Proximity Operations of Formation-Flying Spacecraft Using an Eccentricity/Inclination Vector Separation
Proximity Operations of Formation-Flying Spacecraft Using an Eccentricity/Inclination Vector Separation
复制标题
DOI：
10.2514/1.15114
复制
发表时间：
2006-05
影响因子：
2.6
通讯作者：
S. D’Amico;O. Montenbruck
中科院分区：
文献类型：
--
作者：
S. D’Amico;O. Montenbruck
利用分布式卫星系统实现合成孔径需要严格控制参与卫星的相对运动。本文研究了一种地层飞行概念，该概念能够实现孔径合成的苛刻基线，同时最大限度地减少与近距离操作相关的碰撞危险。讨论了相对运动线性化方程的优美表达式，并将其用于卫星编队设计。偏心/倾角矢量分离的概念，最初是为地球静止卫星开发的，在这里扩展到低地球轨道（LEO）编队。它提供了对相对运动的关键方面的直接洞察，对轨道控制目的和接近分析特别有用。给出了相关微分扰动对初始标称构型的影响，并设计了一种省油的轨道控制策略以保持目标分离。最后，将该方法应用于特定的低轨道编队（TanDEM-X/TerraSAR-X），仿真结果清楚地表明了编队飞行概念的简单性和有效性。
The implementation of synthetic apertures by means of a distributed satellite system requires tight control of the relative motion of the participating satellites. This paper investigates a formation-flying concept able to realize the demanding baselines for aperture synthesis, while minimizing the collision hazard associated with proximity operations. An elegant formulation of the linearized equations of relative motion is discussed and adopted for satellite formation design. The concept of eccentricity/inclination-vector separation, originally developed for geostationary satellites, is here extended to low-Earth-orbit (LEO) formations. It provides immediate insight into key aspects of the relative motion and is particularly useful for orbit control purposes and proximity analyses. The effects of the relevant differential perturbations acting on an initial nominal configuration are presented, and a fuel-efficient orbit control strategy is designed to maintain the target separation. Finally, the method is applied to a specific LEO formation (TanDEM-X/TerraSAR-X), and realistic simulations clearly show the simplicity and effectiveness of the formation-flying concept.