Отрывок: Afterhavingthemotionequations [3] withtheboundaryconditions (table 1) integratedwe get the state vector components relevant to the final transfer segment determined. Let us derive the Hamiltonian for the costate vector mvrvr ,,,, ψψψψψ ϕϕ : mvrv r r dt dm dt dv dt dv dt d dr drH ψψψψϕψ ϕ ϕ ϕ ++++= . (6) Then we plug the right parts of the motion equations into (6): mv r rvrr Sin m a r vv Cos m a rr v r v vH βψψλδψλδψψ ϕ ϕϕ ϕ ϕ + − +−+...
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Поле DC | Значение | Язык |
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dc.contributor.author | Fain, M.K. | - |
dc.contributor.author | Starinova, O.L. | - |
dc.date.accessioned | 2018-05-18 11:02:00 | - |
dc.date.available | 2018-05-18 11:02:00 | - |
dc.date.issued | 2018 | - |
dc.identifier | Dspace\SGAU\20180517\69428 | ru |
dc.identifier.citation | Fain M.K. Mathematical modeling of the space tug transfers between the Lagrange points of the Earth-Moon system/M.K. Fain , O.L. Starinova// Сборник трудов IV международной конференции и молодежной школы «Информационные технологии и нанотехнологии» (ИТНТ-2018) - Самара: Новая техника, 2018. - С.1711-1715 | ru |
dc.identifier.uri | http://repo.ssau.ru/handle/Informacionnye-tehnologii-i-nanotehnologii/Mathematical-modeling-of-the-space-tug-transfers-between-the-Lagrange-points-of-the-EarthMoon-system-69428 | - |
dc.description.abstract | The paper outlines the mathematical modeling of the L1-L2 and L2-L1 missions using electric propulsion. The variation problem of the low thrust spacecraft transfer optimization, with total flight time as the optimization criterion is considered. The locally optimal control programs were obtained by using the Fedorenko method to estimate the derivatives, the gradient method to optimize the control laws and the Runge-Kutta method for the numerical integration of the differential equation system. As the result of optimization, optimal control programs and corresponding trajectories were determined for certain values of acceleration and jet stream velocity of the propulsion system. | ru |
dc.language.iso | en_US | ru |
dc.publisher | Новая техника | ru |
dc.relation.ispartofseries | 3;229 | - |
dc.subject | mathematical modeling | ru |
dc.subject | motion simulation | ru |
dc.subject | spacecraft | ru |
dc.subject | low thrust engine | ru |
dc.subject | ballistic optimization | ru |
dc.subject | Lagrange point | ru |
dc.subject | Earth-Moon system | ru |
dc.title | Mathematical modeling of the space tug transfers between the Lagrange points of the Earth-Moon system | ru |
dc.type | Article | ru |
dc.textpart | Afterhavingthemotionequations [3] withtheboundaryconditions (table 1) integratedwe get the state vector components relevant to the final transfer segment determined. Let us derive the Hamiltonian for the costate vector mvrvr ,,,, ψψψψψ ϕϕ : mvrv r r dt dm dt dv dt dv dt d dr drH ψψψψϕψ ϕ ϕ ϕ ++++= . (6) Then we plug the right parts of the motion equations into (6): mv r rvrr Sin m a r vv Cos m a rr v r v vH βψψλδψλδψψ ϕ ϕϕ ϕ ϕ + − +−+... | - |
Располагается в коллекциях: | Информационные технологии и нанотехнологии |
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paper_229.pdf | Основная статья. | 129.84 kB | Adobe PDF | Просмотреть/Открыть |
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