# Why is a near rectilinear halo orbit proposed for LOP-G (formerly known as Deep Space Gateway?)

Why is a near rectilinear halo orbit a good place for a Lunar Orbital Platform-Gateway (formerly known as Deep Space Gateway)? Are there specific logistical and orbital-mechanical advantages over other possible orbits in cis-lunar space; other Lagrange point associated orbits or even high or elliptical lunar orbits for example?

The Deep Space Gateway would be initially placed in a near rectilinear halo orbit (NRHO) around the Moon.

• Did you have a look into the references at the end of the video? – AtmosphericPrisonEscape Dec 12 '17 at 16:00
• @AtmosphericPrisonEscape it's quite possible someone will have a better, different, or easier to understand answer. Let's see what happens. – uhoh Dec 12 '17 at 18:26

In fact, they are the preferred option among other staging orbits by analizing multiple factors:

EARTH ACCESS:

A study considering NASA SLS and Orion performances was carried out. Since SLS places Orion in a trans-lunar trajectory, Orion vehicle has to carried out orbital maneuvers to reach a orbit near the Moon, so the limiting factor will Orion's propellant load limitations. These makes difficult to access low-lunar orbits since an estimated budget of $\Delta V$=1250 m/s has to be enough for entering and leaving the orbit.

Analyzing the previous constraint, although for some epochs moon keplerian orbits were affordable, they were discarded because they were problemtic for continuous access. This reduces the candidates to orbits within the Restricted 3-Body Model: nominal L1/L2 halos (637-811 m/s), near-rectilinear halo orbit (NRO) (751-840 m/s) and distant retrograde orbit (DRO) (841-957 m/s).

LUNAR SURFACE ACCESS

This metric only measured transfer of the lander located at the staging orbit to a low lunar orbit (LLO) (the cost of descending and ascending from Moon surface to the LLO is assumed constant). Also, transfer time should be reasonable for the crew.

Obviously with this consideration, the preferred staging orbits would be keplerian orbits near the Moon, but they were discarded by Earth-access. It is not difficult to see that between the 3-Body Model orbits candidates the NRO provides the best metric by terms of $\Delta V$ and time, if a polar LLO is chosen (note that polar orbits guarantees global surface access waiting the required amount of time).