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首页> 外文期刊>Acta astronautica >Formation flying and mission design for Proba-3
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Formation flying and mission design for Proba-3

机译：Proba-3的编队飞行和任务设计

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The Proba-3 mission is an ambitious European mission to test the design, implementation and operation of a two-spacecraft formation flying system with a high degree of autonomy with a launch foreseen in the 2015/2016 time-frame. It comprises two spacecraft, the coronagraph and the occulter, which are to be inserted into a highly elliptical orbit. It is intended to perform the formation flying demonstration around the apogee and use the perigee pass for telemetry, orbit determination, orbit correction, and formation configuration manoeuvres. The design of the target orbit is driven by the minimisation of disturbances to the spacecraft formation, and is constrained by the rather low Av capability of the spacecraft of less than 100 ms~(-1) as well as the characteristics of the selected launch vehicle. The secondary mission objective of Proba-3 is to operate the formation as a coronagraph with one spacecraft being the occulter and the other carrying the optics and detectors. The alignment of the formation with the Sun-direction has as a consequence that the geometry of the formation relative to the orbit is prescribed for the perigee pass. This geometry also determines the relative dynamics of the formation. The relationship between formation configuration and orbital parameters is typical for formation flying missions on elliptical orbits and requires a careful choice of the launch time such that the constraints on the angle between the Sun-direction and the orbital plane are fulfilled. Here we present the design of the operational orbit and transfer phase of Proba-3 together with an analysis of the separation, formation acquisition, and target formation maintenance. Also the benefit of available tracking data for contingency situations in the Proba-3 missions is discussed.
机译：Proba-3任务是一项雄心勃勃的欧洲任务，旨在测试高度自主的两机编队飞行系统的设计，实施和运行，并预计在2015/2016年的时间范围内发射。它包括两个航天器，即日冕仪和掩星仪，它们将被插入高度椭圆形的轨道中。它旨在在远地点周围进行编队飞行演示，并使用近地点通行证进行遥测，确定轨道，校正轨道和编队构型。目标轨道的设计受到对航天器编队的干扰最小化的驱动，并且受航天器的低于100 ms〜（-1）的相当低的Av能力以及所选运载火箭的特性的约束。 Proba-3的次要任务目标是用电晕仪操作地层，其中一艘太空船是隐匿者，另一艘则携带光学器件和探测器。结果，地层与太阳方向的对准具有针对近距离通过规定地层相对于轨道的几何形状的结果。这种几何形状还决定了地层的相对动力学。编队构型与轨道参数之间的关系对于椭圆轨道上的编队飞行任务而言是典型的，并且需要仔细选择发射时间，以便满足对太阳方向与轨道平面之间的角度的约束。在这里，我们介绍Proba-3的运行轨道和转移阶段的设计，以及对分离，编队获取和目标编队维护的分析。还讨论了Proba-3任务中针对应急情况的可用跟踪数据的好处。

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