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Injection of a microsatellite in circular orbits using a three-stage launch vehicle

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Autor(es):
Marchi, L. O. ; Murcia, J. O. ; Prado, A. F. B. A. ; Solorzano, C. R. H. ; IOP
Número total de Autores: 5
Tipo de documento: Artigo Científico
Fonte: WAKE CONFERENCE 2021; v. 911, p. 6-pg., 2017-01-01.
Resumo

The injection of a satellite into orbit is usually done by a multi-stage launch vehicle. Nowadays, the space market demonstrates a strong tendency towards the use of smaller satellites, because the miniaturization of the systems improve the cost/benefit of a mission. A study to evaluate the capacity of the Brazilian Microsatellite Launch Vehicle (VLM) to inject payloads into Low Earth Orbits is presented in this paper. All launches are selected to be made to the east side of the Alcantara Launch Center (CLA). The dynamical model to calculate the trajectory consists of the three degrees of freedom (3DOF) associated with the translational movement of the rocket. Several simulations are performed according to a set of restrictions imposed to the flight. The altitude reached in the separation of the second stage, the altitude and velocity of injection, the flight path angle at the moment of the activation of the third stage and the duration of the ballistic flight are presented as a function of the payload carried. (AU)

Processo FAPESP: 11/08171-3 - Dinâmica orbital de pequenos corpos
Beneficiário:Othon Cabo Winter
Modalidade de apoio: Auxílio à Pesquisa - Temático
Processo FAPESP: 16/14665-2 - Astrodinâmica Aplicada a Veículos Espaciais
Beneficiário:Antônio Fernando Bertachini de Almeida Prado
Modalidade de apoio: Auxílio à Pesquisa - Regular