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Halowerk Satellite Pass Predictor
x402
Halowerk Satellite Pass Predictor is a paid API for AI agents from space.halowerk.com, paid per call via x402, $0.004/call, status unknown (last checked 2026-09-14).
Propagates a circular two-body orbit from orbital elements and samples when a satellite is visible above the horizon from a specified ground station location.
Price / call$0.004
Success—
StatusUnknown
How this service works
Propagates a circular two-body orbit from altitude, inclination, RAAN, and initial orbital phase; rotates Earth at a fixed sidereal rate; and samples ground-station elevation. It ignores eccentricity, perturbations, epoch-dependent Greenwich angle, refraction, ellipsoid shape, terrain, and antenna masks, so it is a planning estimate rather than operational ephemeris.
Output
A time-series list of sampled epochs indicating whether the satellite is above the specified minimum elevation angle from the ground station, along with computed elevation values at each step, effectively identifying pass windows (start, peak, end) within the simulation duration.
Example use cases
CubeSat downlink scheduling
“I need to schedule downlink windows for my CubeSat in a 400 km circular orbit, 97-degree inclination, RAAN 200 degrees, starting phase 0 degrees. My ground station is at 51.5 degrees north, -0.1 degrees longitude. Can you predict all passes over the next 6 hours with 30-second steps and a minimum elevation of 10 degrees?”
Amateur satellite contact planning
“When will a satellite at 800 km altitude, 65-degree inclination, RAAN 90 degrees, and initial phase 30 degrees pass over my location at 48.8 degrees north, 2.3 degrees east in the next 12 hours? Use 60-second steps and only show passes above 5 degrees elevation.”
Mission concept feasibility check
“I'm designing a relay mission at 1200 km altitude with 45-degree inclination, RAAN 0 degrees, and initial phase 0 degrees. How many contact windows would a ground station at 34 degrees north, 118 degrees west see over 48 hours, stepping every 120 seconds, with a minimum elevation of 8 degrees?”
Technical details
Endpoint
POSThttps://space.halowerk.com/v1/satellite-passWhen to prefer
Choose this endpoint when you need a fast, simplified circular-orbit pass prediction for planning purposes and do not require high-fidelity perturbation modeling, epoch-based Greenwich angle, terrain masking, or ellipsoid Earth corrections. Ideal for early mission design, link budget scheduling, or educational simulations where a two-body Keplerian approximation is sufficient.
Side effects
- altitude_km below 100 or above 100000 returns validation error
- duration_seconds or step_seconds outside allowed bounds returns 400
- ground latitude or longitude out of range returns parameter error
- missing required fields returns schema validation error
- very short step_seconds with long duration may produce large payloads
- result is a planning estimate only — perturbations, eccentricity, terrain, and real ephemeris not modeled
Input
Schema · Request body
| Field | Type | Description |
|---|---|---|
| raan_deg | number | Right ascension of ascending node relative to Greenwich at t=0. |
| altitude_km | number | Circular altitude above a spherical Earth. |
| step_seconds | integer | |
| inclination_deg | number | |
| duration_seconds | integer | |
| initial_phase_deg | number | Argument of latitude at t=0. |
| ground_latitude_deg | number | |
| ground_longitude_deg | number | |
| minimum_elevation_deg | number |
Tags
x402
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