Predict where a satellite will be, then predict when a ground station can see it.
Two classic astrodynamics engines, your architecture. First an analytic Kepler propagator that advances an orbit by solving Kepler’s equation; then a pass predictor that turns the propagated orbit into rise, culmination and set times for a ground station — what every operations team runs daily.
Kepler’s equation & time of flightOrbit propagationGround-station passes
Objective
Implement kepler_propagate(coe, dt, mu) using a Newton iteration on Kepler’s equation, and predict_passes(coe, station, t0, hours) returning rise/max-elevation/set times. Validate against an independent numerical propagation.
Acceptance criteria
0/4
Workspace
Deliverables
•A module with solve_kepler, kepler_propagate and predict_passes.
•A validation script printing the error against a numerical propagation.
•A short worked example: a day of ISS passes over your city.
Stretch goals
•Account for Earth rotation and J₂ nodal regression and compare pass times after 7 days.
•Add sun-illumination checks so you can predict visible passes.