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Dynamics around small irregularly shaped objects modeled as a mass dipole.

Ahmed A Abozaid1, M Radwan2, A H Ibrahim3

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This study analyzes spacecraft dynamics near a spherical body and an elongated dipole. Stable collinear equilibrium points exist for negative oblateness, crucial for understanding orbital mechanics and asteroid systems.

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Area of Science:

  • Celestial Mechanics
  • Astrodynamics
  • Gravitational Dynamics

Background:

  • Investigates spacecraft motion in a complex gravitational field.
  • Considers a system with a spherical primary and an elongated dipole secondary body.

Purpose of the Study:

  • To analyze the dynamics of a spacecraft near two primary bodies with distinct gravitational models.
  • To determine the existence, location, and stability of equilibrium points under varying system parameters.
  • To explore the implications for real-world systems like the 2001 SN263 asteroid.

Main Methods:

  • Formulation of the equations of motion for a negligible mass spacecraft.
  • Analysis of equilibrium points and their dependence on system parameters.
  • Linear stability analysis of equilibrium points and use of zero-velocity curves.

Main Results:

  • Spacecraft dynamics and equilibrium point locations are significantly influenced by system parameters.
  • Stable collinear equilibrium points are identified for negative oblateness parameters.
  • Triangular equilibrium points exhibit linear stability.

Conclusions:

  • The study provides insights into the complex dynamics of spacecraft in multi-body systems with non-spherical potentials.
  • Findings are relevant for mission design and understanding the orbital behavior of celestial bodies like asteroids.
  • The oblateness parameter critically affects the stability of collinear equilibrium points.