StargazerBranden
Donator
I know there are several methods of rotating the argument of periapsis due to laws of Kepler Orbit/Newtonian physics. Apply prograde thrust when your mean anomaly equals 90 or 270 degrees, burn when your target is at apogee/apoapsis, or circularize your orbit at perigee, null out eccentricity, and at your new desired perigee raise apoapsis until original eccentricity and altitude is reached. The question is, when in regards to matching the argument of perigee to a specific target as it relates to rendezvous, which is a more efficient method?
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