太阳帆作为一种利用太阳辐射压力产生持续小推力的航天推进系统，因其无需消耗推进剂的特点，在深空探测等长期航天任务中展现出独特优势。基于太阳-水星椭圆限制性三体问题这一动力学模型，提出三种递进式的太阳帆指向律，使太阳帆平面由最初正对太阳，过渡到在引力平面内偏离太阳方向，再到最终偏离引力平面。利用多段打靶法进行轨道延拓计算，获得了具有不同共振比的太阳帆共振晕轨道。在三种指向策略下，分别对太阳帆的面质比、锥角与方位角进行参数延拓。结果表明，前两种策略下得到的共振晕轨道在旋转坐标系中关于XZ平面呈对称结构，而第三种策略下获得的轨道则不关于任意平面或直线对称，表现出复杂的空间三维结构，同时保持良好的周期性。最后在高精度星历模型下对轨道稳定性进行分析，结果显示所构建的太阳帆共振晕轨道在无需轨道保持的情况下，可在约4–6个水星轨道周期内（约352–528天）维持轨道形状且不发散，具备一定的自然稳定性。
The solar sail is a type of continuous low-thrust spacecraft that generates propulsion through solar radiation pres-sure. Due to its fuel-free operation, it is particularly suitable for long-duration deep space exploration missions. Based on the dynamical models of the Sun-Mercury elliptic restricted three-body problem, this study proposes three progressive solar sail steering laws. These steering strategies enable the normal vector of the solar sail plane to transition from pointing directly toward the Sun, to deviating within the gravitational plane, and finally to deviating out of the gravitational plane. By employing a multiple-shooting method combined with continuation techniques, families of resonant halo orbits with different resonance ratios are obtained for solar sail spacecraft. Under the three proposed steering laws, parameter continuation is performed with respect to the sail’s area-to-mass ratio, cone angle, and pitch angle, respectively. The first two steering laws yield resonant halo orbits that are symmetric about the XZ-plane of the rotating coordinate system. In contrast, the third steering law produces periodic orbits that are asymmetric with respect to any plane or line, exhibiting complex three-dimension structures with periodicity remained. Finally, the stability of the solar sail resonant halo orbits under different steering laws is analyzed within a high-precision ephemeris model. The results indicate that these orbits can maintain their overall shape without sig-nificant divergence for approximately 4 to 6 Mercury orbital periods (about 352 to 528 days) without station-keeping maneuvering.
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