Orbital stability close to asteroid 624 Hektor using the polyhedral model

We investigate the orbital stability close to the unique L4-point Jupiter binary Trojan asteroid 624 Hektor. The gravitational potential of 624 Hektor is calculated using the polyhedron model with observational data of 2038 faces and 1021 vertexes. Previous studies have presented three different density values for 624 Hektor. The equilibrium points in the gravitational potential of 624 Hektor with different density values have been studied in detail. There are five equilibrium points in the gravitational potential of 624 Hektor no matter the density value. The positions, Jacobian, eigenvalues, topological cases, stability, as well as the Hessian matrix of the equilibrium points are investigated. For the three different density values the number, topological cases, and the stability of the equilibrium points with different density values are the same. However, the positions of the equilibrium points vary with the density value of the asteroid 624 Hektor. The outer equilibrium points move away from the asteroid’s mass center when the density increases, and the inner equilibrium point moves close to the asteroid’s mass center when the density increases. There exist unstable periodic orbits near the surface of 624 Hektor. We calculated an orbit near the primary’s equatorial plane of this binary Trojan asteroid; the results indicate that the orbit remains stable after 28.8375?d.     

Summary of CNCOSPAR Activities 2002-2004

1 In Brief In this report, we summarize the major activities of CNCOSPAR from the year 2002to 2004. During this period, many things happened such as Beijing won the 2006COSPAR scientific assembly, the first Chinese Committee of COSPAR handed over its responsibility to the second committee, etc. During this period, the space science activities developed also very fast. China has sent its first scientific satellite, the first satellite TC-1 of the Double Star Program, into space. China also has a major break through in the manned space flight by a very successful mission of Shenzhou manned space flight. On board of this spacecraft, is the first Chinese astronaut Mr. Liwei Yang. This made China the third country in the world who has the ability that the launch manned space missions independently.     

减小固体火箭外壳板滚弯直线度误差的研究

如何减小固体火箭外壳板滚弯直线度误差是目前火箭生产工艺中的难题,在对最不利实际工况下三轴辊弯板机中心辊进给量沿自身轴线分布规律作系统的分析、计算及研究的基础上,推导出一项箭壳板滚弯直线度误差不等式,并针对此项不等式各参数变化规律,提出几项减小箭壳板滚弯直线度误差的行之有效的措施,可供火箭外壳设计及生产工艺人员参考。     

Sustained data recording system based on disk array

Most sustained data recording systems in many real-time fields are based on tape equipments. We have developed an innovative sustained data recording system based on disk array which consists of Array Controller Module (ACM), String Controller Module (SCM) and Main Controller Module (MCM). This system has a better performance and higher reliability than the traditional tape recorder and can be used conveniently in many areas of data recording, storing, playback, and remote backup. This novel recording system has been used in radar data recorder for spacecraft orbit tracking and satellite remote sensing data recording successfully.     

民航机场建立呼叫中心的作用及实施对策

论文介绍了呼叫中心的技术原理，在分析民诱机场商务活动的现状的基础上，阐述了呼叫中心的特点及其在机场经营业务中的作用，提出了民航机场呼叫中心的模型，最后论述了民航机场实施呼叫中心的对策。     

VKM—5型立式捏合机研制与应用

介绍自行研制的VKM—5型立式捏合机的构造及工作原理,详述了该机采用液压传动和气动元件进行位置检测以及气、电、液安全联锁的特点,并说明与卧式捏合机对比试验情况。     

计算机帧时间对半实物仿真的影响

半实物仿真试验中,要求计算机帧时间与计算积分步长相一致,但在实际试验中不容易精确地做到。本文分析了这种不一致给半实物仿真试验带来的影响,给出了解决的办法,文章中还给出了一实例来说明。     

项目教学法在《微机系统实现与维护》课程教学中的应用探索

项目教学法突破传统的教学模式,在参与项目完成的过程中学生能更好、更快地掌握所学知识,学习的积极性和主动性大大提高。本文将项目教学法的学习模式引入到高职高专的《微机系统实现与维护》课程教学中,对如何把理论与实践有机地结合,如何提高学生的技能水平作了一定的探索。     

英语课堂教学中学生的厌烦心理及其分析

分析英语课堂教学中学生厌烦心理，转变教学观念，培养学生学习兴趣，真正发挥课堂教学的作用。     

故障检测与分离的广义一致性算子法

本文提出了故障检测与分离的广义一致性算子法的一般形式。得出了两个故障可分离的充要条件和多个故障可分离的充要条件。最后给出了检测和分离故障的过程。