Comparison of Single and Multi-Spacecraft Configurations for NEA Deflection by Solar Sublimation

Statistics – Applications

Scientific paper

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Asteroids, Meteoroids, Solar Irradiance, Spaceborne And Space Research Instruments, Apparatus, And Components

Scientific paper

With the increased interest and attention to Near Earth Objects, there have been many proposals of possible methods of deviating of those objects potentially posing a threat to Earth. One such conceptual method envisioned sublimating the surface material of an asteroid using solar energy directed by mirrors onboard an orbiting or hovering spacecraft. In this paper, this method is examined in more detail, with an emphasis on feasibility. A comparison is made between the complexities of deploying and operating a single large rigid structure around asteroids, with that of a formation of smaller spacecraft. Configurations are presented for different Near Earth Asteroids (NEA), duration of thrust, and achieved deflections. Both simplistic single flat mirror and more complex parabolic reflector-lens assemblies are examined, comparing the initial spacecraft mass and payload sizing for various formation sizes. Relative periodic formation orbits are found accounting for perturbations due to the Sun and NEA, and for the solar pressure on the mirror payload on the spacecraft.

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