The maneuver(s) by which a launch vehicle's payload achieves a stable orbit around Earth (or another body). For most LEO missions, orbital insertion occurs ~8-10 minutes after liftoff at first-stage MECO (main engine cutoff) followed by upper-stage burn. For GEO missions, orbital insertion is typically a multi-burn process spanning hours.
In LaunchDetect
LaunchDetect's detection records the ignition event; the post-detection trajectory and orbital insertion are derived from subsequent TLE updates by NORAD/CelesTrak.