FA-69719 / Orbital propagation / Member archive

Elliptic time of flight between anomalies: Mean anomaly adds the eccentric term · case 04

Durations near periapsis are too long.

Member previewVariant 4 · 3 implementations · 7 checks per implementation

Case contract

Input [a, e, nu1, nu2, mu] (degrees). Convert each true anomaly to eccentric anomaly with the half-angle atan2 form and to mean anomaly in [0,2pi); flight always proceeds forward, so dM=(M2-M1) mod 2pi. Return dM/n seconds rounded to 3 with n=sqrt(mu/a^3).

Why this case matters

Orbit determination and mission planning chain many small conversions; one wrong branch or unit silently moves a spacecraft by kilometres.

One recorded failure

Sample boundary fixture

This sample comes from the broken implementation of a controlled reproducer.

Boundary fixture	Actual	Expected	Outcome
elliptic time of flight between anomalies [26560.0, 0.7, 180.0, 200.0, 398600.4418]	`2023.92`	`8874.68`	Failed

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