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作 者:王斐然 刘磊[1] 任兰旭 代锋[3] WANG Feiran;LIU Lei;REN Lanxu;DAI Feng(School of Astronautics,Northwestern Polytechnical University,Xi'an 710072,China;Xi'an Satellite Control Center,Xi'an 710000,China;Xi'an Institute of Space Radio Technology,Xi'an 710000,China)
机构地区:[1]西北工业大学航天学院,西安710072 [2]西安卫星测控中心,西安710000 [3]西安空间无线电技术研究所,西安710000
出 处:《中国空间科学技术(中英文)》2024年第2期164-170,共7页Chinese Space Science and Technology
基 金:国家自然科学基金(52075446,51675430)。
摘 要:针对传统多载荷遥感卫星系统集成度低的问题,提出一种共结构大口径微波与光学一体化空间成像方法,即采用微波、光学成像系统共用卡塞格伦结构的一体化载荷设计,并通过波长分光镜对接收信号进行分光成像。载荷主反射面结构为微波天线和多光学反射镜组成的抛物面,其中光学主镜系统采用婓索干涉Golay6分布式结构组成非连续抛物面,并采用模块化设计将成像载荷进行拼接。模块化设计易于大口径微波与光学成像结构的加工、装配,相较传统多载荷卫星载荷集成度更高,系统更加简化。通过Matlab和Zemax软件对一体化空间载荷进行仿真分析,结果表明,所设计的大口径微波与光学一体化空间成像载荷,满足微波成像的最小有效面积要求和光学成像的调制传递函数(MTF)值要求。Aiming at low integration of traditional multi-load remote sensing satellite systems,a kind of common structure large aperture microwave-optical integrated space imaging method was proposed.The Cassegrain load structure was designed to be shared by microwave-optical imaging systems.The received signal was split and imaged through the wavelength splitter.The main reflector structure of the load was a paraboloid composed of microwave antenna and multi optical reflectors.The optical primary mirror system was composed of discontinuous paraboloid with the distributed structure of Fizeau interference Golay6,and the imaging loads were spliced with modular design.The modular design was easy for the large aperture structures to be processed and assembled.Compared with the traditional multi-load satellite,the modular design is more integrated and the system more simplified.The simulation analysis of the integrated space load was carried out through Matlab and Zemax.The results show that the load meets the requirements of the minimum effective area of microwave imaging and the modulation transfer function(MTF)value of optical imaging.
分 类 号:V11[航空宇航科学与技术—人机与环境工程]
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