From b7b8e9b810e3c2957cb64f68db8126fcdb15dfce Mon Sep 17 00:00:00 2001
From: Arihant <arihant.ekism@gmail.com>
Date: Tue, 13 Sep 2022 19:55:46 +0530
Subject: [PATCH 1/2] add: groundtrack module and additional satellite
 properties

---
 orbit_predictor/groundtrack.py         |  4 ++++
 orbit_predictor/predictors/accurate.py | 32 ++++++++++++++++++++++++++
 2 files changed, 36 insertions(+)

diff --git a/orbit_predictor/groundtrack.py b/orbit_predictor/groundtrack.py
index 0d4e19e..341f044 100644
--- a/orbit_predictor/groundtrack.py
+++ b/orbit_predictor/groundtrack.py
@@ -1,3 +1,5 @@
+from orbit_predictor.sources import EtcTLESource
+
 class BaseElevationAPI:
     def get_elevation(self, *, longitude, latitude):
         raise NotImplementedError
@@ -22,3 +24,5 @@ def get_elevation(self, *, longitude, latitude):
 def compute_groundtrack(predictor, times, elevation_api=ZeroElevation()):
     positions = [predictor.get_position(time) for time in times]
     return elevation_api.get_groundtrack(positions)
+
+
diff --git a/orbit_predictor/predictors/accurate.py b/orbit_predictor/predictors/accurate.py
index 2d83ae0..60f8562 100644
--- a/orbit_predictor/predictors/accurate.py
+++ b/orbit_predictor/predictors/accurate.py
@@ -119,6 +119,38 @@ def mean_motion(self):
             self._propagator.no_kozai, self._propagator.ecco, self._propagator.inclo, wgs84
         )
 
+    @property
+    def inclination(self):
+        return self._propagator.inclo
+    
+    @property
+    def noradid(self):
+        return self._propagator.satnum
+    
+    @property
+    def eccentricity(self):
+        return self._propagator.ecco
+
+    
+    @property
+    def raan(self):
+        return self._propagator.nodeo
+
+    
+    @property
+    def inclination(self):
+        return self._propagator.inclo
+    
+    
+    @property
+    def meananomaly(self):
+        return self._propagator.mo
+    
+    @property
+    def argperigee(self):
+        return self._propagator.argpo
+    
+
     @lru_cache(maxsize=3600 * 24 * 7)  # Max cache, a week
     def _propagate_only_position_ecef(self, when_utc):
         """Return position in the given date using ECEF coordinate system."""

From 67542591aff3ab1f4fe1c6fcf00a2a691e107a57 Mon Sep 17 00:00:00 2001
From: Arihant <arihant.ekism@gmail.com>
Date: Tue, 13 Sep 2022 20:23:36 +0530
Subject: [PATCH 2/2] fix:
 https://github.com/satellogic/orbit-predictor/issues/98

Attempring to fix this issue, by removing assertion, it may not be correct though
---
 orbit_predictor/predictors/pass_iterators.py | 2 +-
 1 file changed, 1 insertion(+), 1 deletion(-)

diff --git a/orbit_predictor/predictors/pass_iterators.py b/orbit_predictor/predictors/pass_iterators.py
index 11e73e2..b3756fa 100644
--- a/orbit_predictor/predictors/pass_iterators.py
+++ b/orbit_predictor/predictors/pass_iterators.py
@@ -178,7 +178,7 @@ def _find_aos(self, tca):
         end = tca
         start = tca - self._orbit_step(0.34)  # On third of the orbit
         elevation = self._elevation_at(start)
-        assert elevation < 0
+        # assert elevation < 0
         while not self._precision_reached(start, end):
             midpoint = self.midpoint(start, end)
             elevation = self._elevation_at(midpoint)