共查询到19条相似文献,搜索用时 109 毫秒
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用于遥感光谱成像的光谱成像仪普遍存在信息获取慢、光子收集效率低、信噪比低或焦平面阵列大等问题,另外数据立方体庞大的数据量给数据传输造成了极大压力。为了从根本上解决这些问题,文章提出将压缩编码孔径应用于遥感光谱成像中,即压缩编码孔径遥感光谱成像。文章对卫星平台的俯仰、侧滚和偏航运动进行建模,然后利用此模型对成像过程进行仿真和重建,提高了成像品质。由于运动模型以及压缩编码孔径成像技术的引入,使得遥感光谱图像的压缩在成像过程中完成,从而大大提高了传统焦平面阵列的利用率,减小了数据传输的压力,减小了成像光谱仪的体积、质量与成本。 相似文献
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星超光谱成像技术应用及现状分析 总被引:1,自引:0,他引:1
文章介绍了星载起光谱成像技术的基本概念、主要应用目标和原理。综述了起光谱成像技术的国内外发展现状。最后对我国发展超光谱成像技术提出一些建议。 相似文献
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军用卫星超光谱成像技术的发展与应用 总被引:1,自引:0,他引:1
概要分析了卫星超光谱成像技术的发展,论述了超光谱成像技术的概念和应用范围。在简单概括美国空军领域发展之后,重点分析了美国海国和NASA在超光谱成像技术领域的发展与应用。 相似文献
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高光谱遥感技术通过记录地表物体在多个连续波段下的光谱信息,实现高精度的地球观测与分析。为了获取更多地物目标的细节信息,研究人员提出了对高光谱成像系统各项参数指标的新要求,国内外开展了大量相关研究。随着卫星技术的成熟,高光谱遥感平台从最初的机载平台逐渐发展到星载平台,促进了高光谱遥感图像在地质、农林业、环境监测等领域的广泛应用。目前,多数光谱成像系统选用传统的光学器件来实现分光,将计算光学与高光谱遥感结合,有利于集成更紧凑便捷的成像系统。文章首先介绍了高光谱成像系统的主要类型和原理,随后对近30年来典型的星载高光谱成像系统及载荷进行了综述,梳理了典型国内外星载高光谱成像系统的发展现状,并对不同国家成像系统的性能指标进行了对比分析,总结了相应的发展历程,并对未来星载高光谱成像系统的发展作出了展望。 相似文献
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由于干涉成像光谱仪具有高通量、高光谱分辨率和光谱多通道等优点,成为超光谱分辨率遥感方面的研究热点,文章简要分析了国内外的研究现状和干涉成像光谱仪的应用前景,主要介绍时间调制型干涉成像光谱仪和基于变形Sagnac干涉仪、双折射棱镜及Savart板等空间调制型的干涉成像光谱仪的形式、原理和特点,分析了其光学结构和影响光谱分辨率的因素。 相似文献
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小卫星高分辨率成像系统 总被引:1,自引:0,他引:1
对小卫星对地观测高分辨率成像系统进行了综述。介绍了国内外有极高分辨率(0.5~1.0m)、高分辨率(1.8~2.5m)和中高分辨率(4-10m)小卫星光学成像系统的性能,并与合成孔径雷达(SAR)成像系统进行了比较。给出了小卫星光学成像系统、SAR高分辨率成像系统和卫星平台的关键技术。讨论了未来小卫星及其高分辨率成像系统技术的发展趋势。 相似文献
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With rich experience of the successful Indian remote sensing satellite series, Indian Space Research Organization (ISRO) has started theme-based satellites like Resourcesat and Oceansat. Further taking the advantage of the improved technologies in areas of miniaturization, the micro- and mini-satellite series have been started, which will provide opportunity for the payloads of stand-alone missions, for applications, study or research. These include payloads for Earth imaging, atmospheric monitoring, ocean monitoring, scientific applications, and stellar observation. The micro-satellites are of 100 kg class, planned with a payload of about 30 kg and 20 W power and mini-satellites of 450 kg class for payloads of 200 kg and power of 200 W. The first satellite in the micro-satellite series is an Earth imaging payload followed by the second satellite with scientific payloads with the participation of students. Further the scientific proposals for micro-satellites are under evaluation. Similarly the first two missions of mini-satellites are defined with first one carrying ocean and environment monitoring payloads followed by the Earth imaging satellite with multi-spectral camera with 700 km swath. The current paper touches upon the technology involved in realization of the micro- and mini-satellites and the scope of applications of the series. 相似文献
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Science and technology satellite-3 (STSAT-3) is being developed and is scheduled for launch in 2011. One of the primary objectives of its mission is to verify the performance of a hall thruster propulsion system (HPS) that uses xenon gas. According to its major functions, the HPS can be divided into several sub-modules. This paper presents the development and qualification of the hall effect thruster propulsion subsystem that includes a xenon feed system (XFS). The xenon feed system regulates the pressure down from the xenon propellant tank and supplies the xenon flows to the anode and cathode. The technology and xenon feed system developed for the STSAT-3 spacecraft will also be applicable to a variety of future electronic propulsion systems and micro-satellites. Details related to the overall development and performance results of the HPS are presented in this paper. 相似文献
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The development of on-orbit autonomous rendezvous and docking (ARD) capabilities represents a key point for a number of appealing mission scenarios that include activities of on-orbit servicing, automated assembly of modular structures and active debris removal. As of today, especially in the field of micro-satellites ARD, many fundamental technologies are still missing or require further developments and micro-gravity testing.In this framework, the University of Padova, Centre of Studies and Activities for Space (CISAS), developed the Autonomous Rendezvous Control and Docking Experiment (ARCADE), a technology demonstrator intended to fly aboard a BEXUS stratospheric balloon. The goal was to design, build and test, in critical environment conditions, a proximity relative navigation system, a custom-made reaction wheel and a small-size docking mechanism.The ARCADE docking mechanism was designed against a comprehensive set of requirements and it can be classified as small-scale, central, gender mating and unpressurized. The large use of commercial components makes it low-cost and simple to be manufactured. Last, it features a good tolerance to off-nominal docking conditions and a by-design soft docking capability.The final design was extensively verified to be compliant with its requirements by means of numerical simulations and physical testing. In detail, the dynamic behaviour of the mechanism in both nominal and off-nominal conditions was assessed with the multibody dynamics analysis software MD ADAMS 2010 and functional tests were carried out within the fully integrated ARCADE experiment to ensure the docking system efficacy and to highlight possible issues. The most relevant results of the study will be presented and discussed in conclusion to this paper. 相似文献
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航天遥感科学技术的发展 总被引:7,自引:4,他引:3
简要说明了航天遥感和航天遥感系统的概念和组成,特别对航天光学遥感成像链、成像系统和遥感系统的概念和组成做了论述,重点介绍了航天遥感科学技术的发展现状和发展方向,同时提出了发展我国航天遥感科学技术的若干建议。 相似文献
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