Aldrin 3:2(1)- Variant (Analytic Ephemeris Establishment)

aldrin-3-2-1-establishment · source: literature · validation: V0

Signature

Bodies: E-M
Sequence (canonical): E-M
Sense: outbound
Period: 2.135 yr (1 × E-M synodic)
1-synodic establishment timeline.
Priority date: 2012-08-13

V∞ at encounters

E (#1): 6.55 km/s
Upper end of the 5.51-6.55 km/s range cited in Rogers 2012 Table 4 for the establishment architectures.
M (#2): — (not published)
Left null per spec rules; specific breakdown requires full table access.

Orbit elements (heliocentric)

Semi-major axis a: — AU
Eccentricity e: —
Perihelion: — AU
Aphelion: — AU
Inclination: —°

Primary citation

Rogers, B. A. et al. (2012). Preliminary Analysis of Establishing Cycler Trajectories Between Earth and Mars via V-Infinity Leveraging. AIAA 2012-4746.

DOI: 10.2514/6.2012-4746

Notes

The 3:2 variant (spacecraft completes 3 orbits per 2 Earth orbits) allows a 1-synodic (2.135 yr) establishment. Incurs a slightly higher V_inf at Earth (6.55 km/s) than the 4:3(2) variant.

Source quotes (per-field provenance)

Every numerical value in this entry traces to a verbatim or paraphrased quote from a cited source.

vinf_kms_at_encounters[0].vinf_kms: Rogers et al. 2012 Table 4 reports V_inf,flyby ranging 5.51-6.55 km/s.
period.years: Rogers et al. 2012: the (1) notation indicates a 1-synodic establishment timeline (2.135 yr).