| Grant number: | 16/15675-1 |
| Support Opportunities: | Regular Research Grants |
| Start date: | December 01, 2016 |
| End date: | December 31, 2018 |
| Field of knowledge: | Engineering - Aerospace Engineering - Flight Dynamics |
| Principal Investigator: | Jorge Kennety Silva Formiga |
| Grantee: | Jorge Kennety Silva Formiga |
| Host Institution: | Instituto de Ciência e Tecnologia (ICT). Universidade Estadual Paulista (UNESP). Campus de São José dos Campos. São José dos Campos , SP, Brazil |
| Associated researchers: | Antônio Fernando Bertachini de Almeida Prado ; Denilson Paulo Souza dos Santos ; Rodolpho Vilhena de Moraes ; Vivian Martins Gomes |
Abstract
The goal this of project is to map the orbital characteristics of space debris to minimize the consequences and the damage caused to the environment, human life and space missions. There are several ways to explain the appearance of such debris, in particular through an explosion of one or more spacecraft and meteor fragments. Initially it will be performed a literature search related to the subject and the search of the number of satellites that are active and inactive. Then a mapping of the orbital behavior of a cloud of debris generated by one of the reasons cited above will be performed. It will be possible to know the orbital characteristics that existing and implemented and that will be used in analytical models. Disturbances due to radiation pressure, third body, Earth's mass distribution and close approach by a celestial body will be considered. In particular, the passage of a cloud near the Earth will be studied from the viewpoint of calculating the effects of the passage in the evolution of the shape and density of the cloud of fragments. In this situation, the system is assumed to be formed by the Sun, the Earth and a spacecraft which explodes and becomes a cloud of particles. Initially, the Sun-Earth system will be considered in circular and planar orbits, which will be extended later to other systems: Sun-Jupiter, Sun, Mars, etc. Thus, in these considerations, the equations of motion initially adopted will be validated for circular planar motion of restricted three-body problem. Then, the spacecraft maneuvers problem in order to avoid collisions with these clouds, to avoid the loss of mission and resulting in satellite re-entry in Earth with potential risks and environmental damage will be considered. (AU)
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