Ballistic capture
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
The first paper on using ballistic capture for transfer designed for spacecraft was written in 1987.
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]
Low-energy transfer
Trajectories that use ballistic capture are also known as a
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
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):
| Mission | Agency | Launch | Method |
|---|---|---|---|
| Hiten | ISAS | 1991 | EBCT |
| SMART-1 | ESA |
2004 | IBCT |
| GRAIL | NASA | 2011 | EBCT |
| BepiColombo | ESA | 2018 | Ballistic capture - Mercury in 2025 |
| CAPSTONE | NASA | 2022 | EBCT |
| Danuri | KARI |
2022 | EBCT |
Hakuto-R Mission 1 |
ispace | 2022 | EBCT |
| SLIM | JAXA/ISAS | 2023 | EBCT |
See also
References
- ^ Bibcode:1987iep..conf.....B.
- ^ ISBN 9780691094809.
- ^ a b 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.
- ^ 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.
- ^ a b Belbruno, E; Miller, J (1993). "Sun-Perturbed Earth-to-Moon Transfers with Ballistic" (PDF). Journal of Guidance, Control, and Dynamics. 9 (4).
- S2CID 254373556.
- ^ 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
- Lunar Transfer Orbits Utilizing Solar Perturbations and Ballistic Capture; Wolfgang Seefelder; 2002.
- Low Energy Transfer To The Moon
- Ballistic Lunar Transfer (BLT) Cheat Sheet
- Designing Low Energy Capture Transfers for Spacecraft to the Moon and Mars (Special Seminar in Symplectic Geometry). Institute for Advanced Study, Princeton. Tuesday October, 28 2014