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朱建萍 《运载火箭与返回技术》2001,22(4):30-33
文章介绍了CBERS-1卫星红外多光谱扫描仪(IRMSS)主体电控子系统的研制过程,对平衡电阻的引入进行了重点论述。CBERS-1卫星扫描仪主体电控子系统具有体积小、质量轻、功能密度高的特点。 相似文献
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CBERS-1卫星红外多光谱扫描仪图像预处理方法 总被引:1,自引:0,他引:1
文章介绍了中国和巴西联合研制的资源一号卫星 (CBERS_1)上的有效载荷之一 - -红外多光谱扫描仪 (IRMSS)图像数据的处理 ,包括错位校正、相对辐射校正和去除噪声等处理过程。 相似文献
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文章简要阐述了资源卫星的发展与现状 ,概括了资源卫星的主要应用领域和将会带来的巨大经济、社会效益。介绍了CBERS_1卫星CCD相机辐射定标技术 ,分析了CBERS_1卫星CCD相机辐射定标和图像预处理过程 ,展示了经过处理的多光谱图像 相似文献
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扫描角监控器是CBERS_1卫星红外多光谱扫描仪(IRMSS)中的重要部件。文章主要介绍了扫描角监控器的工作原理、主要技术指标以及研制过程中的技术状态、技术难点、关键技术和质量保证。最后对国内外相关的技术项目及经济社会效益情况做了简要对比和分析 相似文献
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文章介绍了CBERS -1卫星红外多光谱扫描仪(IRMSS)关键部件扫描子系统研制与应用情况。 相似文献
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文章介绍了CBERS-1卫星红外多光谱扫描仪(IRMSS)关键部件扫描子系统研制与应用情况。 相似文献
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CBERS-1卫星星载太阳定标器的研制 总被引:2,自引:0,他引:2
文章介绍了CBERS_1卫星IRMSS太阳定标器的主要技术指标要求和工作原理 ,并阐述太阳定标器的设计 ,包括光学设计、机械设计和电学设计等。 相似文献
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介绍了一种新的刚体转动的四元数模型。这些模型可以提高再定向控制的对边界条件的适应能力,在此基础上还介绍了这些模型的一些实际应用。 相似文献
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为满足航天器微振动环境模拟的需要,开展了多自由度微振动时域波形复现控制方法研究。首先,介绍了基于时域波形复现的多自由度微振动环境模拟控制理论方法。其次,针对六自由度微振动激励系统,应用MATLAB软件建立了基于实测传递函数矩阵的多输入多输出微振动激励仿真系统,针对微振动时域波形复现闭环控制过程进行了算法编程,并给出了仿真的闭环控制流程图。最后,通过算例对多自由度微振动时域波形复现进行了数值仿真,以给定的白噪声为输入,模拟对实际存在的系统非线性、测量误差等影响因素的控制效果。仿真结果验证了多自由度微振动时域波形复现控制方法的可行性及有效性,所得结论可以为研究多自由度微振动时域波形复现控制系统提供参考。 相似文献
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The first of a series of problems of the optimization of correction of satellite systems, moving over near-circular orbits, is considered. The correction is accomplished by means of low-thrust engines and is supposed to be flexible, where only the parameters of the relative motion of satellites must be corrected. The problem has a large dimension, but is invariant with respect to renumbering of satellites. This allows us to decompose the problem, i.e., to find new variables, linearly dependent on old ones, in which the problem breaks down into a series of independent subproblems of low dimension. The decomposition is accomplished by means of the technique [1] based on the theory of linear representations of groups. 相似文献
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In the present work, the asymptotic dependence of the reservation multiplicity on the failure danger diminution coefficient in both cases of reservation replacement and continually acting reserver is investigated. The comparison of the method of reservation for different multiplicities with the method of diminution of the failure intensity, related to the mean performance time shows that the decrease of the failure intensity of the plazma engine is the most rational. Nevertheless, there is a value of the time flight for which even a simple duplication is better than arbitrarily large, though finite, failure intensity decrease of the engine. The reliability of coupled MOD-thrusters is verified experimentally. The specific character of the thruster V-I curves and, in particular, their increase in the pubricrcrisis region, yield normally working couples, conformly to many types of feed sources with weakly decreasing of constant V-I characteristics. The parallel connection of a second thruster is shown to double the customed current and, as a consequence the thruster intermediary regimes of the thruster and the dynamics of switching on and by breaking the electric line and stopping the propellant rate flow are investigated. 相似文献
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V. V. Laricheva 《Cosmic Research》2013,51(4):304-314
Properties of differential equations of multi-orbit trajectory motion of a spacecraft are investigated analytically. The spacecraft moves under the action of small perturbations (in particular, low thrust) in the plane of a central Newtonian field of attraction. The conditions are specified for existence of a partial singular aperiodic solution, in the neighborhood of which the behavior of osculating elements changes sharply. In this case, phase variables (the angular position of the pericenter and the true anomaly) are found to undergo the sharpest changes. The exact superposition of solutions is suggested for the equations of motion transformed to the form of a quasi-linear, weakly non-stationary system: a partial singular aperiodic solution and fast solutions oscillating around it. Asymptotic representations are obtained for both components of the superposition. They are fairly exact in the region of smallness of perturbing terms at a long variation of the argument. 相似文献
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G. V. Mozhaev 《Cosmic Research》2001,39(6):594-606
In a previous paper [1], as a result of group-theoretic decomposition, one of the problems of the optimization of the flexible correction process was reduced to a series of subproblems. In this paper, the analytical solutions to these subproblems are obtained by the sweep method. A series of other similar problems with different variants of flexibility is also considered; the decomposition of these problems is performed, and their analytical solutions are presented. It is shown for some numerical examples that flexible corrections require essentially lower fuel consumption than the rigid correction, where all parameters characterizing the absolute motion of a satellite system are corrected to their nominal values. 相似文献
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