Ballistic capture is a low energy method for a spacecraft to achieve an orbit around a distant planet or moon with no fuel required to go into orbit. In the ideal case, the transfer is ballistic (requiring zero Delta-v) after launch. In the traditional alternative to ballistic capture, spacecraft would either use a Hohmann transfer orbit or Oberth effect, which requires the spacecraft to burn fuel in order to slow down at the target. A requirement for the spacecraft to carry fuel adds to its cost and complexity.

To achieve ballistic capture the spacecraft is placed on a flight path ahead of the target's orbital path. The spacecraft then falls into the desired orbit, requiring only minor orbit corrections which may only need low power ion thrusters.

The first paper on using ballistic capture for transfer designed for spacecraft was written in 1987.[1] The mathematical theory that describes ballistic capture is called Weak Stability Boundary theory.[2]

Ballistic capture was first used by the Japanese spacecraft Hiten in 1991 as a method to get to the Moon.[3][4][5] This was designed by Edward Belbruno and J. Miller.[3][5] The ballistic capture transfer that performed this is an exterior ballistic capture transfer since it goes beyond the Earth-Moon distance. An interior ballistic capture transfer stays within the Earth-Moon distance.  This was described in 1987[1] and was first used by the ESA SMART-1 spacecraft in 2004.[2]

Advantages

Ballistic capture is predicted to be:

  • safer, as there is no time critical orbit insertion burn,
  • launchable at almost any time, rather than having to wait for a narrow launch window,
  • more fuel efficient for some missions.[2]
The trajectory of KPLO (Danuri) between Earth, Lagrange point #1, and Moon

Low-energy transfer

Trajectories that use ballistic capture are also known as a Low energy transfer (LET). More precisely, the terminology ballistic capture transfer (BCT) is used. They are low energy because they use no delta-V for capture. However, a low energy transfer need not be a ballistic capture transfer. The term ballistic lunar transfer (BLT) is also sometimes used.

The region about a target body where ballistic capture occurs is called a weak stability boundary.[2] The term weak stability boundary transfer is also used, or for short, WSB transfer.

In 2014, ballistic capture transfer was proposed as an alternate low energy transfer for future Mars missions.[6] It can be performed anytime, not only once per 26 months as in other maneuvers and does not involve dangerous and expensive (fuel cost) braking. But it takes up to one year, instead of nine months for a Hohmann transfer.[7]

Missions using ballistic capture

Animation of BepiColombo's trajectory from 20 October 2018 to 2 November 2025
   BepiColombo ·   Earth ·   Venus ·   Mercury ·   Sun
For more detailed animation, see this video

The following missions have used ballistic capture transfers,   (EBCT – Exterior ballistic capture transfer, IBCT – Interior ballistic capture transfer):

Missions using ballistic capture
MissionAgencyLaunchMethod
HitenISAS1991EBCT
SMART-1ESA2004IBCT
GRAILNASA2011EBCT
BepiColomboESA2018Ballistic capture - Mercury in 2025
CAPSTONENASA2022EBCT
DanuriKARI2022EBCT
Hakuto-R Mission 1ispace2022EBCT
SLIMJAXA/ISAS2023EBCT

See also

References

  1. 1 2 Belbruno, E (May 1987). "Lunar Capture Orbits, A method of Constructing Earth-Moon Trajectories and the Lunar GAS Mission" (PDF). Proceedings of AIAA/DGGLR/JSASS Inter. Elec. Propl. Conf. (87–1054). Bibcode:1987iep..conf.....B.
  2. 1 2 3 4 Belbruno, E (2004). Capture Dynamics and Chaotic Motions in Celestial Mechanics. Princeton University Press. ISBN 9780691094809.
  3. 1 2 Belbruno, E; Miller, J (June 1990). "A Ballistic Lunar Capture Transfer for the Japanese Spacecraft Hiten" (PDF). Technical Report JPL-IOM 312/90.4-1731-EAB. Jet Propulsion Laboratory.
  4. ↑ Belbruno, E (1992). "Through the Fuzzy Boundary: A New Route to the Moon" (PDF). The Planetary Report (Carl Sagan, Ed). 7 (3): 8–10 – via The Planetary Society.
  5. 1 2 Belbruno, E; Miller, J (1993). "Sun-Perturbed Earth-to-Moon Transfers with Ballistic" (PDF). J. Guidance Control, and Dynamics. 9 (4).
  6. ↑ Topputo, F; Belbruno, E (2015). "Earth–Mars transfers with ballistic capture". Celestial Mechanics and Dynamical Astronomy. 121 (4): 329–346. arXiv:1410.8856. Bibcode:2015CeMDA.121..329T. doi:10.1007/s10569-015-9605-8. S2CID 254373556.
  7. ↑ Hadhazy, Adam (22 December 2014). "A New Way to Reach Mars Safely, Anytime and on the Cheap". Scientific American. Retrieved 25 December 2014.

Further reading

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