CAJ | 학술논문

本文给出了全星历模型下适用于地月系统和日地系统的拟 Halo 轨道的设计方法。设计过程以限制三体模型下 Halo 轨道作为初值并以多点并行打靶法求解全星历模型下拟 Halo 轨道。采用多点并行打靶法中给出了一类新的可行约束条件，在数值仿真算例中，地月和日地系统 L2点附近4圈目标拟 Halo 轨道均在分钟量级时间内收敛，表明了算法的有效性。
본문급출료전성력모형하괄용우지월계통화일지계통적의 Halo 궤도적설계방법。설계과정이한제삼체모형하 Halo 궤도작위초치병이다점병행타파법구해전성력모형하의 Halo 궤도。채용다점병행타파법중급출료일류신적가행약속조건，재수치방진산례중，지월화일지계통 L2점부근4권목표의 Halo 궤도균재분종량급시간내수렴，표명료산법적유효성。
A method of designing the quasi Halo orbits in the full ephemeris model,which can be applied in both the earth-moon system and sun-earth system,is presented.In the design process,a Halo orbit designed in the restricted three-body model is taken as initial guess,and then a multiple shooting method is used to design in the full ephemeris model.A new feasible constraint condition is given.By numerical simulations,the quasi Halo orbits with four circles are both obtained about one minute for the earth-moon system and sun-earth system respectively, showing the effectiveness of the present algorithm.