低轨小型卫星的发展和应用

本文介绍低轨小卫星的发展和应用前景。低轨小卫星,体积和重量小,轨道低,功能单一,智能化,制造和发射都很容易,投资费用低,受到用户的普遍欢迎,有广阔的发展和应用前景。 小卫星在近几年发展迅速,应用广泛,已经受到世界各国的重视。在许多方面,已经应用小卫星和计划中应用小卫星的例子很多,本文只作简要介绍,目的在于引起人们的重视,发展我国的小卫星事业。     

Interferometric monitoring of satellite longitudes

This paper proposes a technique for monitoring the longitudinal motion of geosynchronous satellites. A two‐antenna interferometer is used, with the baseline orientation adjusted to a particular horizontal azimuth. The interferometer then becomes insensitive to the north–south motion of the satellite, and this enables direct measurement of the satellite's longitudinal motion. Longitudes are monitored continuously, with no delay when orbital manoeuvres occur. The proposed technique is particularly useful when two or more satellites are operating in close proximity and their longitudes must be precisely monitored for safety control. Copyright © 2005 John Wiley & Sons, Ltd.     

中国的三种非同步轨道卫星移动通信系统星座方案

本文介绍基于我国的三种非同步轨道卫星移动通信系统星座方案：低、中轨系统各有２４和１８颗星，轨道高度分别为１３２６和８０３５ｋｍ，两系统各以５°和３０°的仰角对我国的覆盖率为９９．７８％和９９．９６％；椭圆轨道系统１２颗星，近、远地点分别为４２７和２９０６ｋｍ，以７°和１５°仰角对我国北纬２０°以上地区覆盖率分别为９７．９０％和８９．６１％，若增加４颗中轨卫星，以１５°仰角对我国的覆盖率为９９．９９％。     

Design,Implementation, and Validation of KOMPSAT‐2 Software Simulator

In this paper, we present design features, implementation, and validation of a satellite simulator subsystem for the Korea Multi‐Purpose Satellite‐2 (KOMPSAT‐2). The satellite simulator subsystem is implemented on a personal computer to minimize costs and trouble on embedding onboard flight software into the simulator. An object‐oriented design methodology is employed to maximize software reusability. Also, instead of a high‐cost commercial database, XML is used for the manipulation of spacecraft characteristics data, telecommand, telemetry, and simulation data. The KOMPSAT‐2 satellite simulator subsystem is validated by various simulations for autonomous onboard launch and early orbit phase operations, anomaly operation, and science fine mode operation. It is also officially verified by successfully passing various tests such as the satellite simulator subsystem test, mission control element system integration test, interface test, site installation test, and acceptance test.     

星间激光通信技术进展与趋势

较详细地评述了目前国外卫星间光通信技术研究的现状．根据关键单元技术的进展情况，总结了未来星间光通信系统的发展趋势。     

卫星编队飞行中的队形设计研究

目前关于卫星编队飞行的研究有显著的增加。多颗从属卫星(从星)在近距离内与主卫星(主星)组成特定的队形以完成相应的任务,是卫星编队飞行的特点及潜在优势。卫星在编队飞行时,其队形定义为以各颗卫星质心为顶点所构成的几何形状,而队形设计则是根据队形的几何形状求出各卫星的轨道根数(其中主星的轨道根数可以根据任务的要求事先确定)。基于相对轨道根数法,根据卫星相对运动方程,提出了“自然队形”的概念及队形设计的一般方法,并给出了具体的例子。     

大型桁架展开机构热控涂层设计和热变形分析

为控制大型桁架展开机构在低地轨道(Low Earth Orbit,LEO)上的热变形,建立相应的热分析有限元模型,提出3种热控涂层备选方案.根据不同方案计算出机构在LEO上运行4个周期的瞬态温度场,并以最后一个周期的瞬态温度场为基础计算机构的热变形.对热变形的结果进行比较,选取变形值最小的热控涂层方案进行优化,使3根主梁的温差达到最小,从而有效控制桁架展开机构的热变形.     

A New Derivation of the Cubature Kalman Filters

This paper investigates the cubature Kalman filtering (CKF) for nonlinear dynamic systems. This third‐degree rule based filter employs a spherical‐radial cubature rule to numerically compute the integrals encountered in nonlinear filtering problems, thereby removing the requirements of explicitly computing the Jacobians. The cubature rule, however, requires computing the intractable integrals over a high‐dimensional spherical region for multidimensional applications. Moreover, the cubature formula that has been used to construct the spherical cubature formula has some demerits, most notably its inconvenient properties in computation and low estimation accuracy. Aimed at these issues, a general class of CKFs that uses only cubature rules is derived in this paper. It can be shown that the conventional CKF is a special case of the proposed algorithm. The paper also includes higher‐degree CKFs, especially two representative types of the fifth‐degree CKFs. Performance of the proposed algorithms is demonstrated via two target tracking problems. The experimental results, presented herein, illustrate the superior performance of higher‐degree CKFs to conventional nonlinear filters.     

激光推进用于飞行器姿轨控制的分析与仿真

激光推进成本低、可靠性高,可用作飞行器的空间推进和姿态调整。建立了考虑反馈控制和激光推进的飞行器动力学模型,模型中的操纵控制项模拟了飞行器操纵系统和激光推进产生的力、力矩。详细研究了确定操纵项的方法,使用自适应飞行控制律,给出一种通过求解线性方程组确定操纵控制项的方法。以圆形盘旋轨迹为例,进行了数值模拟,计算结果显示,激光推进下的飞行器能很好按照目标轨迹飞行,并对计算结果进行了分析。     

基于NSGA-Ⅱ算法的轨道转移优化方法研究

在普适变量法求解Lambert转移问题基础上,提出基于NSGA-Ⅱ（non-dominated sorting genetic algorithm-Ⅱ）算法的轨道转移时间-能量优化问题解决方法：通过修改非优超排序方法和采用空间扩张策略对NSGA-Ⅱ算法进行了改进,运用约束支配的概念解决了约束条件下Pareto最优集分层困难的问题。仿真实验表明：改进的NSGA-Ⅱ算法能有效求解轨道转移时间-能量优化问题,且比原算法提高了Pareto前沿散布性能。