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首页> 外文期刊>Celestial Mechanics and Dynamical Astronomy: An international journal of space dynamics >Modeling orbital relative motion to enable formationdesign from application requirements
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Modeling orbital relative motion to enable formationdesign from application requirements

机译：对轨道相对运动建模，以根据应用需求进行地层设计

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摘要

While trajectory design for single satellite Earth observation missions is usuallyperformed by means of analytical and relatively simple models of orbital dynamics includingthe main perturbations for the considered cases, most literature on formation flying dynamicsis devoted to control issues rather than mission design. This work aims at bridging the gapbetween mission requirements and relative dynamics in multi-platform missions by meansof an analytical model that describes relative motion for satellites moving on near circularlow Earth orbits. The development is based on the orbital parameters approach and both thecases of close and large formations are taken into account. Secular Earth oblateness effectsare included in the derivation. Modeling accuracy, when compared to a nonlinear model withtwo body and J_2forces, is shown to be of the order of 0.1% of relative coordinates for time-scales of hundreds of orbits. An example of formation design is briefly described shaping atwo-satellite formation on the basis of geometric requirements for synthetic aperture radarinterferometry.
机译：虽然通常通过分析和相对简单的轨道动力学模型来执行单个卫星地球观测任务的轨迹设计，包括所考虑情况的主要扰动，但大多数有关编队飞行动力学的文献都是致力于控制问题而不是任务设计。这项工作旨在通过一个分析模型来弥合多平台任务中的任务要求和相对动力学之间的差距，该模型描述在近圆形低地球轨道上移动的卫星的相对运动。该开发基于轨道参数方法，同时考虑了近地层和大地层的情况。世俗地球扁率效应包括在推导中。与具有两个物体和J_2力的非线性模型相比，建模精度在数百个轨道的时间尺度上显示为相对坐标的0.1％左右。根据合成孔径雷达干涉测量的几何要求，简要描述了一个编队设计示例，其形状为一个双卫星编队。

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