA开源库。
它可以让你在浏览器中的Javascript代码调用Web服务器上的Java代码，就像在Java代码就在浏览器中一样。
DWR包含2个主要部分：● 一个运行在服务器端的Java Servlet，它处理请求并且向浏览器发回响应。
● 运行在浏览器端的JavaScript，它发送请求而且还能动态更新网页。
DWR工作原理是通过动态把Java类生成为Javascript。
它的代码就像Ajax魔法一样，你感觉调用就像发生在浏览器端，但是实际上代码调用发生在服务器端，DWR负责数据的传递和转换。
这种从Java到JavaScript的远程调用功能的方式使DWR用起来有种非常像RMI或者SOAP的常规RPC机制，而且DWR的优点在于不需要任何的网页浏览器插件就能运行在网页上。
Java从根本上讲是同步机制，然而AJAX却是异步的。
所以你调用远程方法时，当数据已经从网络上返回的时候，你要提供有反调（callback）功能的DWR。
Dwr还提供了反转的ajax技术。
第一个DWR程序1.从DWR官网下载dwr.jar。
放到WEB-INF/lib目录下。
2.在WEB-INF目录下的web.xml文件中配置dwr的核心DwrServletweb.xml<?xml version="1.0" encoding="UTF-8"?><web-appversion="2.5"xmlns="/xml/ns/javae" xmlns:xsi="/2001/XMLSchema-instanc" xsi:schemaLocation="/xml/ns/javaee /xml/ns/javaee/web-app_2_5.xsd"><servlet><servlet-name>dwr-invoker</servlet-name><servlet-class>org.directwebremoting.servlet.DwrServlet </servlet-class><init-param><param-name>debug</param-name><param-value>true</param-value></init-param><load-on-startup>1</load-on-startup></servlet><servlet-mapping><servlet-name>dwr-invoker</servlet-name><url-pattern>/dwr/*</url-pattern></servlet-mapping></web-app>3.编写java服务端程序HelloWorld.javapackage com.bean;public class HelloWorld {public String sayHello(String str) {return "hello" + str;}}4.在WEB-INF下新建dwr.xml并引入其dtd文件。
YES2 inherently-safe tethered re-entry mission and contingencies
IAC-03-IAA.6.2.02YES2 inherently-safe tethered re-entry mission and contingenciesM. Kruijff, E.J. v.d. Heide, S. Calzada Gil Delta-Utec SRC, Leiden, Holland, , Abstract This paper discusses the tethered re-entry mission of the 2nd Young Engineers Satellite with a particular focus on the approach to mission planning, safety, risks and contingency. As an introduction, the major safety aspects and lessons learned from YES1 are discussed. YES2 aims at a tethered sample return demonstration using an inherently-safe inflatable capsule, possibly landing in Europe. It is completely student built. The paper provides a summary overview of and references for the evaluations behind design choices such as the selection of landing site, deployment scheme, optimisation of the cut time, mission timeline and contingency planning. The system hardware and control algorithms are driven by a minimalist design for simplicity and reliability. In addition, it discusses and quantifies the approach to safety issues such as meteoroid cutting risk, deployment failure scenarios, tether contingency lifetime and atmospheric entry/ground impact risks. 1. Two inherently-safe YES satellites In May 2002 the European Space Agency kickedoff a hands-on educational project called Young Engineers Satellite 2, managed by Delta-Utec in Leiden, Holland [1,2]. The YES2 is building on the experience and success of YES & TEAMSAT, launched on Ariane 502 in 1997 [3]. This first YES, a 200 kg satellite built in only 6 months, had the objective to deorbit a dummy mass from GTO by a 3 km rotating tether. A late change in nominal Ariane orbit increased the risk of accidental collision with other satellites to a non-negligible level, it was decided to not deploy the tether. Many experiments on TEAMSAT & YES were performed successfully (GPS, radiation sensors, cameras, commercial technology, sunsensors), but some important systems ran into problems. After the flight, a careful analysis was made of potential design flaws and the events that led to them, revealing three major causes[3]: 1. 2. 3. Human interaction under pressure Off-nominal satellite orbit & attitude, System complexity, providing on one hand useful redundancy, but also additional failure modes. There are significant differences between the two projects: YES1 was built in an intense effort, by a small group of co-located youngster working (nearly) full-time. For the YES2 project the students are working within the university curriculum, the focus is generally less intense. The project lasts longer too, so students will have to transfer tasks to a new generation from time to time. However there are more students involved and there is more time available, so more time and effort can be spent on careful analysis and testing. For YES2, students from all over Europe and Canada are now building a satellite with the objective to demonstrate two attractive new technologies: · A 30 km long, 0.5 mm, 5 kg Tether · An Inherently-safe Re-entry capsule, AIR Late 2006 YES2 is to be launched on Foton-M3, a Russian carrier. The 30 km of tether will be deployed from the carrier. At the other end, the AIR capsule is located. There is no conventional de-orbit burn: it is the tether that will accurately swing the capsule towards the Earth. The two technologies serve to demonstrate the SpaceMail application: a frequent sample return capability for the International Space Station9. Here, quick access and delivery to the customer is of importance. Conventional re-entry capsules are however landing in remote areas for reasons of safety. The concept behind YES2 is, if all goes to plan, the capsule will land so softly that it does not pose any risk to the population. We are designing AIR light and slow enough to land in mainland Europe (primary focus Sweden 60-63 degrees North), although alternative landing sites are considered as back-up. Such a mission must be inherently safe: even if something fails, it should still be safe, e.g. a failing capsule can be designed to burn in the atmosphere and therefore be of no threat. The principle approach for safety of YES2 is: Simplicity Increased reliability by having simple, wellunderstood or well-tested systems with few interfaces. Inherent safety Student built satellites cannot be expected to be as highly reliable as their professional equivalents. Therefore, mission and design concepts must be selected such that single failures do not lead to hazards. This also allowsAnnex 1 reports in more detail about the technical challenges and solutions regarding safety of the tether mission in particular.1for highly attractive experiments such as the 30 km tether deployment or a capsule landing in Europe. Understanding your hardware Hardware performance is modelled, simulated (Monte Carlo etc.) and tested. Particularly, An advanced testing system has been built for realtime tether deployment simulation with hardware-in-the-loop, mission simulation and reentry simulations. Awareness of risk & contingencies The system know-how needs to be translated in an overview of primary and secondary risks, failures and abort options. 2. The YES2 mission and safety approach In this section we give a short introduction into the YES2 mission [2.1] and subsequently discuss the tether related safety aspects [2.2], the capsule related safety aspects [2.3], the flight operations and landing concerns [2.4]. 2.1 YES2 Mission plan YES2 will be launched as a piggy back on FOTON in 2006 at ~ 280 km altitude (Fig. 1-[2]). YES2 consists of 2 satellite parts, connected by a tether Fig. 1-[3]: FLOYD (Foton Located Yes Deployer, Fig. 1-[4]) and AIR (An Inherently-safe Re-entry vehicle, Fig. 1-[5]). After initial downward ejection of AIR by a spring system, inertia and gravity gradient are used to deploy the tether between the two parts and AIR is stabilized 3.5 km below FOTON Fig. 1[6]. This takes about 1.5 hours. Possibly, AIR will be inflated at this stage. When synchronization with the projected landing site is achieved several hours later, deployment is continued (t2=0). The increased gravity gradient accelerates the capsule exponentially to ~60 km/hr. A Coriolis force builds up and the tether swings forward below and ahead of the FOTON Fig. 1-[7]. With the 30 km tether fully deployed (t2 ~ 2200 s), it becomes a pendulum and swings back to the vertical, below FOTON, where it is cut at FOTON-side (t2 ~ 3100 s). This cut releases the AIR and tether from FOTON Fig. 1-[8]. The reduced altitude and velocity send AIR into a reentry trajectory. The tether may still be attached to AIR and assist in initial orientation Fig. 1-[9]. Eventually the tether is released, together with all superfluous hardware, the so-called Mechanical and data-Acquisition Support System (MASS). MASS provides stiffness during launch, contains the ejection interface, the inflation system, and possibly a GPS and telemetry unit. AIR is now ultra-light (~5-15 kg) and inflated such to obtain a very low ballistic coefficient. It will slow down already in the very upper layers of the atmosphere and remain relatively cool Fig. 1-[10]. It will come down to Earth softly as a balloon and may therefore be used to land even in inhabited areas of Western Europe Fig. 1-[11]. If the AIR balloon fails to inflate, it will burn, thus creating an inherent level of safety. Thetether itself is dragged along to burn or will reenter soon after due to atmospheric drag. The total mission duration is several hours up to a day (depending on the duration of the synchronisation phase Fig. 1-[6]). Fig. 1 shows the mission stages and telecommands from different viewpoints.Fig. 1: YES2 sample return mission. Foton moves to the right. See text for numbers.22.2 Tether mission safety The YES2 tether deployment safety approach is characterized by the following points, providing a multi-level safety: 1. System well understood 2. Reliability through simplicity 3. Opportunities for evaluation and safe abort during mission, robust deployment 4. Orbital dynamics provide inherent safety 5. Low impact on Foton if failure These points will now be discussed in detail: System well understood The deployer hardware is based on a flight proven tether deployer concept, derived from the SEDS missions (Fig. 2). The following steps are followed to fully characterize the tether hardware:Hardware modelled, tested and characterized in detail. This includes e.g. the tether spool unwinding characteristics inside the canister (Fig. 2) as well as the friction brake performance. For the YES2 brake, mathematical models were developed (Fig. 3b, [5,10,11]) and friction tests were [5],[6] performed, also in zero-gee. Tests in thermal vacuum are planned. Validated 3D Tether simulator [5],[7] MTBSim ( ). Unknowns in orbit parameters are modelled as having normal distributions with conservative standard deviations: Environment (aidrag), initial conditions (ejection speed and direction), control measurement errors, brake friction performance parameters, etc. Standard deviations based on results of testing, literature etc. See also Fig. 4.Reliability through simplicity The tether deployer concept and hardware is chosen for its simplicity, to avoid as much as possible failure modes. There are no moving parts, nor open guides required for the unwinding there is an axial deployment from a spool head as depicted in Fig. 2) and the single thin smooth tether is thus contained. The so-called barberpole brake (Fig. 3a) is a simple snag-free friction-brake design: the friction acts a viscous damping force rather than a (destructive) clamping or inertia force.Fig. 2: Left: FLOYD: YES2 Deployer, SEDS derived. Middle: YES1 tether spool. Right: YES2 tetherAlso the control feedback is designed for simplicity: · Only length measurement is required for feedback. It has been demonstrated there is no need for differential GPS, angle measurement or tension measurement, even not if accurate landing is a requirement[8,9,12]. Furthermore there is no need for communication between the capsule and Foton. The length is measured on the Foton-side, where the control computer is housed in a pressurized, thermally controlled environment. The unwinding of the tether is monitored by optical sensors, counting the number of deployed loops. From a table, the deployed length is calculated and velocity is derived by a filter[5].Dynamics & effect of disturbances studied extensively.Monte Carlo simulations quantified deployment control response Realistic breadboard testing performedYES2 team designed improved test [16] rig , also simulates the mission.With real-time hardware-in-theloop and closed loop control [8]. The results show that a better than 0.5% deployment accuracy can be obtained with the current system, in both length and deployment angle. The lessons learned could be directly applied into design improvements. The results also indicate how the Monte Carlo simulations indeed provide results typical for real [8] hardware systems . Improvements based on the results of above tests. It includes a display of the 3D deployment as actually achieved by the hardware. It can be used for the full range of deployment tension and velocities. Includes EGSE and can also be used to test flight software.Figure 3a: YES2 barberpole brake30.60.50.4 Tension [N]0.30.20.10 0 0.5 1 1.5 Turns [#] 2 2.5 3T = (T0 + I .r .l&2 ( fq q 0 -q ) 2.p . f n .n ).e .e E ArelFig. 3b: Barberpole friction brake behaviour: the applied friction is proportional to the exponential function of the number of turns wrapped around the central pole. The pole itself is positioned by a stepper motor through a feedback based on length measurements. A simplified mathematical model is shown (more advanced models were derived in [5,10,11]). Measurements of tension versus turns performance are shown below, from which the friction parameters in the model can be derived. At high velocities, the tension resulting from the unspooling rises as well (see formula, with at least the square of velocity). This means there will be an inherent tendency for passive braking.This reference deployment is designed to have: 1. good robustness (no very low velocities (<0.3 m/s) during deployment to avoid risk of getting stuck, 2. a nominal tension level with sufficient margin to control in either direction with the brake position 3. a tension level high enough to avoid bending of the tether as a result of Coriolis forces 4. smooth end brake and tether length margin to avoid jerks and slackness when the tether is fully deployed. A feedback will be applied with respect to the brake position from the reference file. Because of the non-linear dynamics of tethers in space, an Energy Feedback was devised and tested. For this, the onboard computer converts length and velocity into a system energy measure based on a mathematical model of the tether system (potential & kinetic)[12]. If the system has too much energy, extra energy is dissipated by applying additional brake turns. The mission operations are kept simple and are minimized for real-time human interaction. There are no telecommands other than switch on/off, (time tagged) eject, start of second stage & cut tether. In order to allow safety for the Foton carrier, the Russian controller will have full control and/or override possibility (Fig. 10c). For example, the tether is cut autonomously, at a fixed time since start of second stage deployment: t2 = tcut. This time can be pre-fixed before launch, or sent after launch by time-tagged telecommand (TTTC), when the orbital parameters are more precisely known. During the tether deployment itself, no telecommands will be sent (other than abort). The cut-time has been determined at a specific point in the swing back (Fig. 1-[8]), some degrees before the vertical chosen such that robustness with respect to system noise is maximal[9]. Opportunities for evaluation and safe abort during mission, robust deployment Fig. 10c shows the reference mission control. Because the deployment is in two stages (Fig. 1), there is the opportunity to evaluate the mission success during the stable synchronization phase. Now the 2-stage deployment was developed not only for this purpose. At 3 km distance between Foton and the capsule, the difference in gravity is sufficiently large to quickly accelerate the capsule. Therefore the second stage of deployment is less sensitive to noise and more predictable. In this way, the robustness of the tether deployment is significantly increased [9], [13] .Fig. 4: Visualization of Monte Carlo simulations results. A large amount of mission, environment, system and control parameters was disturbed according to normal distributions. The image shows the two-stage deployment combined results of 600 simulations, as seen from the side (Foton above in origin, moving left, Earth is down). Interval between the blobs of points is 200 s. Each point indicates the position during a single Monte Carlo run. The final set of small lines (at end of swing below in yellow image) are vectors indicating the error in obtained Delta-V relative to the nominal deorbit vector of 113 m/s, shown in the red box for comparison. These errors translate into a 50 km 1 sigma landing error.·Simple & robust control algorithm: A reference deployment is stored on board containing: tether length, angle and brake position as a function of time.4Orbital dynamics provide inherent safety As explained above the concept of the barberpole and axial spool deployment makes it unlikely that the tether would get stuck and introduce a sudden stop. The following discussion should be considered in such event. The first tens of meters of the tether can be designed to break in case of tether snag. If the tether would snag just after ejection, The kinetic energy of the capsule mv2 will be converted into potential energy of the strain in the tether: ku2. The peak tension F=ku will thus be: Fpeak,snag = v Ö(mEA/L), With k = EA/L and L the current length of the tether. If L is small, shortly after ejection, and in the neighborhood of Foton, the tension will be very high and the tether will break, so there will not be a recoil. In case of unforeseen jerk & slackness near the end of deployment, the capsule will bounce up, and will get into a free orbital trajectory that will tend to restore tension. The oscillation is dampened out without large effect on landing site (Fig. 5, [12]).Furthermore there is always a chance that the tether is cut by micrometeoroids or debris. If this would however happen, the YES2 tether will be (nearly) immediately removed from orbit by drag (low orbit) and momentum transfer effects. Note: the relevant measure for meteorite risk is the integrated exposed time-length product (Annex 1.3). For YES2 we selected a singlestrand tether for simplicity. The part of the tether that is exposed to the space environment longest, should also be the thickest. With the first 3 km (first stage) of thickness 1 mm, the survivability probability amounts to 99.5% for the nominal mission, or 98.9% if the first stage phase is delayed to a full day for mission operation reasons. Low impact on Foton One often-expressed worry is the possible wrapping of the YES2 tether around Foton. YES2 intends to eject to nadir (downward), for simplicity of the attitude requirement of Foton. Now suppose the ejection will be in apogee. With the velocity vector pointing downward, it means that the instantaneous apogee of the capsule must be larger than the altitude at time of ejection. In case of a somehow friction-less deployment, eventually, the capsule could meet-up with Foton again and there is a potential danger of the tether wrapping around Foton. In reality, a tether deploying from a spool will always dissipate some energy, even without friction, to account for: · the increase in kinetic energy of the complete system as new parts of the tether gain speed, · the shock energy (Carnot energy), required to bring into instantaneous motion the tether from the spool[12], in the same way as elements of a chain jump from tensionless to tensioned when pulled. From the law of momentum change, F=d(mv)/dt, it can be directly derived that the minimum tension that accounts for this dissaption is equal to: Tmin,deploy = rv2, with r the linear density of the tether [kg/m], and rv the rate of increase of moving mass [kg/s]. This term is called the rocket term. In addition, in reality, there will always be friction in the system. It will be part of the YES2 safety and contingency investigation what friction levels are required to dissipate enough energy to avoid risk of collision with Foton. It is proposed to put the brake in initial braking position, such that if the stepper motor fails, the system will decelerate gently. Depending on the results of the analysis, it may be required to eject more in backward direction, to decrease orbital energy of the capsule. This 5Fig. 5: tether deployment with and without feedback. The deployment without feedback deviates considerably. Because no tether length margin is included here, the capsule snags at the end of the tether. However the combined orbital/tether dynamics cause the tension to restore and the oscillation to dampen out.If the deployed length is intermediate (several hundreds of meters), the case is much less clear. The best solution is to provide a passive absorption mechanism near the end of the tether. This is called ripstitching (Fig. 6).Fig. 6: Ripstitching concept. The capsule moves with arrow. If the tether (orange) gets suddenly stuck, the ripping of the stitches (black) will absorb some of the energy.will lead to, firstly, a larger difference in orbital period, so to increase the distance between the two bodies in the subsequent apogee, and secondly, a lower apogee so that less time will be spent in the same altitude region. Note that the true anomaly of ejection does not need to be in apogee but can freely (and possibly more optimally) be chosen, because of the 2-stage deployment concept. Moving into secondary level failures, if the tether would wrap, or the capsule should come back to Foton, one should consider that: · The Foton weighs over 6000 kg vs. 0.2 kg/km tether (<7 kg total), so the impact of the tether will be low. · The nominal tension in the tether is also low, less than 10 N throughout the mission, less than 0.1 N typically. · The low ejection energy (20 kg at 2 m/s = 40 J, a walking child) limits the risk of damage to Foton subsystems by capsule impact. · The tether design break strength is near that of typical handling loads (40 kg) so that the risk of deforming appendages of Foton is inherently low. 2.3 Capsule safety and landing Inherent safety As mentioned, the YES2 capsule is An Inherently-safe Re-entry vehicle (AIR). Rather than depending for a soft landing on a parachute system, the capsule will be its own parachute, by being light and large. The landing velocity relates to: vlanding = Ö [2g (mAIR-rairVAIR) / (rair CD S) ] with rairVAIR the buoyancy of the AIR capsule and mAIR/CDS the ballistic parameter. A large volume (> 2 m3), a large surface and a low mass all reduce the landing velocity (YES2: 1<m/S<10). Inflatable capsule The main concept of interest to achieve such velocities is an inflatable capsule, because it is scalable to ISS applications. The key to inherent safety with an inflatable (or unfoldable) capsule is to have a single stage inflatable (it either succeeds or it does not) and to inflate already in space. The inflated capsule will decelerate at very high altitudes (>80 km), in the rarefied flow, with low density and therefore low heat fluxes. The capsule can be dimensioned such that, if for some reason the inflation fails, it will burn and be of no hazard (Fig. 7). In the contingency-case, the capsule with decreased surface will penetrate deeper into the atmosphere until it eventually decelerates as well. Interestingly, the peak of the total dissipated power (Fdragv = 0.5 rair v3 CD S, [W]) remains nearly unaffected, and occurs at similar velocity (~5 km/s), but in a higher 6density region. The smaller surface area S causes increased heat load. The dissipated power expressed in [W/m2] in fact scales roughly with the ballistic coefficient. In reality heat flux and temperature are not directly proportional to dissipated power and will peak typically even before [Fig. 7].2500Tem pera tur e in the w all [K]2000inflation 'failed inflation succ ess150010005000 0 100 2 00 300 400 500 6 00 Tim e fr om e ntry po int at 12 0 km [s]Fig. 7: Capsule wall temperature during re-entry, in case of successful inflation (lower curve), and failed inflation (upper). In case of failure, the capsule will burn.The inflation system and other mechanical hardware, and even the heavy instrumentation is jettisoned before entry, to reduce mass and hardness of the capsule even more. If the capsule is spherical and the final velocity becomes supercritical (Reynolds number > ~300.000), the turbulent, viscous flow will stick to the wall on the back of the capsule, reducing the size of the capsule s (pressure-less) wake, and therefore the pressure drag. The effect on landing velocity is roughly an increase by factor 2. This is one of the reasons to consider a sphere-cone capsule. The steep gradients at the edge of the vehicle will ensure flow release and a large wake, so high drag. Also the sphere-cone allows for a relatively large nose radius (larger shock distance so lower heat flux) and reduces total surface area, both allowing for a potentially lighter capsule.Fig. 8: Triple Tori mock-upAt a mass of 12 kg and diameter of 1.8 m, the Triple Tori expected landing velocity is less than 10 m/s, the equivalent impact energy (if relatively little ground winds) only about 500 J, equivalent to the energy of a handful of dropping soccer balls.A good time for inflation seems to be the synchronization stage (Fig. 1-[6]). This is because then there is a stable situation with a well-known time since ejection. The inflation can thus be simply initiated by a timer connected to a microswitch. There will be no telecommand capability to the AIR capsule, so autonomous inflation is required. The inflation is also expected to reduce any remaining capsule librations when suspended from the tether, due to increasing moments of inertia as well as increasing arm and stabilizing torque of the tether tension. However, the possibility of a long waiting phase of maybe a day could lead to excessive leakage of gas. Later inflation (e.g. after cut of the tether) is possible as well, but it is more difficult to make a reliable, autonomous inflation system. Filtered measurements of tether tension and/or dynamic pressure are required then. 2.4 YESsim mission simulator A complete mission simulation environment YESsim has been developed, connecting the following major functionalities:possible use of the tether to support this [Fig. 9]. YESsim is used to study whether the inflatable capsule deformations cause attitude instabilities during the part of re-entry where heat flux and dynamic pressure are steeply decreasing.Fig. 9: tether orienting capsule at entry. The capsule (red circle) is at ~100 km altitude. The tether is 30 km long, so the upper part is outside the atmosphere. Tension near the capsule is now ~15 N but rising strongly.· · · · · · ·Tether deployment dynamics simulation Re-entry simulation Pressure-induced deformations on inflatable capsule Attitude propagation Heat transport throughout capsule Noise models & Monte Carlo VisualisationsThis integrated 3D tool includes models for the different flow regimes, higher order gravity and solar pressure disturbances, as well as the latest versions of atmosphere and wind models (MSISE00, HWM93, G2S). The heat transport through the capsule is based on models supported by test [17]. The validated tether simulator has been described in section 2.2 and includes tether deployer hardware models. Tether & aerodynamic torques are calculated in real time. The Re-Entry Simulation Tool (REST) includes engineering relationships for the different flow regimes. YESsim will be used to make certain mission decisions, such as best time of inflation, optimal entry angle and time of tether cut at Foton, time of MASS/tether jettison from AIR. The attitude of the capsule when suspended from the tether will be evaluated. The capsule has no active attitude control, so pitch-off rate induced by the ejection must be dampened out or contained by the tether tension or initial spin. With YESsim we can evaluate the required initial condition and acceptable angular rates for correct orientation at entry, as well as theLanding area minimization The Re-Entry Simulator Tool (REST) is the part of YESsim that is used for evaluating trajectory, heat fluxes and landing points. Combined with the Monte Carlo tool, it is used for landing area determination. The Monte Carlo tool takes into account the errors of the density, the wind velocity, the drag coefficient and the lift coefficient (aerodynamic landing area). When coupled to the tether simulator, the total landing area can be simulated. The collection of possible landing areas, due to orbital uncertainties in the planning phase, is called the landing zone. The landing zone is an important parameter for YES2. Although the nominal Foton landing zone in the Kazakhstan region remains a back-up for YES2, it will be attempted to meet the challenge of landing the first capsule ever on (WesternEuropean) soil. Such a landing in inhabited could only be allowed for an inherently-safe vehicle. However, since the European countries in general are rather small, it may be necessary to obtain permission to land from more than one country. Not an easy task indeed. This is where REST will help. It is used for minimization of the landing area in the following ways: recommendations for optimal initial conditions REST is coupled to an NRL-provided module, G2S, which allows for reading-in of actual weather predictions, to improve trajectory estimates at the last moment. The coupling of REST to the tether simulator will be used during the mission7。
DWR框架介绍及使用方法
可以使用下面的javascript调用方式：
<script type="text/javascript"
src="[WEBAPP]/dwr/interface/Remote.js"> </script>
<script type="text/javascript"
src="[WEBAPP]/dwr/engine.js"> </script>
DWR还有个限制：
避免使用JavaScript的保留字，因为用保留字命名的方法会自动被执行。大多数的JavaScript保留字和Java保留字相同，所以不能定义一个“try()”方法，然而有一个最常用的方法是“delete()”，这个方法在JavaScript中有特殊含义，但在Java中没有。
2.5
以上三种方式DWR都支持，仅仅是通过修改配置文件就可以切换实现方式。
4.2
如果需要更快的响应速度，并且可以接受额外的服务器负载，可以配置DWR使用Coment或Polling方式。这种模式称作积极的Reverse Ajax。默认情况下DWR不是以积极ReverseAjax模式启动，仅仅允许piggyback传输模式。
或者你可以都写在一行：
Remote.getData(42, function(str) { alert(str); });
3.2
假设有下面的Java方法，有一个Person类型的Java Bean参数：
public class Remote {
public void doSomethingWithPerson(Person p) {
}
你可以像下面一样调用Javascript：
dwr使用技巧
DWR1 DWRDWR（Direct Web Remoting）是getahead公司开发的一个实现Ajax应用的框架。
它允许客户端Javascript远程调用服务器端Java类的方法，执行相关的事务操作。
本节将从DWR简介、使用入门、适用范围等方面详细介绍DWR。
1.1 DWR简介DWR（Direct Web Remoting）是一个开源的类库，可以帮助开发人员开发包含Ajax技术的网站。
它可以允许在浏览器里的代码使用运行在Web服务器上的Java函数，就像它在浏览器里一样。
DWR包含两个主要的部分，其一是运行在浏览器客户端的Javascript，这部分被用来与服务器通信，并更新页面内容；其二是运行在服务器端的Java Servlet，这部分被用来处理请求并将响应结果发送给浏览器。
DWR采取了一种动态生成基于Java类的Javascript代码的新方法来实现和处理Ajax。
这样Web开发人员就可以在Javascript里像使用浏览器的本地代码一样使用Java代码，而实际上这些Java代码是运行在服务器端并且可以自由访问Web 服务器资源的。
出于安全的考虑，Web开发者必须适当地配置，决定哪些Java类可以安全地被外部使用。
图11-1来自DWR的官方文档，展示了DWR如何利用一些类似Javascript的onClick等事件的结果来改变一个下拉列表框的内容。
这个事件处理器调用一个DWR生成的Javascript函数，它和服务器端的Java函数是匹配的。
DWR接着处理了Java和Javascript之间的所有远程信息，包括转换所有的参数和返回需要的值。
接着DWR执行了相应的回调函数（populateList）。
这个例子演示了如何使用DWR功能函数来改变网页内容。
图11-1 DWR交互过程使用DWR可以有效地从应用程序代码中把Ajax的全部请求-响应循环消除掉。
这意味着，客户端代码再也不需要直接处理XMLHttpRequest对象或者服务器的响应，不再需要编写对象的序列化代码或者使用第三方工具才能把对象变成XML，甚至不再需要编写servlet代码把Ajax请求调整成对Java对象的调用。
DWR中的反向“全推”和“半推”AJAX技术（第1部分）
目录1.1DWR 中的反向“全推”和“半推”AJAX技术（第1部分） (2)1.1.1反向Ajax技术的实现原理 (2)1.1.2DWR 中的反向“全推”Ajax技术的实现实例 (5)1.1.3设计服务器端的Java程序类 (10)1.1DWR 中的反向“全推”和“半推”AJAX技术（第1部分）1.1.1反向Ajax技术的实现原理1、什么是反向Ajax技术（1）反向Ajax反向Ajax的基本概念是客户端不必从服务器获取信息，服务器会把相关信息直接推送到客户端。
（2）为什么要应用反向Ajax技术这样做的目的是解决Ajax传统Web模型下的实时信息获取的问题，常规的实现方式是客户端浏览器必须不断地请求服务器，并主动询问是否存在变更的信息，如果有变更的信息立即更新当前的页面（或者页面中的一部分）。
比如监控（后台硬件热插拔、LED、温度、电压发生变化）、即时通信（其它用户登录、发送信息）、即时报价系统（后台数据库内容发生变化）都需要将后台发生变化的数据实时地传送到客户端而无须客户端浏览器不停地刷新。
（3）反向Ajax技术能够更好地解决这个问题应用反向Ajax技术，能够实现由服务器主动地联系所有的浏览器，并通告这些浏览器服务器端的数据已经发生的变更。
2、常规的Web应用系统无法实现反向Ajax技术（1）常规的AJAX技术所存在的局限性AJAX技术提高了单用户操作的响应性，但Web 本质上是一个多用户的系统。
现有的AJAX 技术的发展并不能解决在一个多用户的Web 应用中，将更新的信息实时地传送给客户端，从而用户可能在“过时”的信息下进行操作。
（2）为什么常规的Web应用中无法实现反向Ajax技术因为HTTP的特点是需要客户端浏览器产生请求后，服务器端响应的程序才会产生响应输出。
如果客户端浏览器等程序不再对服务器端程序产生新的请求，服务器端响应的程序也就不响应客户端程序的请求。
因此，在正常的情况下，服务器端的程序是不可能操纵客户端浏览器。
DWR 在解决编辑冲突中的应用
ＤＷＲ 在解决编辑冲突中的应用 摘 要：随着Ｗｅｂ２．０ 时代的到来，在线协作编辑系统被广泛的使用，随之而来出现的编辑冲突问题也屡见不鲜。
本文首先分析了编辑冲突出现的情况，比较了常见的解决编辑冲突方法，并发现了这些方法的不足，然后介绍了基于Ａｊａｘ 技术的ＤＷＲ 框架在增强用户体验上的优势，最后提出了使用ＤＷＲ 框架解决编辑冲突的方法，从而使编辑冲突的解决更加实时化，响应客户的方式更多样化。
关键字：文本编辑；编辑冲突；ＡＪＡＸ； ０ 引言 在 Ｗｅｂ２．０ 的时代里，文本编辑的使用无处不在。
有些是独立的个人文本编辑系统，如博客的编写，个人空间信息的编写，还有些则是协作编写的系统，例如维基百科，互动百科等。
在这类开放的协作文本编辑系统中，由于编辑与更新的同时性和异步性的存在，编辑冲突的问题也随之产生了。
许多的协作编写系统也提出了自己解决的方法，它们各自有各自的特点，在判断发生编辑冲时尽量做到实时性，在发生编辑冲突后尽量使解决方法更丰富。
但是要将实时性和解决方法的丰富性都做好却很难。
本文从实际出发，探讨了运用ＤＷＲ 技术的解决编辑冲突的策略，有效的体现了解决编辑冲突的实时性和解决方法的丰富性。
编辑冲突出现的情况在一些多人协作的文本编辑的系统中，这样的冲突问题是时常可以碰见的。
但通常出现的情况有两种。
一种是用户与用户之间的编辑冲突。
例如在维基百科中，有些内容任何用户都可以编辑，并且编辑的内容都会得到更新。
那么考虑这种情况：Ａ，Ｂ 为两个普通用户。
对一个词条点击了编辑按钮，进入了编辑状态也对同一个词条点击了编辑按钮，并且也进入了编辑状态完成了他的修改，并单击保存本页。
这个词条用Ａ 的版本保存了也完成了他的修改，并单击保存本页。
这时Ｂ 就出现编辑冲突问题。
因为 Ｂ 用户编辑的内容在尚未提交时就已经被Ａ 更新了。
另外一种情况是用户编辑的内容需要审核的编辑系统，例如百度百科或基于维基的一些文本编辑共建系统中。
corr预测模型指标-定义说明解析
corr预测模型指标-概述说明以及解释1.引言【1.1 概述】本文旨在介绍和探讨corr预测模型指标。
近年来，随着数据科学和机器学习的快速发展，越来越多的企业和研究机构开始关注和搭建预测模型，以帮助他们更好地理解和预测数据趋势。
在这个过程中，corr预测模型指标作为一种常用的衡量和评估预测模型性能的指标，备受关注。
corr预测模型指标是基于相关系数（correlation coefficient）的一种评估模型准确性的指标。
通过分析已知数据点和预测数据点之间的相关性，我们可以评估预测模型的精确度和准确性。
在实际应用中，corr预测模型指标可以应用于各种领域，例如金融市场预测、销售预测、天气预测等，以帮助企业和研究机构做出更准确的决策。
本文将从以下几个方面来介绍corr预测模型指标。
首先，我们将简要介绍文章的结构和各个章节的内容。
接着，我们将详细讨论corr预测模型指标的定义、应用场景以及计算方法。
然后，我们将通过案例分析和实证研究来验证corr预测模型指标的有效性和可行性。
最后，我们将总结本文的主要内容并展望未来的研究方向。
通过本文的阐述，读者将能够全面了解corr预测模型指标的意义和作用，以及如何应用于实际场景中。
同时，本文也将为相关领域的研究者和从业人员提供一些参考和借鉴，以提高他们的预测模型的准确性和预测能力。
总之，本文的目的在于探讨和介绍corr预测模型指标，以帮助读者更好地理解和应用于实践中。
接下来，我们将结合具体案例，深入探讨corr 预测模型指标的各个方面，相信这将为读者提供有价值的信息和洞察力。
1.2文章结构文章结构是文章的骨架，它通常包括引言、正文和结论三个部分。
在本篇文章中，我们将按照以下结构进行阐述：引言部分（Introduction）在引言部分，我们将对本文的主题进行概述，并介绍本文的结构和目的。
正文部分（Main Body）正文部分是文章的核心部分，我们将重点讨论corr预测模型指标。
rwkv语料例子-概述说明以及解释
rwkv语料例子-概述说明以及解释1.引言1.1 概述概述部分应该对整篇文章的主题进行简要介绍，并指出文章的重要性和价值。
下面是对"rwkv语料例子" 这篇文章概述的一个例子：引言部分旨在引出本篇文章的主题——"rwkv语料例子"。
本文旨在使用rwkv语料作为例子来解释其在语料库中的应用和意义。
rwkv语料是一种包含"raw"（原始文本）、"words"（单词列表）、"keywords"（关键词列表）和"values"（值列表）的数据结构。
它在语料库的建立和管理过程中具有重要作用，并在信息检索、自然语言处理等领域发挥着重要作用。
接下来的章节将进一步阐述文章的结构和目的。
第二部分将介绍rwkv 语料的相关要点，通过详细说明其组成和用途，进一步解释其在语料库中的实际应用。
接着，第三部分将对本文进行总结，并对rwkv语料的未来发展进行展望。
总的来说，这篇文章旨在提供一个深入了解rwkv语料的机会，帮助读者了解其在语料库中的作用，为相关领域的研究和开发提供指导。
通过本文的阅读，读者将对rwkv语料有更为全面的认识，并能够进一步应用于实际项目中。
1.2文章结构文章结构是指文章的整体架构和组织方式，它的合理性和清晰度直接影响到读者对文章内容的理解和把握。
一个良好的文章结构能够使文章层次分明，逻辑严谨，有助于读者更好地掌握和理解文章的主旨和论证过程。
本文的结构分为引言、正文和结论三个部分。
引言部分对文章的内容进行了概述和总体描述，旨在引起读者的兴趣和注意。
通过引言可以使读者明确文章的主题和意图，并为后续的正文部分做好铺垫。
正文部分是整篇文章的核心，对于本文来说，它包括了第一个要点和第二个要点两个子部分。
在第一个要点中，我们将详细介绍rwkv语料的特点、应用场景以及相关的实例。
通过具体的例子和分析，读者可以更好地理解rwkv语料的含义和用途。
指标讲解MACDWR
WR的数值范围为 0——100，
其中以0为顶部， 以100为底部。
WR
80——100区间时， 是WR指标的超卖区， 表明市场处于超卖状态， 股票价格已近底部，
可考虑买入。 WR=80这一横线， 超买状态，
股票价格已进入顶部，
可考虑卖出。
•5、当红柱开始消失、绿柱开始放出时，这是股市转市信号之一，表明股市的上涨行情（或高位盘 整行情）即将结束，股价将开始加速下跌，这时应开始卖出大部分股票而不能买入股票。
•6、当绿柱开始消失、红柱开始放出时，这也是股市转市信号之一，表明股市的下跌行情（或低位 盘整）已经结束，股价将开始加速上升，这时应开始加码买入股票或持股待涨。
WR指标的背离 是指WR指标的曲线的走势正好和股价K线图上的走势正好相反。和其他技术分析 指标一样，WR指标的背离也分为顶背离和底背离两种。
1、当股价K线图上的股票走势一峰比一峰高，股价在一直向上涨，而WR指标图 上的WR曲线的走势是在高位一峰比一峰低，这叫顶背离现象。顶背离现象一般 是股价将高位反转的信号，表明股价短期内即将下跌，是比较强烈的卖出信号。
指
MACD
指数平滑异同平均线
标 WR 威廉指标
MACD
定义：由快的指数移动平均线（EMA12）减去 慢的指数移动平均线（EMA26）得到快线DIF， 再用2×（快线DIF-DIF的9日加权移动均线 DEA）得到MACD柱
•12日EMA（快的指数移动平均线）的计算： EMA（12） = 前一日EMA（12） X 11/13 + 今日收盘价 X 2/13 •26日EMA（慢的指数移动平均线）的计算： EMA（26） = 前一日EMA（26） X 25/27 + 今日收盘价 X 2/27 •差离值（DIF）的计算： DIF = EMA（12） - EMA（26） 。 （根据差离值计算其9日的EMA，即离差平均值，是所求的DEA值。为了不与指 标原名相混淆，此值又名DEA或DEM） •DEA = （前一日DEA X 8/10 + 今日DIF X 2/10） •用（DIF-DEA）*2即为MACD柱状图。 •MACD的意义：由快、慢均线的离散、聚合表征当前的多空状态和股价可能的发 展变化趋势。
创高满意度之回归分析
ˆ 创高幕墙员工满意度调查各维度回归分析为了更为清楚地了解各维度满意度对公司总体满意度的影响，本部分将对创 高各维度满意度与公司总体满意度进行回归分析，建立相应的回归方程模型。
设被 解释变量为Y ，解释变量为X ，则多元线性回归理论模型为：Y=a 0+a 1x 1+a 2x 2+······+a j x i +ε其中，Y 是被解释变量，也称为因变量，a j （j=0，1，···，n ）是回归系数， x i （i=1，2，···，n ）是解释变量，也称为自变量，ε是残差。
本部分的回归分析将使用到以下统计量：F 值、R ²、DW 值。
其中F 统计量是为 了检验解释变量与被解释变量之间是否存在显著的线性关系，SPSS 会根据F 统计量 值自动计算出其对应的概率p 值，从而判断出解释变量与被解释变量之间的显著性 水平。
R ²代表拟合优度，R ²取值在0~1之间，R ²越接近于1，说明回归方程对样本 数据点的拟合优度越高，反之，R ²越接近于0，说明回归方程对样本数据点的拟合 优度越低。
DW 观测值是判断残差序列之间是否存在自相关，DW 值在0~4之间，当 残差序列不存在自相关时，DW ≈2（1-ρ）。
如果残差序列存在自相关，说明回归 方程没能充分说明被解释变量的变化规律，还留有一些规律性没有被解释，也就是 认为方程中遗漏了一些较为重要的解释变量；或者，变量存在取值滞后性；或者， 回归模型选择不合适，不应选用线性模型等。
本部分利用SPSS13.0对数据进行处理、分析，发现本部分分析的几个方面的 杜宾值即DW 值均在2左右浮动（具体参数如表1~6所示），因此，适合使用线性回归 模型构建方程，进而分析相应解释变量对被解释变量的影响。
1.从整体上进行分析：各维度上员工满意度对整体满意度的影响如表1所示，本部分解释变量分别为公司满意度（X 1）、工作本身满意度（X 2）、 工作回报满意度（X 3）、工作环境满意度（X 4）、工作群体满意度（X 5），被解释变量 为整体满意度（Y ）。
Wfr命令详解资料
简介wfr- 支持多国语言的字符串批量查找和替换- 批量字符集编码转换∙纯 unicode 规则匹配内核，真正支持各国语言文字的正则匹配。
∙带有兼容性检查的字符集编码转换功能。
同时支持 libiconv （iconv.dll）、IBM libicu 和 Windows 自带的字符集编码转换API。
∙支持 TCL 8.2 兼容的高级正则表达式（ARE）。
∙支持一次性指定多个文件通配符和文件列表。
∙支持管道模式，与其它命令协同工作；支持半管道模式，从文件中获取输入，但将结果写到标准输出。
∙支持包含子目录。
∙支持普通匹配、正则匹配、可忽略大小写、可跨行匹配。
替换时可以使用正则的子表达式。
∙同时支持 posix 标准的扩展正则表达式及 perl 风格的正则匹配。
∙可以格式化替换内容为全大写或全小写，便于在批处理中对环境变量和命令行参数做大小写一致化处理。
∙支持 DOS（Windows）、Macintosh 和 unix 风格的换行符，可选择自动识别（默认）或手动指定。
∙统计功能，列出每个文件中的替换次数、总替换次数等。
∙支持 Win32 和纯 DOS 环境（纯DOS环境中需要 HX DOS Extender 支持）。
∙支持 POSIX 环境，提供 linux x86/x64、FreeBSD、NetBSD、Solaris 等版本下载。
更新历史2013-11-19, Ver 2.3.9-1119UPD: 在 -s 模式下，默认忽略无法访问的子文件夹。
2009-12-13, Ver 2.3.6.1213NEW: 新增 -errstop 参数。
使用此参数时，遇到无法访问的文件和子目录会报错并自动终止查找。
不使用此参数时，fr 会自动跳过无法访问的子目录。
对于无法读写的文件，fr 会输出一行报错信息，但不会终止搜索。
2009-03-12, Ver 2.3.5.0312FIX: 修正了在使用 /r 或 /ric 参数并且使用 ARE 'p' 和 's' 模式进行匹配时，'^' 有时仍然会匹配行首的问题。
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第九章
MATLAB优化算法案例分析与应用
•9.4.5 结果求解及分析
for flag=1:3 if A(i,j)<=ca(k) w=0; X(i,h)=X(i,h); break; elseif A(i,j)>ca(k)&&A(i,j)<B(f1,f2) w=1-exp(-(A(i,j)-ca(k)/ca1(k))^2); X(i,h)=X(i,h)+w*A(i,j);%加权 break; else k=k+1; f2=f2+1; end end
函数建立评价模型，从而对评价指标每天的观测值进行排
序，最后用决策分析中的Borda数方法对四个城市的空气质 量综合排序。
%对应每个中值 %对应每个等级值
第九章
MATLAB优化算法案例分析与应用
•9.4.5 结果求解及分析
第九章
MATLAB优化算法案例分析与应用
•9.4.5 结果求解及分析
第九章
MATLAB优化算法案例分析与应用
•9.5 本章小结
本章考虑到污染物浓度这一评价指标的“质的差异” 和“量的差异”，采用动态加权综合评价方法建立评价模 型，增大了评价结果的客观性。首先对评价指标数据进行 归一化处理，然后选取偏大型正态分布函数作为动态加权
Borda数为
m
m
i 1
B(u j ) Bi (u j ) ( j 1, 2,3, 4)
i 1
建立以下由污染物浓度评价空气质量的数学模型：
x mj ij , (i 1, 2, ,55; j 1, 2,3) xij M m j j 当 x i时, 0 , 2 x i wi ( x) 1 e i , 当 x 时, i m X w ( x ) x , (i 1, 2,3) i i i i 1 m B(u ) B (u ) ( j 1, 2,3, 4) j i j i 1
SO2 NO2 PM10
0
0.1
0.2
0.3
0.4
0.5
0.6
0.7
0.8
0.9
1
加权函数的图像
第九章
MATLAB优化算法案例分析与应用
•9.4.3 空气质量评价模型的建立
为了给每次的检测值进行排序，在基于上述模型的同时，取综合评价 模型为各评价指标的动态加权和，即：
X wi ( xi ) xi
第九章
MATLAB优化算法案例分析与应用
第9章 DWRR应用分析
ห้องสมุดไป่ตู้
第九章
MATLAB优化算法案例分析与应用
•9.1 问题的背景
人类生活在大气里，洁净大气是人类赖于生存的必要条件 。一个人在五个星期内不吃饭或5天内不喝水，尚能维持生命， 但超过5分钟不呼吸空气，便会死亡。随着地球上人口的急剧增 加，人类经济增长的急速增大，地球上的大气污染日趋严重， 其影响也日趋深刻，如由于一些有害气体的大量排放，不仅造 成局部地区大气的污染，而且影响到全球性的气候变化。因此 ，加强大气质量的监测和预报是非常必要。 目前对大气质量的监测主要是监测大气中 等的浓度。
第九章
MATLAB优化算法案例分析与应用
•9.4 模型的建立与求解
表9-2 国标GB 3095-1996中3个主要项目标准限值
日平均浓度限值范围
mg m3
污染物名称 一级标准 二级标准 三级标准
SO2
NO2
PM 10
(0,0.05]
(0,0.08] (0,0.05]
(0.05,0.15]
(0,0.08] (0.05,0.15]
(0.15,0.25]
(0.08,0.12] (0.15,0.25]
对于这种既有“质差”，又有“量差”的问题，采用定常 加权法显然是不合理的，故合理有效地方法是动态加权综合评 价方法。
第九章
MATLAB优化算法案例分析与应用
•9.4.2 动态加权函数的确定
不妨选取呈正态分布曲线的偏大型正态分布函数作为动态加 权函数，即：
x i 0 , 2 x i wi ( x) i 1 e , x i
1 0.9 0.8 0.7 0.6 0.5 0.4 0.3 0.2 0.1 0
x=[0.6,0.67,0.6]; ca=[0.1,0.335,0.1]; % 标 准区间的中值 ca1=x-ca./sqrtm((-log(0.1))) %delta %% x=0:0.1:1; w1=1-exp(-((x-ca(1,1))/ca1(1,1)).^2); % 权值1 w2=1-exp(-((x-ca(1,2))/ca1(1,2)).^2); % 权值2 w3=1-exp(-((x-ca(1,3))/ca1(1,3)).^2); % 权值3 plot(x,w1,'r','linewidth',2) %画图 hold on %图像同轴柄显 示 plot(x,w2,'g','linewidth',2) plot(x,w3,'b','linewidth',2)
第九章
MATLAB优化算法案例分析与应用
•9.4.5 结果求解及分析
ca=[0.1,0.335,0.1]; ca1=[0.5341 0.4492 0.5341]; B=[0.2 0.6 1;0.67 0.67 1;0.2 0.6 1]; a=size(A,1); b=size(A,2); MX=max(A); MN=min(A); f1=1; f2=1; for j=1:b for i=1:a A(i,j)=(A(i,j)-MN(j))/(MX(j)-MN(j)); end end %中值 %δ的值 %标准分级 %A的行数 %A的列数 %A的每列的最大值 %A的每列的最小值 %B的行变量 %B的列变量 %将A里面的值标准化