RS码在旋转头数字磁记录器中的应用研究

本文讨论了数字磁记录器的差错控制方案以及ＲＳ码在旋转头数字磁记录器中的应用。简介ＲＳ码译码器的实现原理和方法。本文所介绍的原理与方法对ＢＣＨ码译码也适用的。文中给出了用ＥＰＬＤ实现的ＲＳ码译码器的结构．经实验测试，该译码器的速度可以达到４７Ｍｂ／ｓ，并成功地用于旋转头数字磁记录器（模样机）中。文章最后提出了ＲＳ码编译码器设计中有关问题与建议。     

基于ISA总线的高码速率大容量遥测数据存储器的研究

介绍基于 ISA(Industry Standard Architecture)总线的高码速度大容量遥测数据存储器的研究。作为计算机主存储设备的硬盘 ,它具有体积小 ,存储容量大的优点 ,本系统拟采用硬盘作为存储设备 ,且遥测数据在存储数据时采用脱线工作方式 ,我们设计了该存储器和计算机的接口且实现了对硬盘传输数据的 PIO(Program Input Output)方式的编程和对遥测数据的差错控制     

第十四讲 遥测磁记录技术

一、磁记录器的基本结构磁记录器由于价廉、存储容量大、可多次使用用可长期保存等特点,一开始就作为数据存储元件,应用在遥测系统和多种领域中。磁记录器由下列五部分组成:磁头、运带机构、记录放大器,重放放大器。磁头是电磁换能器,它可分为记录磁头、重放磁头和消磁头。在记录期间,信号经记录放大器,转换     

遥测系统中的旋转头磁记录器

旋转头磁记录器的数据存贮容量比纵向磁记录器的大得多,且具备一系列优点。文中简介19mm 旋转头磁记录器。它能满足数据存贮容量的要求,又能在恶劣的环境中工作。文中讨论其接口。主要的数据 I/O 接口是8位宽的单通串行口,此外,还有2个附加口,分别提供高速率的串行码和16位宽字。当多数据源被记录/重放时,为了和记录器连接,必须设置接口/多路调制器/解调器。文中介绍了三个配置实例,并简介各方案的特点。结果表明,旋转头磁记录器和多路调制器/解调器结合起来,为遥测系统提供了更大的存贮容量。     

我国第一台微机控制计测磁记录器通过技术评审

航天部七○四所研制成功YJ2-4型微机控制便携式磁记录器于10月29日通过技术评审。 YJ2-4型便携式磁记录器是我国首次采用微机控制的计测磁记录器,它主要特点是:微机控制、可编程梭动与选道记录、自备校准测量系统,元需外部设备即可进行自     

对地观测卫星与载人航天数据存储技术

纵览对地观测卫星与载人航天领域数据存储技术的发展历程,从系统应用的角度,评述空间磁记录器的特性,简介各种典型空间记录器的主要性能参数,以及磁光盘、固态存储技术在空间的应用,展望了国外未来载人航天任务的数据存储要求与空间数据存储技术的发展前景。     

美国遥测技术动态(续)

四、磁记录器(一)我们在遥测年会展览会上见到Schiumberger 公司的子公司 Sangamo 公司;Heneywell 公司;Bow 工业公司的展品,并参观访问了 Ampex 公司。Sangame 公司展出了 SabreX 型实验室用磁记录器;SabreⅩⅡ型空用汽车用磁记录器;Sabre80型磁记录器。Honeywell 公司介     

地空导弹营组网通信软件方案探讨

介绍了基于某系列地空导弹营组网系统通信所定义的JJNET异步串行传输协议的数据格式、协议机制、差错控制、链路管理机制及性能分析，并给出了其实现C语言程序。     

光棚测速的印刷电机转速控制系统

本文介绍的转速控制系统是检前磁记录器主轮伺服系统。该系统与我所以往研制的磁记录器主轮伺服系统有三点主要区别。①采用了低惯直流印刷电机。②采用光栅测速盘。③使用4π型数字式鉴频一鉴相器。本文结合锁相环路伺服系统工作原理,从三面三个特点出发,着重介绍了电机和光栅测速盘的选译,以及4π型数字式鉴频一鉴相器的工作原理。     

液体火箭发动机地面试验时基系统的设计

介绍一种运用数字电路设计时基系统的原理和方法.这种时基系统在液体火箭发动机地面试车中给模拟记录设备(光线示波器、磁记录器等)提供时间基准和历程信号。本文介绍的时基系统具有输出路数多、驱动能力强、时间精度及可靠性高、分析判读方便等优点。文中着重阐述设计原理和方法,对关键电路给出设计原理电路图。     

FY—1C卫星高分辨率云图传输技术

介绍了FY－1C星传输系统的任务、方案、主要技术指标和组成。系统采用极化隔离加带外频谱抑制的方法，达到了信道隔离的技术指标。概述了星载记录器由磁带记录器向固态记录器转变的技术因素以及磁带记录器、FLASH和DRAM固态记录器的研制过程。简述了传输系统在轨测试和运行状况。     

一个简单有效的磁记录纠错系统

介绍一种简单有效的纠错编码方法 ,用于资源卫星高密度数字磁记录器 ,使误码率由 10 -6降低到 10 -11,同时介绍它的基本工作原理、实现方案及试验结果。     

Rotational motion of <Emphasis Type="Italic">Foton M-4</Emphasis>

The actual controlled rotational motion of the Foton M-4 satellite is reconstructed for the mode of single-axis solar orientation. The reconstruction was carried out using data of onboard measurements of vectors of angular velocity and the strength of the Earth’s magnetic field. The reconstruction method is based on the reconstruction of the kinematic equations of the rotational motion of a solid body. According to the method, measurement data of both types collected at a certain time interval are processed together. Measurements of the angular velocity are interpolated by piecewise-linear functions, which are substituted in kinematic differential equations for a quaternion that defines the transition from the satellite instrument coordinate system to the inertial coordinate system. The obtained equations represent the kinematic model of the satellite rotational motion. A solution of these equations that approximates the actual motion is derived from the condition of the best (in the sense of the least squares method) match between the measurement data of the strength vector of the Earth’s magnetic field and its calculated values. The described method makes it possible to reconstruct the actual rotational satellite motion using one solution of kinematic equations over time intervals longer than 10 h. The found reconstructions have been used to calculate the residual microaccelerations.     

The use of refined model of aerodynamic moment in the problem of reconstruction of the <Emphasis Type="Italic">Foton</Emphasis> satellite rotational motion

A new mathematical model of the uncontrolled rotational motion of the Foton satellite is presented. The model is based on the Euler dynamic equations of rigid body motion and takes into account the action upon the satellite of four external mechanical moments: gravitational, restoring aerodynamic, moment with constant components in the satellite-fixed coordinate system, and moment arising due to interaction of the Earth’s magnetic field with the satellite’s proper magnetic moment. To calculate the aerodynamic moment a special geometrical model of the outer satellite shell is used. Detailed form of the formulas giving above-mentioned moments in the equations of satellite motion is agreed with the form of the considered motion. Model testing is performed by determining with its help the rotational motion of the Foton M-2 satellite (it was in orbit from May 31, 2005 to June 16, 2005) using the data of the onboard measurements of the Earth’s magnetic field strength. The use of the new model has led to a relatively small improvement in the accuracy of the motion determination, but allowed us to obtain physically real estimates of some parameters.     

某型号卫星磁环境兼容性分析与控制

某型号卫星的主探测器光电倍增管对卫星的磁环境非常敏感,因此卫星的磁兼容分析和磁设计非常重要。文章结合此卫星的特点对整星的磁场和磁矩等磁兼容性进行了分析计算;对载荷的磁屏蔽方案进行了分析和试验,并根据试验结果给出了磁屏蔽的优化方案;通过分析磁兼容性对姿轨控系统的影响,提出了卫星设计的约束条件,最后给出了磁兼容性分析的结论。     

某型号卫星磁性分析与控制

某型号卫星的有效载荷之一高能望远镜对磁场敏感,因此在设计阶段即需分析卫星在轨时载荷所处的磁场环境,并尽可能提高载荷的抗磁场干扰能力。文章根据卫星的构型,对整星的磁场分布进行了计算;对载荷的抗磁场干扰能力进行了测试;对载荷的磁屏蔽方案进行了仿真与测试;分析了抗磁场干扰设计对整星磁性控制的影响,证明卫星可以满足总磁矩不大于5.0 A?m2的姿态控制要求。     

资源卫星用的高密度数字记录器

资源卫星所用的高密度数字记录器（ＨＤＤＲ）是为资源卫星专门研制的一种新型记录器。该记录器可记录５０Ｍｂ／ｓ的ＮＲＺ－Ｌ信号，记录时间为１５ｍｉｎ，总容量达４．８×１０１０ｂｉｔｓ。本文对该记录器的信道作了系统的介绍。对于作为通用接口的指令、系统、工作原理、电路结构、ＰＲＯＰ码的帧结构、纠错系统、接口指令、运带机构及其设计应考虑的几个因素等作了介绍，最后，给出其指标。结论认为，误差指标远优于用户要求，功耗也比国外同类产品的低，性能优良。     

高精度飞轮控制系统方案分析研究

卫星姿态控制是卫星控制领域里的最重要的一个方面 ,用于保证卫星的正常工作。一般的卫星姿态控制都采用飞轮控制方案 ,所采用的飞轮有磁悬浮飞轮和普通飞轮两种。虽然磁悬浮飞轮能克服飞轮自身摩擦力对卫星姿态的影响 ,但是磁悬浮飞轮在制造、工艺等方面要求高 ,而且成本昂贵。本文讨论了采用直流无刷电机控制普通飞轮的方案中关于转速和电流这两个关键参数的高精度控制问题 ,并给出了实际可行的解决方法。这些方法已在某型卫星上得到了部分应用。     

Determination of attitude motion of the Foton M-2 satellite using the data of onboard measurements of its angular velocity

We present the resutls of a prompt determination of the uncontrolled attitude motion of the Foton M-2 satellite, which was in orbit from May 31 to June 16, 2005. The data of onboard measurements of the angular velocity vector were used for this determination. The measurement sessions were carried out once a day, each lasting 83 min. Upon terminating a session, the data were transmitted to the ground to be processed using the least squares method and integrating the equations of motion of the satellite with respect to its center of mass. As a result of processing, the initial conditions of motion during a session were estimated, as well as parameters of the mathematical model used. The satellite’s actual motion is determined for 12 such sessions. The results obtained in flight completely described the satellite’s motion. This motion, having begun with a small angular velocity, gradually became faster, and in two days became close to the regular Euler precession of an axisymmetric solid body. On June 14, 2005 the angular velocity of the satellite with respect to its longitudinal axis was approximately 1.3 degrees per second, and the angular velocity projection onto a plane perpendicular to this axis had a magnitude of about 0.11 degrees per second. The results obtained are consistent with more precise results obtained later by processing the data on the Earth’s magnetic field measured on the same satellite, and they complement the latter in determination of the motion in the concluding segment of the flight, when no magnetic measurements were performed.     

Magnetic dipole moment estimation and compensation for an accurate attitude control in nano-satellite missions

Nano-satellites provide space access to broader range of satellite developers and attract interests as an application of the space developments. These days several new nano-satellite missions are proposed with sophisticated objectives such as remote-sensing and observation of astronomical objects. In these advanced missions, some nano-satellites must meet strict attitude requirements for obtaining scientific data or images. For LEO nano-satellite, a magnetic attitude disturbance dominates over other environmental disturbances as a result of small moment of inertia, and this effect should be cancelled for a precise attitude control. This research focuses on how to cancel the magnetic disturbance in orbit. This paper presents a unique method to estimate and compensate the residual magnetic moment, which interacts with the geomagnetic field and causes the magnetic disturbance. An extended Kalman filter is used to estimate the magnetic disturbance. For more practical considerations of the magnetic disturbance compensation, this method has been examined in the PRISM (Pico-satellite for Remote-sensing and Innovative Space Missions). This method will be also used for a nano-astrometry satellite mission. This paper concludes that use of the magnetic disturbance estimation and compensation are useful for nano-satellites missions which require a high accurate attitude control.