Russell-Ocampo cycler 3.5.2.+0 (high-V_inf, short-transit, 3-synodic)

russell-ocampo-3.5.2+0 · source: literature · validation: V0

Signature

Bodies: E-M
Sequence (canonical): E-E-M-M
Sense: outbound
Period: 6.405 yr (3 × E-M synodic)
3 x Earth-Mars synodic period (2.135 yr) per Russell 2004 dissertation §3.8 row 3.5.2.+0; n_flybys = 5.
Priority date: 2003-02-09

V∞ at encounters

E (#1): 5.20 km/s
Russell 2004 dissertation Table 3.4 row 3.5.2.+0: Earth v_inf = 5.2 km/s.
M (#2): 9.20 km/s
Russell 2004 dissertation Table 3.4 row 3.5.2.+0: Mars v_inf = 9.2 km/s.

Orbit elements (heliocentric)

Semi-major axis a: — AU
Eccentricity e: —
Perihelion: — AU
Aphelion: 2.174 AU
Inclination: 0.00°

Aphelion derived from Russell 2004 Table 3.4 Aphelion Ratio AR = 1.43 x 1.52 AU (his §3.3 Mars reference radius) = 2.174 AU. Other elements (a, e, perihelion) not directly tabulated in Table 3.4.

Legs

E → M: 121 d, 0 revs
Russell 2004 dissertation Table 3.4 row 3.5.2.+0: Earth->Mars (or aphelion) time = 121 days.

Primary citation

Russell, R. P. & Ocampo, C. A. (2005). Geometric Analysis of Free-Return Trajectories Following a Gravity-Assisted Flyby. Journal of Spacecraft and Rockets, Vol. 42, No. 1, pp. 138-152.

DOI: 10.2514/1.5571

URL: https://arc.aiaa.org/doi/abs/10.2514/1.5571

Peer-reviewed venue for the 24-ballistic cycler catalogue (geometric analysis branch). The conference precursor (Russell/Ocampo AAS 03-145, Feb 2003) establishes priority.

Corroborating sources

Russell, R. P. & Ocampo, C. A. (2004). Systematic Method for Constructing Earth-Mars Cyclers Using Free-Return Trajectories. Journal of Guidance, Control, and Dynamics, Vol. 27, No. 3, pp. 321-335. DOI: 10.2514/1.1011
The companion JGCD paper that introduced the free-return construction method.
Russell, R. P. (2004). Global Search and Optimization for Free-Return Earth-Mars Cyclers. Ph.D. dissertation, University of Texas at Austin, Department of Aerospace Engineering. · link
Table 3.4 row 3.5.2.+0: AR=1.43, TR=1.06, E->M days=121, V_inf,E=5.2, V_inf,M=9.2, 5 flyby turning angles [83, 83, 83, 83, 24] deg. Strictly ballistic by Russell footnotes a/b (AR>=1 AND TR>=1).

Notes

Strictly ballistic per Russell's Table 3.4 footnotes a and b: AR=1.43 >= 1 means the cycler reaches Mars without a powered maneuver; TR=1.06 >= 1 means all required Earth flybys are physically attainable above the 200 km minimum altitude. 3-synodic period. 5 required Earth flybys (turning angles [83, 83, 83, 83, 24] deg per Russell Table 3.4 last column).

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: Russell 2004 dissertation Table 3.4 row 3.5.2.+0: Earth v_inf (km/s) = 5.2.
vinf_kms_at_encounters[1].vinf_kms: Russell 2004 dissertation Table 3.4 row 3.5.2.+0: Mars v_inf (km/s) = 9.2.
legs[0].tof_days: Russell 2004 dissertation Table 3.4 row 3.5.2.+0: Earth->Mars (or aphelion) Time (days) = 121.
aphelion_au: Russell 2004 dissertation Table 3.4 row 3.5.2.+0: Aphelion Ratio = 1.43 (Russell's §3.3 ratio to 1.52 AU = Mars sma); aphelion = 1.43 x 1.52 AU = 2.174 AU.
period.years: 3 x Earth-Mars synodic 2.135 yr = 6.405 yr; Russell 2004 §3.3 fixes synodic geometry on 1.875-yr Mars period (=15-yr alignment); 2.135 yr matches spec.md §9.