Abstract

Transfers in the central Newtonian field are considered under the assumption that low thrust that is constant in magnitude is zeroed when spacecraft with solar batteries enters the Earth’s shadow. Using the maximum principle, the two-point boundary-value problem is formed, in which, however, the conditions for optimal intersection of the shadow boundaries are not considered, which significantly complicates the problem. For this reason, the boundary-value problem is found to be “incomplete” and its solutions are not optimal. Nevertheless, for transfers to a geostationary orbit from highly elliptical orbits, it allows one to obtain “good” trajectories with working substance costs less than those on trajectories without zeroing the thrust, or slightly exceeding them. This is shown by the example of transfers from the initial orbit with an inclination of 13° and with a distance at the perigee of ≈15.6 Mm and at the apogee of ≈83.2 Mm.

中文翻译：

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在暗区关闭低推力的情况下将多轨道转移到对地静止轨道

摘要

当带有太阳能电池的航天器进入地球的阴影时，假设牛顿中部场的转移是在假定恒定大小的低推力为零的前提下进行的。使用最大原理，形成了两点边值问题，但是其中没有考虑阴影边界的最佳交点的条件，这使问题变得更加复杂。因此，发现边值问题是“不完整的”，其解决方案也不是最优的。然而，对于从高椭圆形轨道转移到对地静止轨道，它可以使“有效”轨道的工作物质成本低于在不使推力归零或略微超过它们的情况下的工作物质成本。≈ 15.6毫米，远地点≈ 83.2毫米。