Predict satellite orbits with SGP4

Propagate TLE orbits and fit TLEs from state vectors using SGP4

Computing precise satellite positions for mission planning, ground station tracking, and orbital maintenance using industry-standard SGP4 propagator.

• · TLE (Two-Line Element) set
• · Propagation time in minutes from TLE epoch
• · Osculating state vectors (position, velocity) for TLE fitting

• · Position (TEME frame, km)
• · Velocity (TEME frame, km/s)
• · Fitted TLE or updated TLE epoch

• · Julia language
• · SatelliteToolboxSgp4.jl package
• · SatelliteToolboxBase and SatelliteToolboxTle (re-exported)

• · Valid TLE format (NORAD-standard two-line or three-line)
• · Propagation time in minutes (not seconds)
• · Julian date or epoch time available

• · TLE parsing fails on malformed format
• · Propagation time outside valid range (±30 days typical)
• · Fitted TLE diverges if input vectors not in TEME frame
• · WGS-84 vs WGS-72 mismatch causes coordinate errors

• · JuliaSpace/SatelliteToolboxSgp4.jl is aerospace-industry standard
• · WGS-84 and WGS-72 constants provided for different geoids
• · In-place variants available for low-allocation critical sections