Long-Term Evolution of Highly-Elliptical Orbits: Luni-Solar Perturbation Effects for Stability and Re-entry

Camilla Colombo

doi:10.3389/fspas.2019.00034

Abstract

This paper investigates the long-term evolution of spacecraft in Highly Elliptical Orbits (HEOs). The single averaged disturbing potential due to luni-solar perturbations, zonal harmonics of the Earth gravity field is written in mean Keplerian elements. The double averaged potential is also derived in the Earth-centered equatorial system. Maps of long-term orbit evolution are constructed by measuring the maximum variation of the orbit eccentricity to identify conditions for quasi-frozen, long-lived libration orbits or initial orbit conditions that naturally evolve toward re-entry in the Earth’s atmosphere. The behavior of these long-term orbit maps is studied for increasing values of the initial orbit inclination and anomaly of the perigee with respect to the Moon’s orbital plane. In addition, to allow meeting specific mission constraints, quasi-frozen orbits can be selected as graveyard orbits for the end-of-life of HEO missions. On the opposite side, unstable conditions can be exploited to target Earth re-entry at the end-of-mission.

Highlights

Elliptical Orbits (HEOs) about the Earth are often selected for astrophysics and astronomy missions, as well as for Earth missions, such as Molniya or Tundra orbits, as they offer vantage point for the observation of the Earth and the Universe (Draim et al, 2002)
The dynamics of Highly Elliptical Orbits (HEOs) with high apogee altitude is mainly influenced by the effect of third body perturbations due to the Moon and the Sun, which induces long-term variations in the eccentricity and the inclination, corresponding to large fluctuations of the orbit perigee and the effect of the Earth’s oblateness
The finite variation in orbital elements α achieved by an impulsive maneuver, is computed through Gauss’ planetary equations written in finite-difference form and the new set of orbital elements after the maneuver is propagated with PlanODyn (Colombo, 2016) in single-averaged orbital elements considering luni-solar perturbation and the zonal terms of the Earth gravity potential for the maxim disposal time tdisposal = 30 years

Summary

Introduction

Elliptical Orbits (HEOs) about the Earth are often selected for astrophysics and astronomy missions, as well as for Earth missions, such as Molniya or Tundra orbits, as they offer vantage point for the observation of the Earth and the Universe (Draim et al, 2002).

Results

Conclusion