共查询到16条相似文献,搜索用时 416 毫秒
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利用参照轨道要素研究卫星星座/编队的几何特征 总被引:1,自引:0,他引:1
星座/编队的对地遥感应用要求对卫星群的空间几何特征进行量度和评价。定义了用于刻画卫星星下点球面几何特征的两个指标:平均星间角距和星下点分布面积。作为星下点分布的一维量度,星间角距可由参照轨道要素解析地表达。继而给出星下点最小凸球面多边形的判定算法;与传统方法不同,该算法无需求解星下点坐标即可判定星下点几何特征,进而计算卫星分布面积,作为星下点几何特征的二维表征。最后以四星编队任务为例,通过计算判定星下点几何,分析了编队轨道设计要素与编队几何特征的半定量关系。 相似文献
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大偏心率远距离航天器编队飞行设计 总被引:1,自引:0,他引:1
为寻求适用于大偏心率远距离航天器编队设计的方法,摒弃了简化航天器相对运动非线性微分方程的传统思路,致力于简化该微分方程的解析解。首先,在同周期假定前提下,由运动学得到了椭圆轨道航天器相对于圆轨道航天器运动的封闭解析解,然后将其展开成傅立叶级数,证明了在特定条件下,单倍频项是最主要的,从而导出了编队飞行设计的新公式。最后以空间圆形编队设计为例,阐明了利用新公式进行编队设计的步骤,并用精确的数值计算验证了设计结果的正确性。与C-W方法和一般轨道参数设计方法相比,推导过程中并未采用小偏心率近距离假定,因此导出的新公式可适用于大偏心率远距离航天器的编队设计。 相似文献
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C. A. Markland 《Sadhana》1980,3(1):47-65
This paper gives a broad introduction to the problems of attitude and orbit control of geostationary communications satellites.
It specifically discusses the relationships between the satellite user’s requirements for a broadcasting mission and the design
of the attitude and orbit control system.
To put the subject in perspective, a brief review of past and present satellites is presented first. Then orbit control is
described in terms of the forces that act on a satellite in geostationary orbit and the necessary station-keeping strategies.
The design of attitude control systems for three-axis stabilised satellites is presented by considering the disturbance torques,
attitude sensors and actuators and by identifying the various system problems and their solutions. Sources of error in pointing
the satellite towards the earth are discussed together with the formulation of error budgets. Finally, the design approach
for missions that require extremely accurate pointing is considered, and some remarks are given regarding the achievable accuracy
for this class of satellite missions. 相似文献
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Mokhov NV Rakhno IL Striganov SI Peterson TJ 《Radiation protection dosimetry》2005,116(1-4 PT 2):224-227
In order to investigate the degradation of optical detectors of the Supernova Acceleration Project (SNAP) space mission because of irradiation, a three-dimensional model of the satellite has been developed. A realistic radiation environment at the satellite orbit, including both galactic cosmic rays and cosmic ray trapped in radiation belts, has been taken into account. The modelling has been performed with the MARS14 Monte Carlo code. In a current design, the main contribution to dose accumulated in the photo-detectors is shown to be due to trapped protons. The contribution of primary alpha particles is estimated. Predicted performance degradation for the photodetector for a four-year space mission is 40% and this can be reduced further by means of shielding optimisation. 相似文献
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Rapid tooling (RT) processes driven by rapid prototyping (such as stereolithography and selective laser sintering) can reduce mold development lead-time by 50% or more, though there are certain limitations in terms of mold materials, accuracy, and surface finish. This paper presents a systematic approach for manufacturability analysis of molds produced by rapid tooling methods, based on three aspects: mold feature manufacturability, secondary elements compatibility, and cost effectiveness. The geometric features of functional elements of the mold (core, cavity, side core, etc.) are evaluated for manufacturability using fuzzy-analytic hierarchy process (Fuzzy-AHP) methodology. The secondary elements of mold (parting surface, ejectors, cooling lines, etc.) are checked for compatibility with RT mold properties (machinability, wear resistance, and surface evenness). Finally, the cost of RT mold is estimated using a semi-empirical model based on cost drivers and cost modifiers, and compared with that of a conventional mold. The methodology has been demonstrated with an experimental mold. It is useful not only for RT mold process selection, but also for identifying minor modifications to a mold design to improve its manufacturability and economy. 相似文献
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In this paper, the utilization of multi-sensors of different types, their characteristics, and their data-fusion in launch
vehicles to achieve the goal of injecting the satellite into a precise orbit is explained. Performance requirements of sensors
and their redundancy management in a typical launch vehicle are also included. The role of an integrated system level-test
bed for evaluating multi-sensors and mission performance in a typical launch vehicle mission is described. Some of the typical
simulation results to evaluate the effect of the sensors on the overall system are highlighted 相似文献
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The Tropospheric Emission Spectrometer (TES) is an imaging infrared Fourier-transform spectrometer scheduled to be launched into polar Sun-synchronous orbit aboard the Earth Observing System's Aura satellite in June 2003. The primary objective of the TES is to make global three-dimensional measurements of tropospheric ozone and of the physical-chemical factors that control its formation, destruction, and distribution. Such an ambitious goal requires a highly sophisticated cryogenic instrument operating over a wide frequency range, which, in turn, demands state-of-the-art infrared detector arrays. In addition, the measurements require an instrument that can operate in both nadir and limb-sounding modes with a precision pointing system. The way in which these mission objectives flow down to the specific science and measurement requirements and in turn are implemented in the flight hardware are described. A brief overview of the data analysis approach is provided. 相似文献
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PARASOL in-flight calibration and performance 总被引:2,自引:0,他引:2
Since 18 December 2004, the PARASOL satellite is a member of the so-called A-train atmospheric orbital observatory, flying together with Aqua, Aura, CALIPSO, CLOUDSAT, and OCO satellites. These satellites combine for the first time a full suite of instruments for observing aerosols and clouds, using passive radiometer complementarily with active lidar and radar sounders. The PARASOL payload is extensively derived from the instrument developed for the POLDER programs that performs measurements of bidirectionality and polarization for a very wide field-of-view and for a visible/near-infrared spectral range. An overview of the results obtained during the commissioning phase and the reevaluation after one year in orbit is presented. In-flight calibration methods are briefly described, and radiometric and geometric performances are both evaluated. All algorithms are based on a panel of methods using mainly natural targets previously developed for POLDER missions and adapted or redeveloped in the PARASOL context. Regarding performances, all mission requirements are met except for band 443 (not recommended for use). After one year in orbit, a perfect geometrical stability was found while a slight decrease of the radiometric sensitivity was observed and corrected through an innovative multitemporal algorithm based on observations of bright and scattered convective clouds. The scientific exploitation of PARASOL has now begun, particularly by coupling these specific observations with other A-train sensor measurements. 相似文献