摘要
Artemis任务建造与运行月球轨道门户空间站期间,将在近直线晕轨道(Near-Rectilinear Halo Orbit,NRHO)实施大量货运、载人飞行交会对接任务.针对NRHO调相轨道优化问题,基于圆型限制性三体问题模型,通过信赖域算法对转移时间进行遍历,采用非线性优化算法局部优化来修正位置误差,进而迭代求解非线性方程组降低速度增量,实现了低燃料消耗的NRHO调相优化;针对调相代价问题,对NRHO上不同转移时间和不同相位关系的调相进行了分析.结果表明,该算法计算效率较高,相比遗传算法减少了53.2%的计算时间;转移时间越长(转移轨道圈数越多),消耗的速度增量越小;目标航天器相位滞后时,选择绕NRHO外圈的调相方式更省燃料,反之,相位超前则选择绕内圈更省燃料;追踪航天器从近月点出发时燃料消耗更低.
During the construction and operation of the lunar gateway station under the U.S.Artemis program,numerous cargo and crew rendezvous and docking missions will be executed in the Near-Rectilinear Halo Orbit(NRHO).To address the phasing trajectory optimization problem in NRHO,a method based on the Circular Restricted Three-Body Problem(CRTBP)model is adopted.Initially,the transfer time is traversed using a trust-region algorithm.This step is critical to determining the transfer time that minimizes fuel consumption.Following the exploration of transfer times,a nonlinear optimization algorithm is applied to locally correct position errors along the trajectory.This local optimization finetunes the spacecraft’s path,ensuring precise alignment during the rendezvous.Finally,the nonlinear equations are solved iteratively to reduce the velocity increment required for the maneuver.This reduction in velocity increment is key to achieving low-fuel consumption during the NRHO phasing process.In addressing the phasing cost issue,this method is further utilized to analyze various scenarios on the NRHO,taking into account different transfer times and phase relationships.The analysis demonstrates that the algorithm boasts high computational efficiency,reducing computation time by 53.2%compared to a genetic algorithm.It is also observed that the longer the transfer time,indicating an increase in the number of transfer orbit revolutions,the smaller the velocity increment consumed during the maneuver becomes.Additionally,when the target spacecraft exhibits a phase lag,opting for a phasing maneuver along the outer loop of the NRHO results in fuel savings,whereas if the target spacecraft’s phase is ad-vanced,choosing the inner loop proves to be more fuel-efficient.Finally,the study notes that when the tracking spacecraft departs from the perilune,the consumed velocity increment is comparatively lower.This approach,therefore,provides an effective and efficient solution for optimizing NRHO phasing,en-suring reliable rendezvous operations with reduced fuel consumption and enhanced computational perfor-mance.
作者
李少峰
王有亮
于锡峥
李明涛
LI Shaofeng;WANG Youliang;YU Xizheng;LI Mingtao(National Space Science Center,Chinese Academy of Sciences,Beijing 100190;University of Chinese Academy of Sciences,Beijing 100049)
出处
《空间科学学报》
北大核心
2026年第1期175-188,共14页
Chinese Journal of Space Science
基金
中国科学院青年创新促进会项目资助(2022146)。
关键词
地月空间
圆型限制性三体问题
近直线晕轨道
调相轨道
信赖域算法
Cislunar space
Circular restricted three-body problem
Near-Rectilinear Halo Orbit
Phasing trajectory
Trust-region algorithm
