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malice
7dc1f9c28e
Adds a new SourceAdapter that publishes the current sub-satellite point
(lon, lat, alt) plus velocity + heading for every tracked NORAD ID every
60s on subject central.sat.position.<norad_id>. Complement to v0.11.1's
satpass_predict (observer-anchored pass alerts): sat_positions is the
GLOBAL counterpart, "where is sat X right now?" rather than "when does
sat X pass over observer Y?". Neither replaces the other.
data_class=telemetry surfaces these on /telemetry, not /events (60s ticks
across ~190 sats would drown discrete-event signal). Severity 1. Geo
centroid = sub-sat point so consumers can plot the satellite directly.
Refactors satpass_predict.py to import its pure SGP4 helpers from a new
sat_common.py module (matches the wfigs_common / swpc_common precedent).
Moved: EARTH_RADIUS_KM, gmst_rad, eci_to_ecef, subsatellite_point (4
symbols, ~25 lines of pure math). Observer-specific helpers stay in
satpass_predict.py. Existing satpass_predict tests pass unchanged.
CENTRAL_SAT stream max_bytes bumped from 1 GiB to 5 GiB to accommodate
the additional ~1.9 GiB/week of position events. STREAM_CATEGORY_DOMAINS
extended from ("tle", "pass") to ("tle", "pass", "position") so the
retention sweep covers position events.
Ships disabled (enabled=false) -- celestrak_tle must be enabled and have
polled at least once for sat_positions to have TLE data to propagate.
Co-Authored-By: Claude Opus 4.7 (1M context) <noreply@anthropic.com>
114 lines
4.3 KiB
Python
114 lines
4.3 KiB
Python
"""Tests for the shared satellite-math helpers extracted in v0.12.0.
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These pin the public API surface (no leading underscores) and the numerical
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behavior at known reference points. They duplicate some property tests from
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test_satpass_predict.py by design -- those test the helpers via internal
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re-exports (aliased imports), while these test the module's published
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interface directly. If the public names ever drift or get renamed, these
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fail first.
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"""
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from __future__ import annotations
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import math
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from datetime import datetime, timezone
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import pytest
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from sgp4.api import Satrec, jday
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from central.adapters.sat_common import (
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EARTH_RADIUS_KM,
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eci_to_ecef,
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gmst_rad,
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subsatellite_point,
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)
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# Live TLE from the v0.11.0 stations fixture, ISS (NORAD 25544).
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_ISS_L1 = "1 25544U 98067A 26159.80410962 .00007129 00000+0 13425-3 0 9999"
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_ISS_L2 = "2 25544 51.6336 341.5878 0006923 148.5365 211.6039 15.49672912570453"
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_REF = datetime(2026, 6, 9, 7, 0, 0, tzinfo=timezone.utc)
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class TestEarthRadius:
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def test_value_matches_wgs84_equatorial(self):
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assert EARTH_RADIUS_KM == pytest.approx(6378.137, abs=1e-6)
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class TestGmstRad:
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def test_returns_value_in_canonical_range(self):
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val = gmst_rad(2460835.0, 0.5) # arbitrary post-2000 JD
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assert 0.0 <= val < 2.0 * math.pi
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def test_monotonic_within_a_day(self):
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"""GMST advances ~2π per sidereal day. Two samples 6h apart must
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differ by roughly π/2 (modulo wraparound)."""
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v0 = gmst_rad(2460835.0, 0.0)
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v1 = gmst_rad(2460835.0, 0.25)
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delta = (v1 - v0) % (2.0 * math.pi)
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# 6h sidereal angle is slightly more than π/2 (sidereal day < solar day).
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assert math.pi / 2.0 < delta < math.pi / 2.0 + 0.02
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class TestEciToEcef:
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def test_zero_rotation_is_identity(self):
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result = eci_to_ecef((100.0, 200.0, 300.0), 0.0)
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assert result == pytest.approx((100.0, 200.0, 300.0))
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def test_rotation_preserves_magnitude(self):
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"""Rotation about the z-axis preserves the vector norm."""
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pos = (3000.0, 4000.0, 5000.0)
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rot = eci_to_ecef(pos, math.pi / 3.0)
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mag_in = math.sqrt(sum(c * c for c in pos))
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mag_out = math.sqrt(sum(c * c for c in rot))
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assert mag_out == pytest.approx(mag_in, rel=1e-12)
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def test_z_component_unaffected(self):
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"""Earth-rotation axis is z; z component never changes under GMST rotation."""
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_, _, z = eci_to_ecef((1.0, 2.0, 42.0), 1.3)
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assert z == 42.0
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class TestSubsatellitePoint:
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def test_north_pole_returns_pole(self):
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lon, lat, alt = subsatellite_point((0.0, 0.0, 7000.0))
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assert lat == pytest.approx(90.0)
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assert alt == pytest.approx(7000.0 - EARTH_RADIUS_KM)
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def test_equator_lon_zero(self):
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lon, lat, alt = subsatellite_point((EARTH_RADIUS_KM + 400.0, 0.0, 0.0))
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assert lon == pytest.approx(0.0)
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assert lat == pytest.approx(0.0)
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assert alt == pytest.approx(400.0, abs=1e-6)
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def test_equator_lon_90_east(self):
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lon, lat, alt = subsatellite_point((0.0, EARTH_RADIUS_KM + 400.0, 0.0))
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assert lon == pytest.approx(90.0)
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assert lat == pytest.approx(0.0)
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def test_lon_normalised_into_180_range(self):
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"""A satellite over the antimeridian (-y axis) reads as -90°, never +270°."""
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lon, _, _ = subsatellite_point((0.0, -(EARTH_RADIUS_KM + 400.0), 0.0))
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assert -180.0 <= lon <= 180.0
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assert lon == pytest.approx(-90.0)
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class TestIssRoundTripViaSgp4:
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"""End-to-end: TLE -> SGP4 ECI -> ECEF -> sub-sat point. Pins the math
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against a known orbital configuration. Drift from this would mean the
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helpers regressed in a way that affects production output."""
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def test_iss_sub_sat_point_at_pinned_ref_time(self):
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sat = Satrec.twoline2rv(_ISS_L1, _ISS_L2)
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jd, fr = jday(_REF.year, _REF.month, _REF.day,
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_REF.hour, _REF.minute, _REF.second)
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err, pos_eci, _ = sat.sgp4(jd, fr)
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assert err == 0
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pos_ecef = eci_to_ecef(pos_eci, gmst_rad(jd, fr))
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lon, lat, alt = subsatellite_point(pos_ecef)
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# ISS inclination 51.6° -- lat must lie within bounds
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assert -52.0 <= lat <= 52.0
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# lon in valid range
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assert -180.0 <= lon <= 180.0
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# ISS altitude ~400-420 km
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assert 380.0 <= alt <= 460.0
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