diff --git a/docs/src/tutorials/orbit_propagation_example.md b/docs/src/tutorials/orbit_propagation_example.md
index b1ab73c..21a7e1b 100644
--- a/docs/src/tutorials/orbit_propagation_example.md
+++ b/docs/src/tutorials/orbit_propagation_example.md
@@ -73,14 +73,6 @@ t, epc, eci = sim!(orb, epcf)
 And that's it! All it took was 6 lines of code with the SatelliteDynamics 
 module to propagate an orbit. 
 
-<!-- We can visualize the orbit in inertial space:
-
-![](../plots/keplerian_orbit.svg)
-
-Or the evolution of the orbital elements:
-
-![](../plots/keplerian_elements.svg) -->
-
 ## Full Force Model
 
 We can also repeat the same propagation with a full force orbit model to see the
@@ -110,15 +102,4 @@ orb  = EarthInertialState(epc0, eci0, dt=1.0,
 
 # Propagate the orbit
 t, epc, eci = sim!(orb, epcf)
-```
-
-<!-- We can visualize the orbit in inertial space:
-
-![](../plots/fullforce_orbit.svg)
-
-Or the evolution of the orbital elements:
-
-![](../plots/fullforce_elements.svg)
-
-From these plots we can see the effect of the orbit perturbations on each of the
-orbital elements. -->
\ No newline at end of file
+```
\ No newline at end of file