TheMoon is the only celestial body that human beings have visited.The design of the Earth-Moon transfer orbits is a critical issue in lunar exploration missions.In the 21st century,new lunar missions including the con...TheMoon is the only celestial body that human beings have visited.The design of the Earth-Moon transfer orbits is a critical issue in lunar exploration missions.In the 21st century,new lunar missions including the construction of the lunar space station,the permanent lunar base,and the Earth-Moon transportation network have been proposed,requiring low-cost,expansive launch windows and a fixed arrival epoch for any launch date within the launch window.The low-energy and low-thrust transfers are promising strategies to satisfy the demands.This review provides a detailed landscape of Earth-Moon transfer trajectory design processes,from the traditional patched conic to the state-of-the-art low-energy and low-thrust methods.Essential mechanisms of the various utilized dynamic models and the characteristics of the different design methods are discussed in hopes of helping readers grasp thebasic overviewof the current Earth-Moon transfer orbitdesignmethods anda deep academic background is unnecessary for the context understanding.展开更多
The 2:1 resonant distant retrograde orbit(DRO),known for its long-term stability and global accessibility,holds strategic significance in current Earth-Moon space mission explorations.This paper conducts a comprehensi...The 2:1 resonant distant retrograde orbit(DRO),known for its long-term stability and global accessibility,holds strategic significance in current Earth-Moon space mission explorations.This paper conducts a comprehensive analysis of the problem of low-energy transferring into 2:1 DRO using the weak stability boundary(WSB)and lunar gravity assist(LGA)in the planar bi-circular restricted four-body problem(BCR4BP).The transfer process is categorized into three phases:the Earth-Moon transfer,Sun-Earth weak stability boundary transfer,and DRO low-energy capture.Addressing key questions,our study investigates:(1)Under what LGA conditions can the spacecraft reach the approximate area where the WSB region is situated?(2)How do trajectories,upon reaching the region where the WSB is located,return to the vicinity of 2:1 DRO,potentially facilitating low-energy DRO insertion?Our study involved a comprehensive analysis of the spacecraft’s changes in Earth-Moon mechanical energy and Jacobi energy during the entire transfer process.This analysis yielded the energy and geometric conditions necessary for potential low-energy DRO insertion,effectively filtering out numerous impractical candidate trajectories and enhancing computational effciency.In this paper,the geometric condition is referred to as the low-energy transfer gateway(LETG).Using the LEGT as the stitching interface,a significant number of feasible solutions were obtained effectively for bi-impulse DRO transfer trajectories through differential correction,some of which were previously undiscovered.展开更多
The Horyu-VI nano-satellite is an international lunar mission with the purpose of studying the lunar horizon glow(LHG)—a still unclear phenomenon caused by electrostatically charged lunar dust particles.This study an...The Horyu-VI nano-satellite is an international lunar mission with the purpose of studying the lunar horizon glow(LHG)—a still unclear phenomenon caused by electrostatically charged lunar dust particles.This study analyzes the mission trajectory with the hypothesis that it is launched as a secondary payload of the NASA ARTEMIS-II mission.In particular,the effect of the solar gravity gradient is studied;in fact,depending on the starting relative position of the Moon,the Earth,and the Sun,the solar gradient acts differently on the trajectory—changing it significantly.Therefore,the transfer and lunar capture problem is solved in several cases with the initial Sun–Earth–Moon angle as the key parameter.Furthermore,the inclination with respect to the Moon at capture is constrained to be equatorial.Finally,the problem of stabilization and circularization of the lunar orbit is addressed in a specific case,providing an estimate of the total propellant cost to reach the final orbit around the Moon.展开更多
基金supported by the National Key Research and Development Program of China(No.2021YFA0717100)the National Natural Science Foundation of China(Nos.12072270 and U2013206).
文摘TheMoon is the only celestial body that human beings have visited.The design of the Earth-Moon transfer orbits is a critical issue in lunar exploration missions.In the 21st century,new lunar missions including the construction of the lunar space station,the permanent lunar base,and the Earth-Moon transportation network have been proposed,requiring low-cost,expansive launch windows and a fixed arrival epoch for any launch date within the launch window.The low-energy and low-thrust transfers are promising strategies to satisfy the demands.This review provides a detailed landscape of Earth-Moon transfer trajectory design processes,from the traditional patched conic to the state-of-the-art low-energy and low-thrust methods.Essential mechanisms of the various utilized dynamic models and the characteristics of the different design methods are discussed in hopes of helping readers grasp thebasic overviewof the current Earth-Moon transfer orbitdesignmethods anda deep academic background is unnecessary for the context understanding.
基金supported by the Strategic Priority Program on Space Science of the Chinese Academy of Sciences(Grant No.XDA30010200).
文摘The 2:1 resonant distant retrograde orbit(DRO),known for its long-term stability and global accessibility,holds strategic significance in current Earth-Moon space mission explorations.This paper conducts a comprehensive analysis of the problem of low-energy transferring into 2:1 DRO using the weak stability boundary(WSB)and lunar gravity assist(LGA)in the planar bi-circular restricted four-body problem(BCR4BP).The transfer process is categorized into three phases:the Earth-Moon transfer,Sun-Earth weak stability boundary transfer,and DRO low-energy capture.Addressing key questions,our study investigates:(1)Under what LGA conditions can the spacecraft reach the approximate area where the WSB region is situated?(2)How do trajectories,upon reaching the region where the WSB is located,return to the vicinity of 2:1 DRO,potentially facilitating low-energy DRO insertion?Our study involved a comprehensive analysis of the spacecraft’s changes in Earth-Moon mechanical energy and Jacobi energy during the entire transfer process.This analysis yielded the energy and geometric conditions necessary for potential low-energy DRO insertion,effectively filtering out numerous impractical candidate trajectories and enhancing computational effciency.In this paper,the geometric condition is referred to as the low-energy transfer gateway(LETG).Using the LEGT as the stitching interface,a significant number of feasible solutions were obtained effectively for bi-impulse DRO transfer trajectories through differential correction,some of which were previously undiscovered.
文摘The Horyu-VI nano-satellite is an international lunar mission with the purpose of studying the lunar horizon glow(LHG)—a still unclear phenomenon caused by electrostatically charged lunar dust particles.This study analyzes the mission trajectory with the hypothesis that it is launched as a secondary payload of the NASA ARTEMIS-II mission.In particular,the effect of the solar gravity gradient is studied;in fact,depending on the starting relative position of the Moon,the Earth,and the Sun,the solar gradient acts differently on the trajectory—changing it significantly.Therefore,the transfer and lunar capture problem is solved in several cases with the initial Sun–Earth–Moon angle as the key parameter.Furthermore,the inclination with respect to the Moon at capture is constrained to be equatorial.Finally,the problem of stabilization and circularization of the lunar orbit is addressed in a specific case,providing an estimate of the total propellant cost to reach the final orbit around the Moon.
