Artificial halo orbits for low-thrust propulsion spacecraft

Details Artificial halo orbits for low-thrust propulsion spacecraft Artificial halo orbits for low-thrust propulsion spacecraft

Aug 2009

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2009cemda.104..321b&link_type=abstract

Celestial Mechanics and Dynamical Astronomy, Volume 104, Issue 4, pp.321-335

Astronomy and Astrophysics

Astronomy

4

Restricted Three Body Problem, Halo Orbits, Low-Thrust Propulsion, Continuation Method, Artificial Equilibrium Points

Scientific paper

We consider periodic halo orbits about artificial equilibrium points (AEP) near to the Lagrange points L 1 and L 2 in the circular restricted three body problem, where the third body is a low-thrust propulsion spacecraft in the Sun-Earth system. Although such halo orbits about artificial equilibrium points can be generated using a solar sail, there are points inside L 1 and beyond L 2 where a solar sail cannot be placed, so low-thrust, such as solar electric propulsion, is the only option to generate artificial halo orbits around points inaccessible to a solar sail. Analytical and numerical halo orbits for such low-thrust propulsion systems are obtained by using the Lindstedt Poincaré and differential corrector method respectively. Both the period and minimum amplitude of halo orbits about artificial equilibrium points inside L 1 decreases with an increase in low-thrust acceleration. The halo orbits about artificial equilibrium points beyond L 2 in contrast show an increase in period with an increase in low-thrust acceleration. However, the minimum amplitude first increases and then decreases after the thrust acceleration exceeds 0.415 mm/s2. Using a continuation method, we also find stable artificial halo orbits which can be sustained for long integration times and require a reasonably small low-thrust acceleration 0.0593 mm/s2.

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