U0L1 3:2(1)- establishment trajectory (Rogers 2015 Table 4)

u0l1-3-2-1-establishment · source: literature · validation: V0

Signature

Bodies: E-M
Primary: Sun (default — heliocentric)
Sequence (canonical): E-M
Sense: outbound
Orbit class: Precursor
precursor MGA (one-shot insertion into a cycler)
Cycler class: single-ellipse
Returns: 1 — finite for epoch-locked classes
Validity window: 2025-11-25 → 2026-03-02
Launch epoch: 2025-11-25T00:00:00Z
Inserts into: U0L1 high-energy zero-loop one-synodic Earth-Mars cycler
Trajectory regime: ballistic
Maintenance ΔV band: unclassified
Model assumption: analytic-ephemeris
Mid-fidelity: real eccentricity / inclination retained; not full N-body.
Period: 2.135 yr (1 × E-M synodic)
1-synodic establishment timeline (single-Earth-orbit phasing).
V_∞ leveraging ΔV (establishment): 0.794 km/s
Source ephemeris: STOUR analytic ephemeris
Ephemeris model the source states its numbers were computed against.
Priority date: 2015-03-11

V∞ at encounters

E (encounter 1): 8.05 km/s
Rogers 2015 Table 4 row U0L1 '3:2(1)-': V∞ flyby = 8.049 km/s; V∞ launch = 3.702 km/s. Note the very large 4.35 km/s V_inf leveraging swing - U0L1's large aphelion (3.20 AU) requires high V_inf.
M (encounter 2): — (not published)
Rogers 2015 Table 4 tabulates V∞ launch and V∞ flyby, not a distinct V∞ at Mars.

Orbit elements (heliocentric)

Semi-major axis a: — AU
Eccentricity e: —
Perihelion: 0.960 AU
Aphelion: 3.189 AU
Inclination: —°

perihelion_au/aphelion_au SOURCED: Rogers 2015 Table 4 row U0L1 '3:2(1)-': Periapse = 0.960 AU, Apoapse = 3.189 AU.

Orbit view 2.5D ecliptic projection

spacecraft: analytic-ephemeris (real e/i retained) planets: J2000 osculating ellipse (Standish & Williams Table 1) clock: idealized phase clock (no epoch) orientation: coplanar-idealized (no Ω/ω published — in-plane ellipse) encounters: time-true on the idealized phase clock (real mean motions, phase chosen so the geometry's encounters occur)

— — planet orbit (true J2000 ellipse) ——— cycler ellipse

Definition status

incomplete — core fields missing or known-unknowns tracked below

Known-unknowns (1)

Values we expect to exist but have not yet filled (distinct from "not applicable"). Tracked per upstream docs/spec.md §16.6.4.

trajectory [unknown]
Per-segment trajectory topology not isolated from the accessible Rogers 2015 Table 4.

source: Rogers/Hughes/Longuski/Aldrin 2015 Acta Astro 112:114-125, Table 4.

Primary citation

Rogers, B. A. et al. (2015). Establishing cycler trajectories between Earth and Mars. Acta Astronautica 112:114-125 (2015).

DOI: 10.1016/j.actaastro.2015.03.002

orbit source Rogers et al. 2012, Table 1 orbit fidelity analytic-ephemeris V∞ source Rogers et al. 2012, Table 1 V∞ fidelity analytic-ephemeris

Notes

U0L1 cycler insertion variant (1-synodic 3:2(1)- timeline). U0L1 has the largest aphelion (3.20 AU, well beyond Mars) in Rogers Table 1, and correspondingly the largest leveraging benefit: 49.1 mt propellant savings via V-infinity leveraging (Rogers Table 9) vs the next-largest (Aldrin 3:2(1)- at 24.3 mt). The 0.794 km/s DSM is the highest in Rogers Table 4. Admitted as orbit_class=precursor_mga (2026-06-17). The inserts_into pointer resolves to mcconaghy-2005-em-u0l1.

Source quotes (per-field provenance)

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

launch_epoch: Rogers 2015 Table 4 row U0L1 '3:2(1)-': LD = 11/25/2025.
vinf_kms_at_encounters[0].vinf_kms: Rogers 2015 Table 4: V∞ flyby = 8.049 km/s.
v_infinity_leveraging_dv_kms: Rogers 2015 Table 4: ΔV_DSM = 0.794 km/s.
orbit_elements.perihelion_au: Rogers 2015 Table 4: Periapse = 0.960 AU.
orbit_elements.aphelion_au: Rogers 2015 Table 4: Apoapse = 3.189 AU.