Abstract Artificial sun-synchronous orbits are suitable for remote sensing satellites and useful in giving accurate surface mapping. To design such orbits accurately with arbitrary orbital elements, three control strategies are provided with the consideration of main zonal harmonics up to J4 and solar radiation pressure (SRP). In this paper, the continuous variable low-thrust control is used as a way to achieve these artificial orbits and given by electric propulsions rather than chemical engines to enlarge lifespan of the spacecraft. The normal continuous low-thrust control is used to illustrate the control strategies. Furthermore, formulas for refinement of normal control thrusts are applied to overcome errors due to approximations. The results of the simulation show that the control strategies explained in this paper can realize sun-synchronous orbits with arbitrary orbital parameters without side effects and the effect of solar radiation pressure is very small relative to main zonal harmonics. A new technique is suggested, ASSOT-3, to minimize fuel consumption within one orbital period more than others. This technique is based on computing the root mean square of the rate of ascending node longitude instead of the average.

中文翻译：

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使用连续低推力控制策略设计具有主要区域谐波和太阳辐射压力的人工太阳同步轨道

摘要 人工太阳同步轨道适用于遥感卫星，有助于精确地表测绘。为了使用任意轨道元素准确设计此类轨道，提供了三种控制策略，并考虑了高达 J4 的主要纬向谐波和太阳辐射压力 (SRP)。在本文中，连续可变低推力控制被用作实现这些人造轨道的一种方式，并通过电力推进而不是化学发动机来延长航天器的寿命。使用正常的连续低推力控制来说明控制策略。此外，还应用了正常控制推力的细化公式来克服由于近似值引起的误差。仿真结果表明，本文阐述的控制策略可以实现任意轨道参数的太阳同步轨道，没有副作用，太阳辐射压力的影响相对于主要的纬向谐波非常小。建议采用新技术 ASSOT-3，以将一个轨道周期内的燃料消耗降至最低。该技术基于计算升交点经度率的均方根而不是平均值。