Ideal satellite formation configuration with an elliptic reference orbit

被引：0

作者：

School of Aerospace, Tsinghua University, Beijing 100084, China ^{[1
]}

机构：

来源：

Qinghua Daxue Xuebao | 2006年 / 2卷 / 266-270期

关键词：

Design - Equations of motion - Feature extraction - Geometry - Orbits - Perturbation techniques - Remote sensing - Space flight;

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摘要：

To design the ideal satellite formation configurations with an elliptic reference orbit, the characteristics of the relative motion are summarized from the precise equations in terms of the reference orbital elements. Several ideal formation orbits were produced with specific geometric features. Three ideal configurations were developed for three-satellite formations which can be used for remote sensing missions. The reference orbital elements approach is convenient for designing ideal formation orbits and configurations and can select the satellite initial states according to the formation features. The ideal formation design can be used to determine the natural formation design, which is more complicated but more useful due to perturbation effects and the formation initialization.

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