THE APPLICATION OF SATELLITE POSITIONING TECHNOLOGY AND ITS INDUSTRIALIZATION IN CHINA

Satellite positioning technology has been widely used in all kinds of military and civil land, marine, space and aeronautical target positioning tasks, naviga tion activities and accurate surveying measurements since 90 s in the last cen tury due to its advantage in providing all-weather, real-time, three dimensional and high precision positioning information, as well as speed and accurate timing information. By now, it has already formed a new hi-tech industry basically.This paper briefly reviews the development of the global satellite positioning and navigation technologies including the basic information of China's "Plough navigation system", introduces the history of satellite positioning technology and its major application fields as well as the status quo of this being industri alized trade in China, gives an account of the writers' vision for the application and prospect of the satellite positioning technologies in China, and approaches the tactics and stresses of the satellite positioning technology's application and its industrialization future in China.     

Trajectory Tracking Control for a GMM Actuator Based on a Heuristic ILC Method

A heuristic iterative learning control （ILC） method is presented and applied to the trajectory tracking control of a giant magnetostrictive material （GMM） actuator. A GMM actuator is used as experimental equipment for micro-displacement trajectory tracking control. The advantage of the presented approach lies in quitting the model of the GMM actuator. The experimental results attest to the high efficiency of the presented method for the micro-displacement trajectory tracking control.     

Needs and Tools for Future Gravity Measuring Missions

This paper compares the requirements that can be expected of gravity measuring missions with respect to the status of the instrumentation and satellite technologies. The error sources of gravity gradiometry and satellite-to-satellite tracking are analysed and the elements limiting the accuracy are identified. Proposed and approved future missions that will fly technologies of interest for gravity sensing are recalled. Areas of technical development of interest are reviewed. The article finishes with two possible conceptual missions presented as examples and with a chapter of conclusions. This revised version was published online in August 2006 with corrections to the Cover Date.     

Ocean Tides in GRACE Monthly Averaged Gravity Fields

The GRACE mission will map the Earth's gravity fields and its variations with unprecedented accuracy during its 5-year lifetime. Unless ocean tide signals and their load upon the solid earth are removed from the GRACE data, their long period aliases obscure more subtle climate signals which GRACE aims at. In this analysis the results of Knudsen and Andersen (2002) have been verified using actual post-launch orbit parameter of the GRACE mission. The current ocean tide models are not accurate enough to correct GRACE data at harmonic degrees lower than 47. The accumulated tidal errors may affect the GRACE data up to harmonic degree 60. A study of the revised alias frequencies confirm that the ocean tide errors will not cancel in the GRACE monthly averaged temporal gravity fields. The S₂ and the K₂ terms have alias frequencies much longer than 30 days, so they remain almost unreduced in the monthly averages. Those results have been verified using a simulated 30 days GRACE orbit. The results show that the magnitudes of the monthly averaged values are slightly higher than the previous values. This may be caused by insufficient sampling to fully resolve and reduce the tidal signals at short wavelengths and close to the poles. This revised version was published online in August 2006 with corrections to the Cover Date.     

固体运载火箭弹道设计与优化

本文针对采用固体火箭发动机卫星的陆基多级固体运载火箭弹道进行了详细的阐述，提出了适合固体运载火箭弹道计算和弹道优化的方法，该方法适用于方案论证和初步弹道计算。     

滑翔飞行器弹道规划与制导方法综述综述

滑翔飞行器以其突出的机动突防能力、高精度打击以及全球快速可达等优势成为当下航空航天领域研究热点。作为控制飞行器可靠执行既定飞行任务的核心部分,弹道规划与制导方法是关注的焦点。概述当前滑翔飞行器弹道规划与制导方法,尤其是基于标准剖面和基于预测校正思想的弹道规划与制导方法的研究现状。进一步,分析当下滑翔飞行器弹道规划与制导方法的研究热点与难点,并结合人工智能,对滑翔飞行器弹道规划与制导方法未来可能的发展趋势进行了展望。     

基于高分四号数据的多时相多通道云检测算法

针对高分四号（GF-4）卫星影像波段较少导致传统云检测算法难以区分云与冰雪像元的问题,提出一种多时相多通道云检测算法。该算法首先对GF-4卫星影像进行辐射定标和配准,然后利用云与典型地表的光谱差异得到潜在云像元,之后利用序列GF-4卫星影像之间的差异识别出移动的云像元,最后利用中红外波段反演地表亮度温度来去除冰雪像元。该算法在海南、辽宁和安徽3个研究区域进行验证,并将检测结果与传统单时相云检测算法、支持向量机（SVM）云检测算法和实时差分（RTD）云检测算法的检测结果进行对比。结果表明,该算法优于其他3种云检测算法,准确识别率均达到90%以上,误检率均低于5%,有利于GF-4卫星影像的进一步利用。     

基于DTW的HJ-1B卫星地表温度产品质量检验

HJ-1B卫星热红外数据应用广泛,但其地表温度反演产品的质量检验工作尚不完善。以黑河流域为研究区,利用普适性单通道算法得到HJ 1B地表温度,基于7个地面站点（下垫面为荒漠、沙漠、植被、农作物、雪地和湿地）同步观测资料和MODIS地表温度产品（MOD11A1）,引入动态时间规整方法（DTW）对站点处HJ 1B地表温度进行验证。试验结果表明：HJ 1B地表温度反演产品与地面观测值的偏差值在沙漠和荒漠站点为1K以内,均方根误差在05K左右;对于植被和农作物站点的偏差在2K以内,均方根误差为1~2K;基于DTW的验证对时序不匹配的数据评价结果与现有指标表现一致。HJ-1B地表温度反演产品与地面站点的相对偏差均低于其与MODIS地表温度反演产品的相对偏差。     

六面体小微卫星散热面最优化设计

以散热面吸收外热流最小为目标函数,建立了基于六面体卫星的散热面最优化设计模型,并以某倾斜轨道六面体小微卫星为例、针对不同卫星热耗分别得出了最优化的散热面布局。计算结果表明:采用文章所述的最优化设计方法得到的散热面布局,可以有效降低由于卫星吸收外热流变化造成的整星温度的波动,可以为六面体卫星散热面的优化设计提供理论支持;进一步分析表明,不同热耗水平的卫星对应不同的最优化散热面布局。     

一种在轨卫星质量特性计算方法

提出一种基于交互式迭代和批量最小二乘法的在轨质量特性计算方法,仅使用陀螺作为敏感器,动力学模型适用于零动量和偏置动量两种控制模式,考虑了卫星与飞轮动量交换以及参数之间耦合关系,且能够适用于在轨不进行连续大角度姿态机动的卫星。计算结果表明,此方法具有快速、稳定的收敛特性和较高的计算精度。