%0 Journal Article
%@nexthigherunit 8JMKD3MGPCW/3F2UALS
%@nexthigherunit 8JMKD3MGPCW/446AF4B
%@mirrorrepository urlib.net/www/2017/11.22.19.04.03
%3 ferreira_planar.pdf
%4 sid.inpe.br/mtc-m21c/2019/01.25.14.54
%8 Dec.
%9 journal article
%@issn 2238-3603
%A Ferreira, Alessandra F. S.,
%A Prado, Antonio Fernando Bertachini de Almeida,
%A Winter, Othon C.,
%@secondarytype PRE PI
%B Computational and Applied Mathematics
%D 2018
%K Powered Swing-By, Close approach, Impulsive maneuvers, Spacecraft trajectory, Energy decrease.
%N Suppl. 1
%P 202-219
%@secondarymark B2_MATEMÁTICA_/_PROBABILIDADE_E_ESTATÍSTICA B2_INTERDISCIPLINAR B3_CIÊNCIA_DA_COMPUTAÇÃO B4_ENGENHARIAS_IV
%T Planar powered Swing-By maneuvers to brake a spacecraft
%V 37
%X The Swing-By maneuver is a technique used in many space mission to modify the trajectory of a spacecraft. The most usual goal is to increase the energy of the spacecraft, but it is also possible to reduce this energy. An important application is to break a spacecraft coming to the Earth using a Swing-By with the moon, which is the example used in the present paper. Other possibilities also exist, such as reducing the velocity of a spacecraft going to the planets Mercury or Venus. The goal is to help a possible capture by the planet, or at least to provide a passage with smaller velocities to allow better observations during the passage. Therefore, the goal of the present paper is to study the energy loss that a spacecraft may have during a powered Swing-By maneuver, which is a maneuver that combines a close approach by a celestial body with the application of an impulsive maneuver. The behavior of the energy variation is analyzed as a function of the parameters related to the pure gravity maneuver: periapsis radius, angle of approach and approach velocity; and the parameters related to the impulsive maneuver: the location of application of the impulse and its direction and magnitude. The maneuver is performed in a system composed by two bodies, such as the Earth-moon system, around the secondary body, and the energy is measured with respect to the primary body of the system. This problem is solved by developing a mathematical algorithm that guides larger efforts in terms of computer simulations. The results show maps of conditions made from the numerical simulations for different points of application and direction of the impulse, where the maneuver is advantageous and how much more energy can be removed from the spacecraft.
%@area ETES
%@electronicmailaddress aleferrazsilva@hotmail.com
%@electronicmailaddress antonio.prado@inpe.br
%@electronicmailaddress ocwinter@gmail.com
%@documentstage not transferred
%@group CMC-ETES-SESPG-INPE-MCTIC-GOV-BR
%@group DIDMC-CGETE-INPE-MCTIC-GOV-BR
%@dissemination WEBSCI; PORTALCAPES; SCOPUS.
%@usergroup simone
%@resumeid
%@resumeid 8JMKD3MGP5W/3C9JGJA
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@affiliation Instituto Nacional de Pesquisas Espaciais (INPE)
%@affiliation Universidade Estadual Paulista (UNESP)
%@versiontype publisher
%@holdercode {isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S}
%@doi 10.1007/s40314-017-0483-4
%2 sid.inpe.br/mtc-m21c/2019/01.25.14.54.52