diff --git a/docs/user/first_simulation.rst b/docs/user/first_simulation.rst
index 5e322dac5..b9f1d16e5 100644
--- a/docs/user/first_simulation.rst
+++ b/docs/user/first_simulation.rst
@@ -301,6 +301,14 @@ We can then see if the rocket is stable by plotting the static margin:
     If it is unreasonably **high**, your rocket is **super stable** and the
     simulation will most likely **fail**.
 
+
+To guarantee that the rocket is stable, the positions of all added components
+must be correct. The ``Rocket`` class can help you with the ``draw`` method:
+
+.. jupyter-execute::
+
+    calisto.draw()
+
 Running the Simulation
 ----------------------
 
diff --git a/docs/user/motors/hybridmotor.rst b/docs/user/motors/hybridmotor.rst
index 0105234af..9f373fa88 100644
--- a/docs/user/motors/hybridmotor.rst
+++ b/docs/user/motors/hybridmotor.rst
@@ -128,7 +128,7 @@ Finally we can add the oxidizer tank to the hybrid motor. This is done using the
 .. jupyter-execute::
 
   example_hybrid.add_tank(
-    tank = oxidizer_tank, position = 1.0115
+    tank = oxidizer_tank, position = 1.0615
   )
 
 And we can see all the results with:
diff --git a/docs/user/motors/liquidmotor.rst b/docs/user/motors/liquidmotor.rst
index 463d26dc4..5a1b4e8d5 100644
--- a/docs/user/motors/liquidmotor.rst
+++ b/docs/user/motors/liquidmotor.rst
@@ -91,14 +91,14 @@ curve, but keep in mind that you can use
       thrust_source=lambda t: 4000 - 100 * t**2,
       dry_mass=2,
       dry_inertia=(0.125, 0.125, 0.002),
-      nozzle_radius=0.15,
-      center_of_dry_mass_position=0.584,
+      nozzle_radius=0.075,
+      center_of_dry_mass_position=1.75,
       nozzle_position=0,
       burn_time=5,
       coordinate_system_orientation="nozzle_to_combustion_chamber",
   )
-  example_liquid.add_tank(tank=oxidizer_tank, position=0.6)
-  example_liquid.add_tank(tank=fuel_tank, position=1.8)
+  example_liquid.add_tank(tank=oxidizer_tank, position=1.0)
+  example_liquid.add_tank(tank=fuel_tank, position=2.5)
 
 
 .. caution::
@@ -120,7 +120,7 @@ curve, but keep in mind that you can use
 .. seealso:: 
     
     You can find details on each of the initialization parameters in 
-    :class:`rocketpy.SolidMotor.__init__`
+    :class:`rocketpy.LiquidMotor.__init__`
 
     And you can find details on adding tanks in :ref:`Adding Tanks`
 
diff --git a/docs/user/motors/tanks.rst b/docs/user/motors/tanks.rst
index 1a5c88961..5d027b3a3 100644
--- a/docs/user/motors/tanks.rst
+++ b/docs/user/motors/tanks.rst
@@ -174,7 +174,14 @@ and gas masses through time and is defined as such:
 
   More details can be found in :class:`rocketpy.MassFlowRateBasedTank.__init__`.
 
-We can some useful with:
+We can see some useful plots with:
+
+.. jupyter-execute::
+
+  # Draw the tank
+  N2O_flow_tank.draw()
+
+|
 
 .. jupyter-execute::
 
@@ -222,6 +229,13 @@ Then we can define the ``MassBasedTank`` as such:
 
 We can see some outputs with:
 
+.. jupyter-execute::
+
+  # Draw the tank
+  N2O_mass_tank.draw()
+
+|
+
 .. jupyter-execute::
 
   # Evolution of the Propellant Mass and the Mass flow rate
@@ -270,6 +284,13 @@ Then we can define the ``UllageBasedTank`` as such:
 
 We can see some outputs with:
 
+.. jupyter-execute::
+
+  # Draw the tank
+  N2O_ullage_tank.draw()
+
+|
+
 .. jupyter-execute::
 
   # Evolution of the Propellant Mass and the Mass flow rate
@@ -317,6 +338,13 @@ Then we can define the ``LevelBasedTank`` as such:
 
 We can see some outputs with:
 
+.. jupyter-execute::
+
+  # Draw the tank
+  N20_level_tank.draw()
+
+| 
+
 .. jupyter-execute::
 
   # Evolution of the Propellant Mass and the Mass flow rate
diff --git a/docs/user/rocket.rst b/docs/user/rocket.rst
index 119028608..ddd6fbfb4 100644
--- a/docs/user/rocket.rst
+++ b/docs/user/rocket.rst
@@ -224,6 +224,13 @@ to the rocket in one step:
     - :class:`rocketpy.Rocket.add_elliptical_fins`
     - :class:`rocketpy.Rocket.add_tail`
 
+Now we can see a representation of the rocket, this will guarantee that the
+rocket has been constructed correctly:
+
+.. jupyter-execute::
+
+    calisto.draw()
+
 
 Adding Airfoil Profile to Fins
 ~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~