Halo orbit

Halo orbit

A halo orbit is a periodic, three-dimensional orbit near the L1 L2 or L3 Lagrange points in the three-body problem of orbital mechanics. Although a spacecraft in a halo orbit moves in a circular path around the Lagrange point, it does not technically orbit the actual Lagrange point, because the Lagrange point is just an equilibrium point with no gravitational pull, but travels in a closed, repeating path near the Lagrange point. Halo orbits are the result of a complicated interaction between the gravitational pull of the two planetary bodies and the coriolis and centrifugal accelerations on a spacecraft. Halo orbits exist in many three-body systems, such as the SunEarth system and the Earth–Moon system. Continuous "families" of both Northern and Southern halo orbits exist at each Lagrange point. Because halo orbits tend to be unstable, stationkeeping is required to keep a satellite on the orbit.


  • Definition and history 1
  • See also 2
  • References 3
  • External links 4

Definition and history

Robert W. Farquhar first used the name "halo" for these orbits in his 1968 Ph.D. thesis.[1] Farquhar advocated using spacecraft in a halo orbit on the far side of the Moon (Earth–Moon L2) as a communications relay station for an Apollo mission to the far side of the Moon. A spacecraft in such a halo orbit would be in continuous view of both the Earth and the far side of the Moon. In the end, neither a communication link satellite nor an Apollo co-mission positioned at L2 for a far side Apollo lunar landing ever took flight.[2]

The first mission to use a halo orbit was ISEE-3, launched in 1978. It traveled to the Sun–Earth L1 point and remained there for several years. The next mission to use a halo orbit was Solar and Heliospheric Observatory (SOHO), a joint ESA and NASA mission to study the Sun, which arrived at Sun–Earth L1 in 1996. It used an orbit similar to ISEE-3.[3] Although several other missions since then have traveled to Lagrange points, they typically have used non-periodic orbits (also called Lissajous orbits) that are slightly different from halo orbits.

Farquhar used analytical expressions to represent halo orbits, but Kathleen Howell showed that more precise trajectories could be computed numerically.[4] The most recent mission to use a halo orbit was Genesis, launched in 2001, which also pioneered the use of dynamical systems theory to find low-energy trajectories to and from the halo orbit.

See also


  1. ^ Farquhar, R. W.: "The Control and Use of Libration-Point Satellites", Ph.D. Dissertation, Dept. of Aeronautics and Astronautics, Stanford University, Stanford, California, 1968
  2. ^ Schmid, P. E. (June 1968). "Lunar Far-Side Communication Satellites" (PDF). NASA. Retrieved 2008-07-16. 
  3. ^ Dunham, D.W. and Farquhar, R. W.: "Libration-Point Missions 1978-2000," Libration Point Orbits and Applications, Parador d'Aiguablava, Girona, Spain, June 2002
  4. ^ Howell, K. C.: "Three-Dimensional, Periodic, 'Halo' Orbits", Celestial Mechanics, Volume 32, Number 53, 1984

External links

  • CDS140B: Computation of Halo Orbit Archived September 16, 2006 at the Wayback Machine
  • SOHO - The Trip to the L1 Halo Orbit
  • Low Energy Interplanetary Transfers Using Halo Orbit Hopping Method with STK/Astrogator
  • Gaia's Lissajous Type Orbit — a Lissajous-type orbit, i.e., a near-circular ellipse or "halo"