{"title":"基于低推力优化和反馈控制的低能地月任务分析","authors":"A. Almonte","doi":"10.21741/9781644902813-130","DOIUrl":null,"url":null,"abstract":"Abstract. This work is focused on designing a low-energy orbit transfer in the Earth-Moon system, aimed at reaching stable capture in a highly elliptical lunar orbit, with the use of low-thrust propulsion. The mission at hand includes three different phases: low-energy ballistic transfer starting from Earth, low-thrust minimum-fuel arc, and low-thrust lunar orbit insertion using variable-thrust nonlinear orbit control. First, a reference trajectory is generated in the framework of the Patched Planar Circular Restricted Three-Body Problem (PPCR3BP), leveraging invariant manifold dynamics. Trajectory propagation is performed using the Bicircular Restricted Four-Body Problem (BR4BP) model. Particle swarm optimization is applied for trajectory refinement and to detect the subsequent minimum-fuel low-thrust arc. Finally, the lunar orbit is entered thanks to the use of variable-thrust nonlinear orbit control.","PeriodicalId":87445,"journal":{"name":"Materials Research Society symposia proceedings. Materials Research Society","volume":null,"pages":null},"PeriodicalIF":0.0000,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":"{\"title\":\"Low-energy earth-moon mission analysis using low-thrust optimal and feedback control\",\"authors\":\"A. Almonte\",\"doi\":\"10.21741/9781644902813-130\",\"DOIUrl\":null,\"url\":null,\"abstract\":\"Abstract. This work is focused on designing a low-energy orbit transfer in the Earth-Moon system, aimed at reaching stable capture in a highly elliptical lunar orbit, with the use of low-thrust propulsion. The mission at hand includes three different phases: low-energy ballistic transfer starting from Earth, low-thrust minimum-fuel arc, and low-thrust lunar orbit insertion using variable-thrust nonlinear orbit control. First, a reference trajectory is generated in the framework of the Patched Planar Circular Restricted Three-Body Problem (PPCR3BP), leveraging invariant manifold dynamics. Trajectory propagation is performed using the Bicircular Restricted Four-Body Problem (BR4BP) model. Particle swarm optimization is applied for trajectory refinement and to detect the subsequent minimum-fuel low-thrust arc. Finally, the lunar orbit is entered thanks to the use of variable-thrust nonlinear orbit control.\",\"PeriodicalId\":87445,\"journal\":{\"name\":\"Materials Research Society symposia proceedings. Materials Research Society\",\"volume\":null,\"pages\":null},\"PeriodicalIF\":0.0000,\"publicationDate\":\"2023-11-01\",\"publicationTypes\":\"Journal Article\",\"fieldsOfStudy\":null,\"isOpenAccess\":false,\"openAccessPdf\":\"\",\"citationCount\":\"0\",\"resultStr\":null,\"platform\":\"Semanticscholar\",\"paperid\":null,\"PeriodicalName\":\"Materials Research Society symposia proceedings. Materials Research Society\",\"FirstCategoryId\":\"1085\",\"ListUrlMain\":\"https://doi.org/10.21741/9781644902813-130\",\"RegionNum\":0,\"RegionCategory\":null,\"ArticlePicture\":[],\"TitleCN\":null,\"AbstractTextCN\":null,\"PMCID\":null,\"EPubDate\":\"\",\"PubModel\":\"\",\"JCR\":\"\",\"JCRName\":\"\",\"Score\":null,\"Total\":0}","platform":"Semanticscholar","paperid":null,"PeriodicalName":"Materials Research Society symposia proceedings. Materials Research Society","FirstCategoryId":"1085","ListUrlMain":"https://doi.org/10.21741/9781644902813-130","RegionNum":0,"RegionCategory":null,"ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"","JCRName":"","Score":null,"Total":0}
Low-energy earth-moon mission analysis using low-thrust optimal and feedback control
Abstract. This work is focused on designing a low-energy orbit transfer in the Earth-Moon system, aimed at reaching stable capture in a highly elliptical lunar orbit, with the use of low-thrust propulsion. The mission at hand includes three different phases: low-energy ballistic transfer starting from Earth, low-thrust minimum-fuel arc, and low-thrust lunar orbit insertion using variable-thrust nonlinear orbit control. First, a reference trajectory is generated in the framework of the Patched Planar Circular Restricted Three-Body Problem (PPCR3BP), leveraging invariant manifold dynamics. Trajectory propagation is performed using the Bicircular Restricted Four-Body Problem (BR4BP) model. Particle swarm optimization is applied for trajectory refinement and to detect the subsequent minimum-fuel low-thrust arc. Finally, the lunar orbit is entered thanks to the use of variable-thrust nonlinear orbit control.