Capabilities
Orbital Mechanics Engine
SGP4/SDP4 propagation, atmospheric drag modeling, and TLE processing for compliance-aware orbital analysis.
The ephemeris subsystem processes Two-Line Element sets from CelesTrak and propagates orbits using the SGP4 model for near-Earth objects and SDP4 for deep-space objects via the satellite.js library. Atmospheric drag modeling incorporates solar flux data (F10.7) and geomagnetic indices to predict orbital decay trajectories. Fuel depletion analysis models remaining delta-v against required disposal maneuvers. These physics outputs feed directly into compliance engines — determining whether a spacecraft will meet its 25-year deorbit obligation, maintain authorized orbital parameters, and retain sufficient fuel reserves for end-of-life disposal.
Key Capabilities
SGP4/SDP4 Propagation
Ingests NORAD TLE data and propagates position and velocity states forward in time, accounting for J2 perturbations, atmospheric drag, and solar radiation pressure.
Atmospheric Drag Modeling
Incorporates daily solar flux polling and geomagnetic activity indices to model drag-induced orbital decay with uncertainty bounds across solar cycle predictions.
Fuel Depletion Analysis
Tracks remaining propellant against planned maneuver budgets and regulatory disposal requirements to predict when fuel reserves become compliance-critical.