Atmospheric close approaches with the Earth considering drag and lift forces
| Autor: | Jhonathan Orlando Murcia Piñeros, Justyna Golebiewska, Vivian Martins Gomes, Antonio F. B. A. Prado |
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| Přispěvatelé: | Universidade Estadual Paulista (Unesp), Instituto Nacional de Pesquisas Espaciais-INPE, Adam Mickiewicz University |
| Jazyk: | angličtina |
| Rok vydání: | 2016 |
| Předmět: |
Orbital maneuvers
02 engineering and technology 01 natural sciences Swing-by Aero-gravity maneuver Astrodynamics 0203 mechanical engineering Gravitational field Planet 0103 physical sciences 010303 astronomy & astrophysics Physics 020301 aerospace & aeronautics Spacecraft business.industry Applied Mathematics Gravity drag Mechanics Close approach Orbital station-keeping Lift (force) Computational Mathematics Drag Physics::Space Physics Astrophysics::Earth and Planetary Astrophysics Orbital maneuver business |
| Zdroj: | Scopus Repositório Institucional da UNESP Universidade Estadual Paulista (UNESP) instacron:UNESP |
| Popis: | Made available in DSpace on 2018-12-11T17:29:46Z (GMT). No. of bitstreams: 0 Previous issue date: 2016-10-01 A maneuver called “Aero-Gravity Assisted” is known in the literature to increase the energy gains given by a close approach between a spacecraft and a planet using the atmosphere of the planet. In a sequence of studies related to this problem, the present paper studies close approaches between a spacecraft and the Earth, in situations where the passage is close enough to the surface of the Earth such that the spacecraft crosses its atmosphere. The dynamical model considers the atmosphere of the Earth, in terms of drag and lift, the gravitational fields of the Earth and the Sun, assumed to be points of mass, and the spacecraft. The Earth and the Sun are assumed to be in circular coplanar orbits around their common center of mass. The equations of motion are the ones given by the circular planar restricted three-body problem with the addition of the forces generated by the atmospheric drag and lift. The primary objective is to map the variations of energy of the orbits of the spacecraft due to this close approach. The results show how the atmosphere affects the trajectory of the spacecraft, generating situations where the variation of energy changes sign with respect to the gravity part of the maneuver or where they have a zero net result, based in the equilibrium between atmospheric and gravity forces. This result opens the possibility of changing only the eccentricity of the orbit, keeping fixed its semi-major axis. Grupo de Dinâmica Orbital e Planetologia Universidade Estadual Paulista-FEG/UNESP Instituto Nacional de Pesquisas Espaciais-INPE Faculty of Physics Astronomical Observatory Institute Adam Mickiewicz University Grupo de Dinâmica Orbital e Planetologia Universidade Estadual Paulista-FEG/UNESP |
| Databáze: | OpenAIRE |
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