1. LEO Orbit Secular Precession Analysis
Flight Dynamics EngineerBackground
An engineer needs to verify the nodal drift and perigee rotation rates of a low-Earth observation satellite over a 30-day period.
Problem
Calculate secular drift caused by higher-order zonals and verify agreement between mean-element propagation and numerical integration.
How to use
Set semi-major axis to 8000 km, eccentricity to 0.05, inclination to 52.5°, select J2–J4 zonal depth with no third-body perturbations, and enable the reconstruction panel.
semiMajorAxisKm: 8000, eccentricity: 0.05, inclinationDeg: 52.5, raanDeg: 30, argPerigeeDeg: 70, meanAnomalyDeg: 0, durationDays: 30, zonalDepth: "j2-j4", lunisolar: "none", showReconstruction: trueOutcome
Generated report detailing RAAN drift of approximately −2.76°/day, perigee drift of +1.9°/day, ground-track resonance evaluation, and an RK4 cross-validation within 1e-4 eccentricity deviation.