{"title":"Control of the Process of Rapprochement of a Tether System with a Passive Space Object in a Near-Circular Orbit","authors":"Yu. M. Zabolotnov, Changqing Wang, Zheng Min","doi":"10.1134/s0010952524600239","DOIUrl":null,"url":null,"abstract":"<h3 data-test=\"abstract-sub-heading\">Abstract</h3><p>The article deals with the control of the process of rapprochement of a tether system with a passive space object (cargo, space debris, etc.) in an almost circular near-Earth orbit. It is assumed that the active spacecraft, which includes a tether system with a capture device (not deployed), is located in a close (relative to the orbit of the cargo) orbit, which was formed using some known long-range guidance algorithm. It is assumed that the active spacecraft, which includes a tether system with a capture device (not deployed), is located in a close (relative to the orbit of the cargo) orbit, which was formed using some known long-range guidance algorithm. The position of the dummy point is chosen based on the fact that, after the deployment of the tether system, the capture device appears in the vicinity of the cargo immediately or after some small portion of passive movement in orbit. The control of the process of approaching the spacecraft with a fictitious point in the spatial case is constructed using the Bellman dynamic programming principle using a linearized system. Continuous control is used with the help of jet engines with finite thrust. The components of the reactive forces for which the control is being constructed are directed along the transversal and binormal in the orbital coordinate system. It is assumed that the unavoidable guidance errors can be corrected by changing the length of the tether or in some other way. A numerical example of modeling the processes under consideration using nonlinear equations of motion is given illustrating the proposed control scheme.</p>","PeriodicalId":56319,"journal":{"name":"Cosmic Research","volume":null,"pages":null},"PeriodicalIF":0.6000,"publicationDate":"2024-06-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":"0","resultStr":null,"platform":"Semanticscholar","paperid":null,"PeriodicalName":"Cosmic Research","FirstCategoryId":"101","ListUrlMain":"https://doi.org/10.1134/s0010952524600239","RegionNum":4,"RegionCategory":"物理与天体物理","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":null,"EPubDate":"","PubModel":"","JCR":"Q4","JCRName":"ASTRONOMY & ASTROPHYSICS","Score":null,"Total":0}
引用次数: 0
Abstract
The article deals with the control of the process of rapprochement of a tether system with a passive space object (cargo, space debris, etc.) in an almost circular near-Earth orbit. It is assumed that the active spacecraft, which includes a tether system with a capture device (not deployed), is located in a close (relative to the orbit of the cargo) orbit, which was formed using some known long-range guidance algorithm. It is assumed that the active spacecraft, which includes a tether system with a capture device (not deployed), is located in a close (relative to the orbit of the cargo) orbit, which was formed using some known long-range guidance algorithm. The position of the dummy point is chosen based on the fact that, after the deployment of the tether system, the capture device appears in the vicinity of the cargo immediately or after some small portion of passive movement in orbit. The control of the process of approaching the spacecraft with a fictitious point in the spatial case is constructed using the Bellman dynamic programming principle using a linearized system. Continuous control is used with the help of jet engines with finite thrust. The components of the reactive forces for which the control is being constructed are directed along the transversal and binormal in the orbital coordinate system. It is assumed that the unavoidable guidance errors can be corrected by changing the length of the tether or in some other way. A numerical example of modeling the processes under consideration using nonlinear equations of motion is given illustrating the proposed control scheme.
期刊介绍：
Cosmic Research publishes scientific papers covering all subjects of space science and technology, including the following: ballistics, flight dynamics of the Earth’s artificial satellites and automatic interplanetary stations; problems of transatmospheric descent; design and structure of spacecraft and scientific research instrumentation; life support systems and radiation safety of manned spacecrafts; exploration of the Earth from Space; exploration of near space; exploration of the Sun, planets, secondary planets, and interplanetary medium; exploration of stars, nebulae, interstellar medium, galaxies, and quasars from spacecraft; and various astrophysical problems related to space exploration. A chronicle of scientific events and other notices concerning the main topics of the journal are also presented.
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