Optimized low-thrust mission to the Atira asteroids

Atira asteroids are recently-discovered celestial bodies characterised by orbits lying completely inside the heliocentric orbit of the Earth. The study of these objects is difficult due to the limitations of ground-based observations: objects can only be detected when the Sun is not in the field of view of the telescope. However, many asteroids are expected to exist in the inner region of the Solar System, many of which could pose a significant threat to our planet. In this paper, a small, low-cost, mission to visit the known Atira asteroids and to discover new Near Earth Asteroids (NEA) is proposed. The mission is realised using electric propulsion. The trajectory is optimised to maximise the number of visited asteroids of the Atira group using the minimum propellant consumption. During the tour of the Atira asteroids an opportunistic NEA discovery campaign is proposed to increase our knowledge of the asteroid population. The mission ends with a transfer to an orbit with perihelion equal to Venus’s orbit radius. This orbit represents a vantage point to monitor and detect asteroids in the inner part of the Solar System and provide early warning in the case of a potential impact.

[1]  Hyperbolic Injection Issues for MXER Tethers , 2003 .

[2]  J. S. Stuart,et al.  Observational constraints on the number, albedos, size, and impact hazards of the near-Earth asteroids , 2003 .

[3]  Massimiliano Vasile,et al.  Extended analytical formulas for the perturbed Keplerian motion under a constant control acceleration , 2015 .

[4]  Massimiliano Vasile,et al.  Direct transcription of low-thrust trajectories with finite trajectory elements , 2012 .

[5]  B. Gladman,et al.  The orbital distribution of Near-Earth Objects inside Earth's orbit , 2012 .

[6]  W. Burgett,et al.  Absolute magnitudes and slope parameters for 250,000 asteroids observed by Pan-STARRS PS1 – Preliminary results , 2015, 1506.00762.

[7]  Massimiliano Vasile,et al.  On the Preliminary Design of Multiple Gravity-Assist Trajectories , 2011, ArXiv.

[8]  B. Pavri,et al.  Dawn: An Ion-Propelled Journey to the Beginning of the Solar System , 2008, 2008 IEEE Aerospace Conference.

[9]  Massimiliano Vasile,et al.  Multi-population inflationary differential evolution algorithm with Adaptive Local Restart , 2015, 2015 IEEE Congress on Evolutionary Computation (CEC).

[10]  J. Doye,et al.  Global Optimization by Basin-Hopping and the Lowest Energy Structures of Lennard-Jones Clusters Containing up to 110 Atoms , 1997, cond-mat/9803344.

[11]  Brad Wallace,et al.  The Near Earth Object Surveillance Satellite: Mission status and CCD evolution after 18 months on-orbit , 2013 .

[12]  Paul Jaffe,et al.  Orbital mechanics , 2017, IEEE Spectrum.

[13]  Dario Izzo,et al.  An efficient pruning technique for the global optimisation of multiple gravity assist trajectories , 2005 .

[14]  John W. Fowler,et al.  The IRAS Minor Planet Survey , 1992 .

[15]  Marc D. Rayman,et al.  Design of the First Interplanetary Solar Electric Propulsion Mission , 2002 .

[16]  R. Storn,et al.  Differential Evolution: A Practical Approach to Global Optimization (Natural Computing Series) , 2005 .

[17]  Carl G. Sauer,et al.  Planetary Mission Capability of Small Low Power Solar Electric Propulsion Systems , 1995 .

[18]  Stephen Kemble.  Interplanetary Mission Analysis and Design , 2006 .

[19]  Jun'ichiro Kawaguchi.  The Hayabusa mission - Its seven years flight , 2011, 2011 Symposium on VLSI Circuits - Digest of Technical Papers.

[20]  Massimiliano Vasile,et al.  Incremental solution of LTMGA transfers transcribed with an advanced shaping approach , 2010 .

[21]  Bernard Bonnard,et al.  Mécanique céleste et contrôle des véhicules spatiaux , 2006 .

[22]  Massimiliano Vasile,et al.  Adaptive Inflationary Differential Evolution , 2014, 2014 IEEE Congress on Evolutionary Computation (CEC).

[23]  Victoria Coverstone-Carroll,et al.  Benefits of solar electric propulsion for the next generation of planetary exploration missions , 1997 .