航天超光谱成像技术原理及其发展现状

介绍了国际航天超光谱成像仪的发展状况,简要分析了光栅型超光谱成像仪和干涉型超光谱成像仪的原理,并对我国发展航天超光谱成像遥感技术提出了建议。     

航天超光谱成像仪原理分析

介绍了国内外航天超光谱成像仪的研制概况,主要分析介绍了光栅型超光谱成像仪和干涉型超光谱成像仪的原理,并指出了需要进一步研讨的问题。     

Mighty-Ⅱ星载干涉型超光谱成像仪

介绍了美国研制的 Mighty-Ⅱ卫星载干涉型超光谱成像仪,主要内容包括卫星发射前后的校准结果、在轨性能,以及该超光谱成像仪在设计寿命内的有关数据。它是第一台在轨成功使用的超光谱成像仪。     

超光谱成像仪成像电路的设计与实现

超光谱成像仪是环境减灾-1A卫星的主载荷之一,也是我国第一台采用静态干涉型光谱成像技术的星载遥感相机。成像电路是超光谱成像仪的核心组件之一,文章介绍了超光谱成像仪成像电路的系统组成,以及各功能模块的结构、功能和设计原理。     

星载高光谱成像仪数据地面预处理系统设计

环境与灾害监测预报小卫星星座A星(简称环境-1A卫星,HJ-1A)上搭载的高光谱成像仪(HSI)是我国第一个对地成像的干涉成像光谱仪,具有多谱段、高光谱分辨率的优点.针对高光谱成像仪的特点,设计了星载高光谱成像仪数据地面预处理系统.该系统由产品生产、质量检测和定标处理单元组成,集成了高光谱成像仪数据完整性处理、背景处理...     

超光谱成像仪的实验室定标

星载超光谱成像仪是一种空间调制型干涉光谱成像仪,文章研究了一套适用于干涉成像光谱仪、具有一定精度的实验室定标方法,满足了超光谱成像仪的实验室定标要求。采用激光光源进行光谱定标,光谱定标精度优于2nm。用远距点光源光路进行CCD探测器像元响应不均匀性修正,并进一步用天空背景光或均匀平行光进行全系统光能传输不均匀修正,实现了干涉图平场,相对定标精度达到2.46%。采用太阳模拟光源和均匀平行光路,用光谱辐射度计（ASD）实现标准辐射亮度的传递进行光谱辐射度定标,绝对定标精度达到8.21%。     

基于光谱特性的高光谱图像压缩方案

根据干涉型高光谱成像仪成像特点,提出了一种针对干涉型光谱仪所获得高光谱图像的基于光谱特性的图像压缩方案。由于光谱信息最终从“点”十涉图像中恢复,因此方案中首先通过高精度匹配技术将原始“像面”干涉图像序列“重组”成“点”干涉图像,然后针对“点”干涉图像序列进行压缩。在重组过程中采取基于光流的亚像素级匹配和基于梯度的三角插值算法,实现了高精度的图像匹配重组;在压缩环节利用“点”干涉图像与光谱信息之间的傅立叶变换关系,提出一种能够很好保持频谱特性的基于一维DCT的压缩算法。实验证明,压缩算法总体性能远高于针对“像而”干涉圈序列的压缩算法．很好地控制了光谱信息的失真。     

环境减灾-1A卫星空间调制型干涉光谱成像仪技术

介绍了空间调制型干涉光谱成像技术的基本原理,结合为环境与灾害监测测预报小卫星研制的超光谱成像仪总体方案,阐述了该类仪器的主要技术参数设计方法,以及光学、机械、电子、定标和数据复原处理等环节的关键技术,给出了仪器在轨运行获得的部分超光谱数据,以及仪器的应用潜力.     

环境-1A超光谱成像仪相对辐射定标方法应用研究

介绍了环境-1A卫星上装载的新型有效载荷超光谱成像仪的工作原理。指出我国使用超光谱干涉仪尚处于试验阶段,对在轨数据处理方法还需要完善。文章针对干涉仪的数据立方体特性提出一种空间维的基于统计方法的在轨干涉数据相对辐射定标处理方法,并通过对卫星实际在轨数据的对比处理来验证其处理效果。结果表明,相对辐射定标处理可以修正CCD响应的不均匀性和入射光场的不均匀性,减小非线性相位偏移,提高复原光谱的精度。     

星载高光谱成像仪在轨偏航定标方法

高光谱成像仪以其纳米级光谱分辨率可同时获取地物的图像和光谱信息,辐射定标的精度是其定量化应用的关键环节,而偏航定标降低了对定标场地的选择要求,为高光谱成像仪在轨高频次定标提供了支撑。文章提出一种基于卫星平台90°偏航机动的高光谱成像仪在轨偏航定标方法,包括偏航数据的获取及数据处理、分析方法。基于资源一号02D卫星在轨数据对此方法进行了验证,结果表明:该方法对高光谱成像仪的相对辐射校正具有良好的效果,探测器所有像元相对辐射定标精度可达1%,原始图像中的条纹噪声得到很好去除。文章提出的方法可以实现高光谱成像仪的高频次、全视场相对辐射校正,为后续高光谱数据的定量化应用打下基础。     

“中华卫星一号”及其海洋水色成像仪

介绍了中国台湾研制的“中华卫星一号”（ＲＯＣＳＡＴ－１）实验卫星的概况。较详细介绍该卫星上的海洋水色成像仪的构成、主要性能。给出了“中华卫星一号”及其海洋水色成像仪外形图和结构图。     

FY-4 Meteorological Satellite

FY-4 is the second generation of Chinese geostationary satellite for quantitative remote sensing meteorological application. The detection efficiency, spectral bands, spatial and time resolution have been greatly improved with respect to those of first generation, as well as the radiometric calibration and sensitivity. The combination of multichannel detection and vertical sounding was first realized on FY-4, because both the Advanced Geostationary Radiation Imager(AGRI) and Geostationary Interferometric Infrared Sounder(GIIRS) are on the same spacecraft. The main performance of the payloads including AGRI, GIIRS and Lightning Mapping Imager, and the spacecraft bus are presented, the performance being equivalent to the level of the third generation meteorological satellites in Europe and USA. The acquiring methods of remote sensing data including multichannel and high precision quantitative observing, imaging collection of the ground and cloud, vertical observation of atmospheric temperature and moisture, lightning imaging observation and space environment detection are shown. Several innovative technologies including high accuracy rotation angle detection and scanning control, high precision calibration, micro vibration suppression, unified reference of platform and payload and on-orbit measurement, real-time image navigation and registration on-orbit were applied in FY-4.     

Selected configuration tradeoffs of contour optical instruments

The Comet Nucleus Tour (CONTOUR) is a low-cost NASA Discovery mission designed to conduct three close flybys of comet nuclei. Selected configuration tradeoffs conducted to balance science requirements with low mission cost are reviewed. The tradeoffs discussed focus on the optical instruments and related spacecraft considerations. Two instruments are under development. The CONTOUR Forward Imager (CFI) is designed to perform optical navigation, moderate resolution nucleus/jet imaging, and imaging of faint molecular emission bands in the coma. The CONTOUR Remote Imager and Spectrometer (CRISP) is designed to obtain high-resolution multispectral images of the nucleus, conduct spectral mapping of the nucleus surface, and provide a backup optical navigation capability.Tradeoffs discussed are: (1) the impact on the optical instruments of not using reaction wheels on the spacecraft, (2) the improved performance and simplification gained by implementing a dedicated star tracker instead of including this function in CFI, (3) the improved flexibility and robustness of switching to a low frame rate tracker for CRISP, (4) the improved performance and simplification of replacing a visible imaging spectrometer by enhanced multispectral imaging in CRISP, and (5) the impact on spacecraft resources of these and other tradeoffs.     

Design and implementation of the flight dynamics system for COMS satellite mission operations

The first Korean multi-mission geostationary Earth orbit satellite, Communications, Ocean, and Meteorological Satellite (COMS) was launched by an Ariane 5 launch vehicle in June 26, 2010. The COMS satellite has three payloads including Ka-band communications, Geostationary Ocean Color Imager, and Meteorological Imager. Although the COMS spacecraft bus is based on the Astrium Eurostar 3000 series, it has only one solar array to the south panel because all of the imaging sensors are located on the north panel. In order to maintain the spacecraft attitude with 5 wheels and 7 thrusters, COMS should perform twice a day wheel off-loading thruster firing operations, which affect on the satellite orbit. COMS flight dynamics system provides the general on-station functions such as orbit determination, orbit prediction, event prediction, station-keeping maneuver planning, station-relocation maneuver planning, and fuel accounting. All orbit related functions in flight dynamics system consider the orbital perturbations due to wheel off-loading operations. There are some specific flight dynamics functions to operate the spacecraft bus such as wheel off-loading management, oscillator updating management, and on-station attitude reacquisition management. In this paper, the design and implementation of the COMS flight dynamics system is presented. An object oriented analysis and design methodology is applied to the flight dynamics system design. Programming language C# within Microsoft .NET framework is used for the implementation of COMS flight dynamics system on Windows based personal computer.     

基于实验室定标和均匀景统计的相对辐射定标方法

提出了一种基于实验室定标和均匀景统计的定标方法,并应用于CBERS-02卫星遥感图像相对辐射校正。首先分析宽视场成像仪(Wide Field Imager,WFI)实验室基础定标系数;然后结合均匀景的定标方法,生成一组新的相对辐射定标系数;最后评价WFI图像相对辐射校正的效果。结果表明:文章提出的定标方法有效,可以较好地解决宽幅遥感图像辐射校正问题,同时为遥感卫星相对辐射校正提供了一种新的途径。     

Instantaneous Real-Time Detection Technology of GLI on FY-4 Geostationary Meteorological Satellite

Lightning is a typical example of an instantaneous random point source target. It has close connection with severe convective phenomena such as a thunderstorm, whose distribution, variation, position and forecasting can be acquired through lightning observation. In this paper, we discuss the way to achieve instantaneous lightning signal intensification and detection from geostationary orbit by using the differences between the lightning signal and the slowly changing background noise such as that of cloud, land and ocean, combining three methods, spectral filtering, spatial filtering and background noise, enabling removal between frames. After six months of operation in orbit, lightning within the coverage of the Geostationary Lightning Imager was effectively detected, strongly supporting the case for shorttime and real-time early warning, forecasting and tracking of severe convective phenomena in China.     

Identification of dust outbreaks on infrared MSG-SEVIRI data by using a Robust Satellite Technique (RST)

Dust storms are meteorological phenomena of great interest for scientific community because of their potential impact on climate changes, for the risk that may pose to human health and due to other issues as desertification processes and reduction of the agricultural production. Satellite remote sensing, thanks to global coverage, high frequency of observation and low cost data, may highly contribute in monitoring these phenomena, provided that proper detection methods are used.In this work, the known Robust Satellite Techniques (RST) multitemporal approach, used for studying and monitoring several natural/environmental hazards, is tested on some important dust events affecting Mediterranean region in May 2004 and Arabian Peninsula in February 2008. To perform this study, data provided by the Spinning Enhanced Visible and Infrared Imager (SEVIRI) have been processed, comparing the generated dust maps to some independent satellite-based aerosol products. Outcomes of this work show that the RST technique can be profitably used for detecting dust outbreaks from space, providing information also about areas characterized by a different probability of dust presence. They encourage further improvements of this technique in view of its possible implementation in the framework of operational warning systems.     

Detection of volcanic gases and particles by satellite

In this paper the detection of components of volcanic eruption has been carried out investigating, in appropriate bands of the electromagnetic spectrum (6.25, 8.7, 10.8, 12 μm), the values of the brightness temperature. The analysis has been performed in the Thermal Infrared Region (TIR) studying both the absorption–emission and scattering phenomena related to the interactions between electromagnetic radiation and volcanic emissions. The results have been achieved by means of a combined use of numerical simulations, devoted to examining the behaviour of the atmosphere gases and volcanic components, and remotely sensed satellite images. The proposed methodologies allow an estimate of the amount of gaseous and solid components, of the size of the emitted particles, of the height of the volcanic plume and of the distance of the volcanic components from the crater. The processed images come from the Spinning Enhanced Visible and InfraRed Imager (SEVIRI) sensor on board the geo-stationary satellite Meteosat Second Generation (MSG) and take into consideration an eruption of the Etna volcano as a study case (1st of April 2012, 04:30 and 05:30 UTC). The procedures are general and may therefore be extended to any other similar case.     

Sunspot oscillations as derived from the <Emphasis Type="Italic">SOHO</Emphasis>/MDI magnetograms

As a result of processing long (up to 144 h) series of sunspot magnetograms obtained on the SOHO (Solar and Heliospheric Observatory) spacecraft with the MDI (Michelson Doppler Imager) instrument it is shown that the mode with a period of 800–1300 min is a limiting low-frequency oscillation mode of the magnetic field of a sunspot as a whole. Its period is essentially and nonlinearly depends on the sunspot magnetic field strength. In addition to this mode, higher harmonics are also revealed in the sunspot oscillation spectra in the bands 40–45, 60–80, 135–170, 220–250, and 480–520 min. The oscillation power in these bands monotonically and rapidly decreases with increasing frequency, which is characteristic for overtones arising due to the nonlinear nature of oscillations. The limiting oscillation mode stably exists in sunspots for 1.5–2 days, which coincides with the average lifetime of a supergranular cell. The mode with the period of 35–48 h observed in the power spectrum is not an eigen mode of sunspots, because its period is independent of its magnetic field strength. Probably, it occurs as a quasiperiod of an external exciting force caused by disturbances from supergranular cells surrounding the sunspot.     

航天电子产品的工艺设计

文章论述了航天电子产品在工程设计过程中工艺设计的重要性，以及在产品设计中融入工艺设计概念后具体设计及相关内容。围绕设计、工艺、装联实践中的具体情况，提出了设计中应注意的问题。