Результаты исследований: Публикации в книгах, отчётах, сборниках, трудах конференций › статья в сборнике материалов конференции › научная › Рецензирование
Maneuvering in Near-Earth Space with the Use of the Collinear Libration Points. / Shmyrov, Alexander; Shymanchuk, Dzmitry.
2015 INTERNATIONAL CONFERENCE ON MECHANICS SEVENTH POLYAKHOVS READING. ред. / AA Tikhonov. Institute of Electrical and Electronics Engineers Inc., 2015.Результаты исследований: Публикации в книгах, отчётах, сборниках, трудах конференций › статья в сборнике материалов конференции › научная › Рецензирование
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TY - GEN
T1 - Maneuvering in Near-Earth Space with the Use of the Collinear Libration Points
AU - Shmyrov, Alexander
AU - Shymanchuk, Dzmitry
N1 - Conference code: 7
PY - 2015
Y1 - 2015
N2 - The use of the neighborhood of collinear libration point (L-1 or L-2()) of the Sun-Earth system has long been of practical importance in connection with projects implemented by NASA and ESA. A celestial body motion is considered in a rotating frame within the Hill's problem of the circular restricted three-body problem. It is known that collinear libration points are unstable but its instability can be used as a positive factor for maneuvering a celestial body in the near-Earth space. For example, it may be used to solve the problem of comet and asteroid hazard to monitor space objects posing threat to the Earth. We offer a methodology for constructing control algorithms for the orbital motion of a celestial body. This methodology is based on the properties of a specially introduced phase variables function called "hazard function". Numerical simulation results are given.
AB - The use of the neighborhood of collinear libration point (L-1 or L-2()) of the Sun-Earth system has long been of practical importance in connection with projects implemented by NASA and ESA. A celestial body motion is considered in a rotating frame within the Hill's problem of the circular restricted three-body problem. It is known that collinear libration points are unstable but its instability can be used as a positive factor for maneuvering a celestial body in the near-Earth space. For example, it may be used to solve the problem of comet and asteroid hazard to monitor space objects posing threat to the Earth. We offer a methodology for constructing control algorithms for the orbital motion of a celestial body. This methodology is based on the properties of a specially introduced phase variables function called "hazard function". Numerical simulation results are given.
M3 - статья в сборнике материалов конференции
BT - 2015 INTERNATIONAL CONFERENCE ON MECHANICS SEVENTH POLYAKHOVS READING
A2 - Tikhonov, AA
PB - Institute of Electrical and Electronics Engineers Inc.
Y2 - 2 February 2015 through 6 February 2015
ER -
ID: 9426736