From c33592fbc9cf21c9e31c0b7c682849edc50e0632 Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Thu, 7 Mar 2024 02:17:25 -0500
Subject: [PATCH 01/20] BUG: use rocket.dry_mass instead of rocket.mass in the
 u_dot_parachute

---
 rocketpy/simulation/flight.py | 2 +-
 1 file changed, 1 insertion(+), 1 deletion(-)

diff --git a/rocketpy/simulation/flight.py b/rocketpy/simulation/flight.py
index 326b5db04..48f94d156 100644
--- a/rocketpy/simulation/flight.py
+++ b/rocketpy/simulation/flight.py
@@ -1911,7 +1911,7 @@ def u_dot_parachute(self, t, u, post_processing=False):
         rho = self.env.density.get_value_opt(u[2])
         to = 1.2
         ma = ka * rho * (4 / 3) * np.pi * R**3
-        mp = self.rocket.mass
+        mp = self.rocket.dry_mass
         eta = 1
         Rdot = (6 * R * (1 - eta) / (1.2**6)) * (
             (1 - eta) * t**5 + eta * (to**3) * (t**2)

From 54fb66e3e50264407158db18d2f32cf1afc065c9 Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Thu, 7 Mar 2024 02:18:08 -0500
Subject: [PATCH 02/20] DOC: improve Rocket.dry_mass documentation (prevent
 future mistakes)

---
 rocketpy/rocket/rocket.py | 13 ++++++-------
 1 file changed, 6 insertions(+), 7 deletions(-)

diff --git a/rocketpy/rocket/rocket.py b/rocketpy/rocket/rocket.py
index ffcf3b1c8..8154f2967 100644
--- a/rocketpy/rocket/rocket.py
+++ b/rocketpy/rocket/rocket.py
@@ -61,6 +61,9 @@ class Rocket:
         pointing from the rocket's nose cone to the rocket's tail.
     Rocket.mass : float
         Rocket's mass without motor and propellant, measured in kg.
+    Rocket.dry_mass : float
+        Rocket's mass without propellant, measured in kg. It does include the
+        motor mass.
     Rocket.center_of_mass : Function
         Position of the rocket's center of mass, including propellant, relative
         to the user defined rocket reference system.
@@ -394,22 +397,18 @@ def evaluate_total_mass(self):
     def evaluate_dry_mass(self):
         """Calculates and returns the rocket's dry mass. The dry
         mass is defined as the sum of the motor's dry mass and the
-        rocket mass without motor. The function returns an object
-        of the Function class and is defined as a function of time.
+        rocket mass without motor.
 
         Returns
         -------
-        self.total_mass : Function
-            Function of time expressing the total mass of the rocket,
-            defined as the sum of the propellant mass and the rocket
-            mass without propellant.
+        self.dry_mass : float
+            Rocket's dry mass (Rocket + Motor) (kg)
         """
         # Make sure there is a motor associated with the rocket
         if self.motor is None:
             print("Please associate this rocket with a motor!")
             return False
 
-        # Calculate total dry mass: motor (without propellant) + rocket mass
         self.dry_mass = self.mass + self.motor.dry_mass
 
         return self.dry_mass

From 9ab1629ae831a729627ab45b5c9db65c67cfbf03 Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Thu, 7 Mar 2024 02:18:59 -0500
Subject: [PATCH 03/20] TST: update tests expected values after last bug
 solving. - See the last 3 commits to understand.

---
 tests/test_flight.py         | 4 ++--
 tests/unit/test_utilities.py | 2 +-
 2 files changed, 3 insertions(+), 3 deletions(-)

diff --git a/tests/test_flight.py b/tests/test_flight.py
index a2e42281c..f9a939667 100644
--- a/tests/test_flight.py
+++ b/tests/test_flight.py
@@ -691,7 +691,7 @@ def test_accelerations(flight_calisto_custom_wind, flight_time, expected_values)
         ("t_initial", (0, 0, 0)),
         ("out_of_rail_time", (0, 2.248727, 25.703072)),
         ("apogee_time", (-13.209436, 16.05115, -0.000257)),
-        ("t_final", (5, 2, -5.334289)),
+        ("t_final", (5, 2, -5.65998)),
     ],
 )
 def test_velocities(flight_calisto_custom_wind, flight_time, expected_values):
@@ -729,7 +729,7 @@ def test_velocities(flight_calisto_custom_wind, flight_time, expected_values):
         ("t_initial", (1.6542528, 0.65918, -0.067107)),
         ("out_of_rail_time", (5.05334, 2.01364, -1.7541)),
         ("apogee_time", (2.35291, -1.8275, -0.87851)),
-        ("t_final", (0, 0, 141.42421)),
+        ("t_final", (0, 0, 159.2212)),
     ],
 )
 def test_aerodynamic_forces(flight_calisto_custom_wind, flight_time, expected_values):
diff --git a/tests/unit/test_utilities.py b/tests/unit/test_utilities.py
index 68dbc3d7f..b07064906 100644
--- a/tests/unit/test_utilities.py
+++ b/tests/unit/test_utilities.py
@@ -153,7 +153,7 @@ def test_fin_flutter_analysis(flight_calisto_custom_wind):
     assert np.isclose(flutter_mach(np.inf), 1.0048188594647927, atol=5e-3)
     assert np.isclose(safety_factor(0), 64.78797, atol=5e-3)
     assert np.isclose(safety_factor(10), 2.1948620401502072, atol=5e-3)
-    assert np.isclose(safety_factor(np.inf), 65.40588722032527, atol=5e-3)
+    assert np.isclose(safety_factor(np.inf), 61.64222220469224, atol=5e-3)
 
 
 def test_flutter_prints(flight_calisto_custom_wind):

From feb1791b46245422f26cb60e9c5a0ee221d769c9 Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Thu, 7 Mar 2024 02:39:01 -0500
Subject: [PATCH 04/20] TST: Add assertion for impact velocity in
 test_bella_lui_rocket.py

---
 tests/acceptance/test_bella_lui_rocket.py | 7 +++++++
 1 file changed, 7 insertions(+)

diff --git a/tests/acceptance/test_bella_lui_rocket.py b/tests/acceptance/test_bella_lui_rocket.py
index 69669c66f..a1297e1fb 100644
--- a/tests/acceptance/test_bella_lui_rocket.py
+++ b/tests/acceptance/test_bella_lui_rocket.py
@@ -242,3 +242,10 @@ def drogue_trigger(p, h, y):
     assert (
         abs(apogee_time_measured - apogee_time_simulated) / apogee_time_simulated < 0.02
     )
+    # Guarantee the impact velocity is within 30% of the real data.
+    # Use the last 5 real points to avoid outliers
+    assert (
+        abs(test_flight.impact_velocity - np.mean(vert_vel_kalt[-5:]))
+        / abs(test_flight.impact_velocity)
+        < 0.30
+    )

From 0829a779ed27c567f50b670a8106c1a3277d4de2 Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Thu, 7 Mar 2024 02:39:31 -0500
Subject: [PATCH 05/20] DEV: update changelog

---
 CHANGELOG.md | 5 +++++
 1 file changed, 5 insertions(+)

diff --git a/CHANGELOG.md b/CHANGELOG.md
index 4ab36ca79..0aec0e229 100644
--- a/CHANGELOG.md
+++ b/CHANGELOG.md
@@ -38,6 +38,11 @@ and this project adheres to [Semantic Versioning](http://semver.org/).
 
 ### Fixed
 
+## [v1.2.2] - 2024-03-dd
+
+You can install this version by running `pip install rocketpy==1.2.2`
+
+- BUG: wrong rocket mass in parachute u dot method [#569](https://github.com/RocketPy-Team/RocketPy/pull/569)
 
 ## [v1.2.1] - 2024-02-22
 

From 014e633aae170219da41e9b2156b917fcafafde3 Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Thu, 7 Mar 2024 18:37:08 -0500
Subject: [PATCH 06/20] ENH: Add new stability margin properties to Flight
 class

---
 rocketpy/simulation/flight.py | 20 ++++++++++++++++++++
 1 file changed, 20 insertions(+)

diff --git a/rocketpy/simulation/flight.py b/rocketpy/simulation/flight.py
index 326b5db04..c642d1123 100644
--- a/rocketpy/simulation/flight.py
+++ b/rocketpy/simulation/flight.py
@@ -2426,6 +2426,26 @@ def min_stability_margin(self):
         """Minimum stability margin."""
         return self.stability_margin(self.min_stability_margin_time)
 
+    @property
+    def initial_stability_margin(self):
+        """Stability margin at time 0.
+        
+        Returns
+        -------
+        float
+        """
+        return self.stability_margin(0)
+
+    @property
+    def out_of_rail_stability_margin(self):
+        """Stability margin at the time the rocket leaves the rail.
+        
+        Returns
+        -------
+        float
+        """
+        return self.stability_margin(self.out_of_rail_time)
+
     # Reynolds Number
     @funcify_method("Time (s)", "Reynolds Number", "spline", "zero")
     def reynolds_number(self):

From 6779a3e191430ee1491d598af80184eb3c4de791 Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Thu, 7 Mar 2024 18:37:20 -0500
Subject: [PATCH 07/20] TST: Add tests for initial and out-of-rail stability
 margins in Flight class

---
 tests/unit/test_flight.py | 28 ++++++++++++++++++++++++++++
 1 file changed, 28 insertions(+)

diff --git a/tests/unit/test_flight.py b/tests/unit/test_flight.py
index 87249cf44..e6ab6b8b8 100644
--- a/tests/unit/test_flight.py
+++ b/tests/unit/test_flight.py
@@ -258,3 +258,31 @@ def test_get_controller_observed_variables(flight_calisto_air_brakes):
     obs_vars = flight_calisto_air_brakes.get_controller_observed_variables()
     assert isinstance(obs_vars, list)
     assert len(obs_vars) == 0
+
+
+def test_initial_stability_margin(flight_calisto_custom_wind):
+    """Test the initial_stability_margin method of the Flight class.
+
+    Parameters
+    ----------
+    flight_calisto_custom_wind : rocketpy.Flight
+    """
+    res = flight_calisto_custom_wind.initial_stability_margin
+    assert isinstance(res, float)
+    assert res == flight_calisto_custom_wind.stability_margin(0)
+    assert np.isclose(res, 2.05, atol=0.1)
+
+
+def test_out_of_rail_stability_margin(flight_calisto_custom_wind):
+    """Test the out_of_rail_stability_margin method of the Flight class.
+
+    Parameters
+    ----------
+    flight_calisto_custom_wind : rocketpy.Flight
+    """
+    res = flight_calisto_custom_wind.out_of_rail_stability_margin
+    assert isinstance(res, float)
+    assert res == flight_calisto_custom_wind.stability_margin(
+        flight_calisto_custom_wind.out_of_rail_time
+    )
+    assert np.isclose(res, 2.14, atol=0.1)

From 55e5cc25cd70c367ea62898fe1fc0e198cb2a4e5 Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Thu, 7 Mar 2024 18:38:42 -0500
Subject: [PATCH 08/20] MNT: update CHANGELOG.md

---
 CHANGELOG.md | 1 +
 1 file changed, 1 insertion(+)

diff --git a/CHANGELOG.md b/CHANGELOG.md
index 7ff32bd8d..6345de19f 100644
--- a/CHANGELOG.md
+++ b/CHANGELOG.md
@@ -32,6 +32,7 @@ and this project adheres to [Semantic Versioning](http://semver.org/).
 
 ### Added
 
+- ENH: Add new stability margin properties to Flight class [#572](https://github.com/RocketPy-Team/RocketPy/pull/572)
 - ENH: adds `Function.remove_outliers` method [#554](https://github.com/RocketPy-Team/RocketPy/pull/554)
 
 ### Changed

From c8b26b63f28271d415e79b9e566ed7ee01af1d47 Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Thu, 7 Mar 2024 18:43:22 -0500
Subject: [PATCH 09/20] DOC: Add initial and out-of-rail stability margins to
 Flight class documentation

---
 rocketpy/simulation/flight.py | 8 ++++++--
 1 file changed, 6 insertions(+), 2 deletions(-)

diff --git a/rocketpy/simulation/flight.py b/rocketpy/simulation/flight.py
index c642d1123..ff0ee1840 100644
--- a/rocketpy/simulation/flight.py
+++ b/rocketpy/simulation/flight.py
@@ -426,6 +426,10 @@ class Flight:
         Rocket's static margin during flight in calibers.
     Flight.stability_margin : Function
             Rocket's stability margin during flight, in calibers.
+    Flight.initial_stability_margin : float
+        Rocket's initial stability margin in calibers.
+    Flight.out_of_rail_stability_margin : float
+        Rocket's stability margin in calibers when it leaves the rail.
     Flight.stream_velocity_x : Function
         Freestream velocity x (East) component, in m/s, as a function of
         time. Can be called or accessed as array.
@@ -2429,7 +2433,7 @@ def min_stability_margin(self):
     @property
     def initial_stability_margin(self):
         """Stability margin at time 0.
-        
+
         Returns
         -------
         float
@@ -2439,7 +2443,7 @@ def initial_stability_margin(self):
     @property
     def out_of_rail_stability_margin(self):
         """Stability margin at the time the rocket leaves the rail.
-        
+
         Returns
         -------
         float

From 864fd6d0355232989c4fe7ded5b132e500515ef2 Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Sat, 9 Mar 2024 07:09:40 -0500
Subject: [PATCH 10/20] REL: Update version to 1.2.2

---
 CHANGELOG.md               | 2 +-
 docs/conf.py               | 2 +-
 docs/user/installation.rst | 2 +-
 setup.py                   | 2 +-
 4 files changed, 4 insertions(+), 4 deletions(-)

diff --git a/CHANGELOG.md b/CHANGELOG.md
index 0aec0e229..9732e38f5 100644
--- a/CHANGELOG.md
+++ b/CHANGELOG.md
@@ -38,7 +38,7 @@ and this project adheres to [Semantic Versioning](http://semver.org/).
 
 ### Fixed
 
-## [v1.2.2] - 2024-03-dd
+## [v1.2.2] - 2024-03-09
 
 You can install this version by running `pip install rocketpy==1.2.2`
 
diff --git a/docs/conf.py b/docs/conf.py
index f2397dfa8..75f7a18a7 100644
--- a/docs/conf.py
+++ b/docs/conf.py
@@ -24,7 +24,7 @@
 author = "RocketPy Team"
 
 # The full version, including alpha/beta/rc tags
-release = "1.2.1"
+release = "1.2.2"
 
 
 # -- General configuration ---------------------------------------------------
diff --git a/docs/user/installation.rst b/docs/user/installation.rst
index 16dec6886..328a251a4 100644
--- a/docs/user/installation.rst
+++ b/docs/user/installation.rst
@@ -19,7 +19,7 @@ If you want to choose a specific version to guarantee compatibility, you may ins
 
 .. code-block:: shell
 
-    pip install rocketpy==1.2.1
+    pip install rocketpy==1.2.2
 
 
 Optional Installation Method: ``conda``
diff --git a/setup.py b/setup.py
index 73d989de4..96f21a8d3 100644
--- a/setup.py
+++ b/setup.py
@@ -23,7 +23,7 @@
 
 setuptools.setup(
     name="rocketpy",
-    version="1.2.1",
+    version="1.2.2",
     install_requires=necessary_require,
     extras_require={
         "env_analysis": env_analysis_require,

From 1aecd491ddc1f455046567164b23fe1c8bd9a0be Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Thu, 7 Mar 2024 18:37:08 -0500
Subject: [PATCH 11/20] ENH: Add new stability margin properties to Flight
 class

---
 rocketpy/simulation/flight.py | 20 ++++++++++++++++++++
 1 file changed, 20 insertions(+)

diff --git a/rocketpy/simulation/flight.py b/rocketpy/simulation/flight.py
index 326b5db04..c642d1123 100644
--- a/rocketpy/simulation/flight.py
+++ b/rocketpy/simulation/flight.py
@@ -2426,6 +2426,26 @@ def min_stability_margin(self):
         """Minimum stability margin."""
         return self.stability_margin(self.min_stability_margin_time)
 
+    @property
+    def initial_stability_margin(self):
+        """Stability margin at time 0.
+        
+        Returns
+        -------
+        float
+        """
+        return self.stability_margin(0)
+
+    @property
+    def out_of_rail_stability_margin(self):
+        """Stability margin at the time the rocket leaves the rail.
+        
+        Returns
+        -------
+        float
+        """
+        return self.stability_margin(self.out_of_rail_time)
+
     # Reynolds Number
     @funcify_method("Time (s)", "Reynolds Number", "spline", "zero")
     def reynolds_number(self):

From c36d27f9e3d1cd3c0487d1f68d39ade8fa39572a Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Thu, 7 Mar 2024 18:37:20 -0500
Subject: [PATCH 12/20] TST: Add tests for initial and out-of-rail stability
 margins in Flight class

---
 tests/unit/test_flight.py | 28 ++++++++++++++++++++++++++++
 1 file changed, 28 insertions(+)

diff --git a/tests/unit/test_flight.py b/tests/unit/test_flight.py
index 87249cf44..e6ab6b8b8 100644
--- a/tests/unit/test_flight.py
+++ b/tests/unit/test_flight.py
@@ -258,3 +258,31 @@ def test_get_controller_observed_variables(flight_calisto_air_brakes):
     obs_vars = flight_calisto_air_brakes.get_controller_observed_variables()
     assert isinstance(obs_vars, list)
     assert len(obs_vars) == 0
+
+
+def test_initial_stability_margin(flight_calisto_custom_wind):
+    """Test the initial_stability_margin method of the Flight class.
+
+    Parameters
+    ----------
+    flight_calisto_custom_wind : rocketpy.Flight
+    """
+    res = flight_calisto_custom_wind.initial_stability_margin
+    assert isinstance(res, float)
+    assert res == flight_calisto_custom_wind.stability_margin(0)
+    assert np.isclose(res, 2.05, atol=0.1)
+
+
+def test_out_of_rail_stability_margin(flight_calisto_custom_wind):
+    """Test the out_of_rail_stability_margin method of the Flight class.
+
+    Parameters
+    ----------
+    flight_calisto_custom_wind : rocketpy.Flight
+    """
+    res = flight_calisto_custom_wind.out_of_rail_stability_margin
+    assert isinstance(res, float)
+    assert res == flight_calisto_custom_wind.stability_margin(
+        flight_calisto_custom_wind.out_of_rail_time
+    )
+    assert np.isclose(res, 2.14, atol=0.1)

From 36fb6b5dca9343dbb9d3483546ade4ec9a8709f7 Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Thu, 7 Mar 2024 18:38:42 -0500
Subject: [PATCH 13/20] MNT: update CHANGELOG.md

---
 CHANGELOG.md | 1 +
 1 file changed, 1 insertion(+)

diff --git a/CHANGELOG.md b/CHANGELOG.md
index 3a8476ad6..3586d54e3 100644
--- a/CHANGELOG.md
+++ b/CHANGELOG.md
@@ -32,6 +32,7 @@ and this project adheres to [Semantic Versioning](http://semver.org/).
 
 ### Added
 
+- ENH: Add new stability margin properties to Flight class [#572](https://github.com/RocketPy-Team/RocketPy/pull/572)
 - ENH: adds `Function.remove_outliers` method [#554](https://github.com/RocketPy-Team/RocketPy/pull/554)
 
 ### Changed

From 1264a67b8f5e7386f650132ccef67406dd2446a0 Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Thu, 7 Mar 2024 18:43:22 -0500
Subject: [PATCH 14/20] DOC: Add initial and out-of-rail stability margins to
 Flight class documentation

---
 rocketpy/simulation/flight.py | 8 ++++++--
 1 file changed, 6 insertions(+), 2 deletions(-)

diff --git a/rocketpy/simulation/flight.py b/rocketpy/simulation/flight.py
index c642d1123..ff0ee1840 100644
--- a/rocketpy/simulation/flight.py
+++ b/rocketpy/simulation/flight.py
@@ -426,6 +426,10 @@ class Flight:
         Rocket's static margin during flight in calibers.
     Flight.stability_margin : Function
             Rocket's stability margin during flight, in calibers.
+    Flight.initial_stability_margin : float
+        Rocket's initial stability margin in calibers.
+    Flight.out_of_rail_stability_margin : float
+        Rocket's stability margin in calibers when it leaves the rail.
     Flight.stream_velocity_x : Function
         Freestream velocity x (East) component, in m/s, as a function of
         time. Can be called or accessed as array.
@@ -2429,7 +2433,7 @@ def min_stability_margin(self):
     @property
     def initial_stability_margin(self):
         """Stability margin at time 0.
-        
+
         Returns
         -------
         float
@@ -2439,7 +2443,7 @@ def initial_stability_margin(self):
     @property
     def out_of_rail_stability_margin(self):
         """Stability margin at the time the rocket leaves the rail.
-        
+
         Returns
         -------
         float

From ee01e9dd9f159d463e642465244ebe08f4038565 Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Thu, 21 Mar 2024 15:29:08 -0400
Subject: [PATCH 15/20] MNT: Fix initial stability margin calculation in Flight
 class

---
 rocketpy/simulation/flight.py | 2 +-
 1 file changed, 1 insertion(+), 1 deletion(-)

diff --git a/rocketpy/simulation/flight.py b/rocketpy/simulation/flight.py
index ff0ee1840..344a831fb 100644
--- a/rocketpy/simulation/flight.py
+++ b/rocketpy/simulation/flight.py
@@ -2438,7 +2438,7 @@ def initial_stability_margin(self):
         -------
         float
         """
-        return self.stability_margin(0)
+        return self.stability_margin(self.time[0])
 
     @property
     def out_of_rail_stability_margin(self):

From c9cc0deb6393ed38b3dc18b9d0c8dc59ee840e42 Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Fri, 22 Mar 2024 06:12:41 -0400
Subject: [PATCH 16/20] ENH: add new stability Flight properties to flight
 prints

---
 rocketpy/prints/flight_prints.py | 18 ++++++++++--------
 1 file changed, 10 insertions(+), 8 deletions(-)

diff --git a/rocketpy/prints/flight_prints.py b/rocketpy/prints/flight_prints.py
index 5b1f9b914..ec702a12c 100644
--- a/rocketpy/prints/flight_prints.py
+++ b/rocketpy/prints/flight_prints.py
@@ -67,8 +67,7 @@ def initial_conditions(self):
                 self.flight.w1(0), self.flight.w2(0), self.flight.w3(0)
             )
         )
-
-        return None
+        print(f"Initial Stability Margin: {self.flight.initial_stability_margin:.3f} c")
 
     def numerical_integration_settings(self):
         """Prints out the Numerical Integration settings available about the
@@ -150,9 +149,8 @@ def out_of_rail_conditions(self):
         print("\nRail Departure State\n")
         print("Rail Departure Time: {:.3f} s".format(self.flight.out_of_rail_time))
         print(
-            "Rail Departure Velocity: {:.3f} m/s".format(
-                self.flight.out_of_rail_velocity
-            )
+            "Rail Departure Stability Margin: "
+            f"{self.flight.out_of_rail_stability_margin:.3f} c"
         )
         print(
             "Rail Departure Stability Margin: {:.3f} c".format(
@@ -408,9 +406,13 @@ def stability_margin(self):
         about the flight."""
         print("\nStability Margin\n")
         print(
-            "Maximum Stability Margin: {:.3f} c at {:.2f} s".format(
-                self.flight.max_stability_margin, self.flight.max_stability_margin_time
-            )
+            f"Initial Stability Margin: {self.flight.initial_stability_margin:.3f} c "
+            f"at {self.flight.time[0]:.2f} s"
+        )
+        print(
+            "Out of Rail Stability Margin: "
+            f"{self.flight.out_of_rail_stability_margin:.3f} c "
+            f"at {self.flight.out_of_rail_time:.2f} s"
         )
         print(
             "Minimum Stability Margin: {:.3f} c at {:.2f} s".format(

From 2456b119baccafff2df4fcea5a9a37fa0b8d55d4 Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Fri, 22 Mar 2024 06:14:47 -0400
Subject: [PATCH 17/20] BUG: refactor the initial_conditions
 _FlightPrints.method to use correct initial time - This also adopts f-string
 interpolation for the initial_conditions prints

---
 rocketpy/prints/flight_prints.py | 41 +++++++++++++++-----------------
 1 file changed, 19 insertions(+), 22 deletions(-)

diff --git a/rocketpy/prints/flight_prints.py b/rocketpy/prints/flight_prints.py
index ec702a12c..b9be3f6ee 100644
--- a/rocketpy/prints/flight_prints.py
+++ b/rocketpy/prints/flight_prints.py
@@ -33,39 +33,36 @@ def initial_conditions(self):
         -------
         None
         """
-
         print("\nInitial Conditions\n")
 
-        # Post-process results
-        if self.flight.post_processed is False:
-            self.flight.post_process()
+        t_init = self.flight.time[0]
+
+        print(f"Initial time: {t_init:.3f} s")
         print(
-            "Position - x: {:.2f} m | y: {:.2f} m | z: {:.2f} m".format(
-                self.flight.x(0), self.flight.y(0), self.flight.z(0)
-            )
+            f"Position - x: {self.flight.x(t_init):.2f} m | "
+            f"y: {self.flight.y(t_init):.2f} m | "
+            f"z: {self.flight.z(t_init):.2f} m"
         )
         print(
-            "Velocity - Vx: {:.2f} m/s | Vy: {:.2f} m/s | Vz: {:.2f} m/s".format(
-                self.flight.vx(0), self.flight.vy(0), self.flight.vz(0)
-            )
+            f"Velocity - Vx: {self.flight.vx(t_init):.2f} m/s | "
+            f"Vy: {self.flight.vy(t_init):.2f} m/s | "
+            f"Vz: {self.flight.vz(t_init):.2f} m/s"
         )
         print(
-            "Attitude - e0: {:.3f} | e1: {:.3f} | e2: {:.3f} | e3: {:.3f}".format(
-                self.flight.e0(0),
-                self.flight.e1(0),
-                self.flight.e2(0),
-                self.flight.e3(0),
-            )
+            f"Attitude (quaternions) - e0: {self.flight.e0(t_init):.3f} | "
+            f"e1: {self.flight.e1(t_init):.3f} | "
+            f"e2: {self.flight.e2(t_init):.3f} | "
+            f"e3: {self.flight.e3(t_init):.3f}"
         )
         print(
-            "Euler Angles - Spin φ : {:.2f}° | Nutation θ: {:.2f}° | Precession ψ: {:.2f}°".format(
-                self.flight.phi(0), self.flight.theta(0), self.flight.psi(0)
-            )
+            f"Euler Angles - Spin φ : {self.flight.phi(t_init):.2f}° | "
+            f"Nutation θ: {self.flight.theta(t_init):.2f}° | "
+            f"Precession ψ: {self.flight.psi(t_init):.2f}°"
         )
         print(
-            "Angular Velocity - ω1: {:.2f} rad/s | ω2: {:.2f} rad/s| ω3: {:.2f} rad/s".format(
-                self.flight.w1(0), self.flight.w2(0), self.flight.w3(0)
-            )
+            f"Angular Velocity - ω1: {self.flight.w1(t_init):.2f} rad/s | "
+            f"ω2: {self.flight.w2(t_init):.2f} rad/s | "
+            f"ω3: {self.flight.w3(t_init):.2f} rad/s"
         )
         print(f"Initial Stability Margin: {self.flight.initial_stability_margin:.3f} c")
 

From 844b36399c3b2e5cfa927df37c9a2b80f77bcd4f Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Fri, 22 Mar 2024 07:25:09 -0400
Subject: [PATCH 18/20] MNT: Refactor flight prints module - F-strings as
 faster in python, let's use them! - Added a docstring to the module! -
 useless comments were removed - docstrings were updated - no code line is
 longer than 88 columns (pylint and flake8 restriction) - improve parachute
 printing

---
 CHANGELOG.md                     |   1 +
 rocketpy/prints/flight_prints.py | 369 ++++++++++++++-----------------
 2 files changed, 165 insertions(+), 205 deletions(-)

diff --git a/CHANGELOG.md b/CHANGELOG.md
index 3586d54e3..f366f5abd 100644
--- a/CHANGELOG.md
+++ b/CHANGELOG.md
@@ -37,6 +37,7 @@ and this project adheres to [Semantic Versioning](http://semver.org/).
 
 ### Changed
 
+- MNT: Refactor flight prints module [#758](https://github.com/RocketPy-Team/RocketPy/pull/578)
 - DOC: Convert CompareFlights example notebooks to .rst files [#576](https://github.com/RocketPy-Team/RocketPy/pull/576)
 - ENH: Optional argument to show the plot in Function.compare_plots [#563](https://github.com/RocketPy-Team/RocketPy/pull/563)
 
diff --git a/rocketpy/prints/flight_prints.py b/rocketpy/prints/flight_prints.py
index b9be3f6ee..4a31b5c28 100644
--- a/rocketpy/prints/flight_prints.py
+++ b/rocketpy/prints/flight_prints.py
@@ -1,3 +1,17 @@
+"""rocketpy/prints/flight_prints.py
+
+This module contains the _FlightPrints class, which is responsible for printing
+flight information in a user-friendly manner.
+
+Notes
+-----
+- This module does not have any external dependencies (avoid importing libraries).
+- We assume that all flight information is valid, no validation checks is run.
+- Avoid calculating values here, only print the values from the Flight class.
+- The _FlightPrints is a private class, it is subjected to change without notice.
+"""
+
+
 class _FlightPrints:
     """Class that holds prints methods for Flight class.
 
@@ -5,7 +19,6 @@ class _FlightPrints:
     ----------
     _FlightPrints.flight : Flight
         Flight object that will be used for the prints.
-
     """
 
     def __init__(
@@ -24,10 +37,11 @@ def __init__(
         None
         """
         self.flight = flight
-        return None
 
     def initial_conditions(self):
-        """Prints all initial conditions data available about the Flight.
+        """Prints initial conditions data available about the flight, including
+        position, velocity, attitude, euler angles, angular velocity, and
+        stability margin.
 
         Returns
         -------
@@ -67,187 +81,146 @@ def initial_conditions(self):
         print(f"Initial Stability Margin: {self.flight.initial_stability_margin:.3f} c")
 
     def numerical_integration_settings(self):
-        """Prints out the Numerical Integration settings available about the
-        flight.
+        """Prints out the numerical integration settings available about the
+        flight, this includes the maximum allowed flight time, maximum allowed
+        time step, and other settings.
 
         Returns
         -------
         None
         """
-
         print("\nNumerical Integration Settings\n")
-        print("Maximum Allowed Flight Time: {:f} s".format(self.flight.max_time))
-        print("Maximum Allowed Time Step: {:f} s".format(self.flight.max_time_step))
-        print("Minimum Allowed Time Step: {:e} s".format(self.flight.min_time_step))
-        print("Relative Error Tolerance: ", self.flight.rtol)
-        print("Absolute Error Tolerance: ", self.flight.atol)
-        print("Allow Event Overshoot: ", self.flight.time_overshoot)
-        print("Terminate Simulation on Apogee: ", self.flight.terminate_on_apogee)
-        print("Number of Time Steps Used: ", len(self.flight.time_steps))
+        print(f"Maximum Allowed Flight Time: {self.flight.max_time:.2f} s")
+        print(f"Maximum Allowed Time Step: {self.flight.max_time_step:.2f} s")
+        print(f"Minimum Allowed Time Step: {self.flight.min_time_step:.2e} s")
+        print(f"Relative Error Tolerance: {self.flight.rtol}")
+        print(f"Absolute Error Tolerance: {self.flight.atol}")
+        print(f"Allow Event Overshoot: {self.flight.time_overshoot}")
+        print(f"Terminate Simulation on Apogee: {self.flight.terminate_on_apogee}")
+        print(f"Number of Time Steps Used: {len(self.flight.time_steps)}")
         print(
-            "Number of Derivative Functions Evaluation: ",
-            sum(self.flight.function_evaluations_per_time_step),
+            "Number of Derivative Functions Evaluation: "
+            f"{sum(self.flight.function_evaluations_per_time_step)}"
         )
+        avg_func_evals_per_step = sum(
+            self.flight.function_evaluations_per_time_step
+        ) / len(self.flight.time_steps)
         print(
-            "Average Function Evaluations per Time Step: {:3f}".format(
-                sum(self.flight.function_evaluations_per_time_step)
-                / len(self.flight.time_steps)
-            )
+            f"Average Function Evaluations per Time Step: {avg_func_evals_per_step:.3f}"
         )
 
-        return None
-
     def surface_wind_conditions(self):
-        """Prints out the Surface Wind Conditions available about the flight.
+        """Prints out the Surface Wind Conditions for the flight.
 
         Returns
         -------
         None
         """
-        if self.flight.post_processed is False:
-            self.flight.post_process()
         print("\nSurface Wind Conditions\n")
-        print(
-            "Frontal Surface Wind Speed: {:.2f} m/s".format(
-                self.flight.frontal_surface_wind
-            )
-        )
-        print(
-            "Lateral Surface Wind Speed: {:.2f} m/s".format(
-                self.flight.lateral_surface_wind
-            )
-        )
-
-        return None
+        print(f"Frontal Surface Wind Speed: {self.flight.frontal_surface_wind:.2f} m/s")
+        print(f"Lateral Surface Wind Speed: {self.flight.lateral_surface_wind:.2f} m/s")
 
     def launch_rail_conditions(self):
-        """Prints out the Launch Rail Conditions available about the flight.
+        """Prints out the Launch Rail Conditions available about the flight,
+        including the length, inclination, and heading of the launch rail.
 
         Returns
         -------
         None
         """
-
         print("\nLaunch Rail\n")
-        print("Launch Rail Length:", self.flight.rail_length, " m")
-        print("Launch Rail Inclination: {:.2f}°".format(self.flight.inclination))
-        print("Launch Rail Heading: {:.2f}°".format(self.flight.heading))
-        return None
+        print(f"Launch Rail Length: {self.flight.rail_length} m")
+        print(f"Launch Rail Inclination: {self.flight.inclination:.2f}°")
+        print(f"Launch Rail Heading: {self.flight.heading:.2f}°")
 
     def out_of_rail_conditions(self):
-        """Prints out the Out of Rail Conditions available about the flight.
+        """Prints out the Out of Rail Conditions available about the flight,
+        including the time, velocity, stability margin, angle of attack, thrust
+        to weight ratio, and Reynolds number.
 
         Returns
         -------
         None
         """
-        if self.flight.post_processed is False:
-            self.flight.post_process()
         print("\nRail Departure State\n")
-        print("Rail Departure Time: {:.3f} s".format(self.flight.out_of_rail_time))
+        print(f"Rail Departure Time: {self.flight.out_of_rail_time:.3f} s")
+        print(f"Rail Departure Velocity: {self.flight.out_of_rail_velocity:.3f} m/s")
         print(
             "Rail Departure Stability Margin: "
             f"{self.flight.out_of_rail_stability_margin:.3f} c"
         )
         print(
-            "Rail Departure Stability Margin: {:.3f} c".format(
-                self.flight.stability_margin(self.flight.out_of_rail_time)
-            )
-        )
-        print(
-            "Rail Departure Angle of Attack: {:.3f}°".format(
-                self.flight.angle_of_attack(self.flight.out_of_rail_time)
-            )
+            "Rail Departure Angle of Attack: "
+            f"{self.flight.angle_of_attack(self.flight.out_of_rail_time):.3f}°"
         )
         print(
-            "Rail Departure Thrust-Weight Ratio: {:.3f}".format(
-                self.flight.rocket.thrust_to_weight(self.flight.out_of_rail_time)
-            )
+            "Rail Departure Thrust-Weight Ratio: "
+            f"{self.flight.rocket.thrust_to_weight(self.flight.out_of_rail_time):.3f}"
         )
         print(
-            "Rail Departure Reynolds Number: {:.3e}".format(
-                self.flight.reynolds_number(self.flight.out_of_rail_time)
-            )
+            "Rail Departure Reynolds Number: "
+            f"{self.flight.reynolds_number(self.flight.out_of_rail_time):.3e}"
         )
 
-        return None
-
     def burn_out_conditions(self):
-        """Prints out the Burn Out Conditions available about the flight.
+        """Prints out the Burn Out Conditions available about the flight,
+        including the burn out time, altitude, speed, freestream speed, Mach
+        number, and kinetic energy.
 
         Returns
         -------
         None
         """
         print("\nBurn out State\n")
-        print("Burn out time: {:.3f} s".format(self.flight.rocket.motor.burn_out_time))
+        print(f"Burn out time: {self.flight.rocket.motor.burn_out_time:.3f} s")
         print(
-            "Altitude at burn out: {:.3f} m (AGL)".format(
-                self.flight.z(self.flight.rocket.motor.burn_out_time)
-                - self.flight.env.elevation
-            )
+            "Altitude at burn out: "
+            f"{self.flight.altitude(self.flight.rocket.motor.burn_out_time):.3f} "
+            "m (AGL)"
         )
         print(
-            "Rocket velocity at burn out: {:.3f} m/s".format(
-                self.flight.speed(self.flight.rocket.motor.burn_out_time)
-            )
+            "Rocket speed at burn out: "
+            f"{self.flight.speed(self.flight.rocket.motor.burn_out_time):.3f} m/s"
         )
-        print(
-            "Freestream velocity at burn out: {:.3f} m/s".format(
-                (
-                    self.flight.stream_velocity_x(
-                        self.flight.rocket.motor.burn_out_time
-                    )
-                    ** 2
-                    + self.flight.stream_velocity_y(
-                        self.flight.rocket.motor.burn_out_time
-                    )
-                    ** 2
-                    + self.flight.stream_velocity_z(
-                        self.flight.rocket.motor.burn_out_time
-                    )
-                    ** 2
-                )
-                ** 0.5
-            )
+
+        stream_velocity = self.flight.free_stream_speed(
+            self.flight.rocket.motor.burn_out_time
         )
+        print(f"Freestream velocity at burn out: {stream_velocity:.3f} m/s")
+
         print(
-            "Mach Number at burn out: {:.3f}".format(
-                self.flight.mach_number(self.flight.rocket.motor.burn_out_time)
-            )
+            "Mach Number at burn out: "
+            f"{self.flight.mach_number(self.flight.rocket.motor.burn_out_time):.3f}"
         )
         print(
-            "Kinetic energy at burn out: {:.3e} J".format(
-                self.flight.kinetic_energy(self.flight.rocket.motor.burn_out_time)
-            )
+            "Kinetic energy at burn out: "
+            f"{self.flight.kinetic_energy(self.flight.rocket.motor.burn_out_time):.3e} "
+            "J"
         )
 
-        return None
-
     def apogee_conditions(self):
-        """Prints out the Apogee Conditions available about the flight.
+        """Prints out the Apogee Conditions available about the flight,
+        including the apogee time, altitude, freestream speed, latitude, and
+        longitude.
 
         Returns
         -------
         None
         """
-        if self.flight.post_processed is False:
-            self.flight.post_process()
         print("\nApogee State\n")
+        print(f"Apogee Time: {self.flight.apogee_time:.3f} s")
         print(
-            "Apogee Altitude: {:.3f} m (ASL) | {:.3f} m (AGL)".format(
-                self.flight.apogee, self.flight.apogee - self.flight.env.elevation
-            )
+            f"Apogee Altitude: {self.flight.apogee:.3f} m (ASL) | "
+            f"{self.flight.altitude(self.flight.apogee_time):.3f} m (AGL)"
         )
-        print("Apogee Time: {:.3f} s".format(self.flight.apogee_time))
+        print(f"Apogee Freestream Speed: {self.flight.apogee_freestream_speed:.3f} m/s")
+        print(f"Apogee X position: {self.flight.x(self.flight.apogee_time):.3f} m")
+        print(f"Apogee Y position: {self.flight.y(self.flight.apogee_time):.3f} m")
+        print(f"Apogee latitude: {self.flight.latitude(self.flight.apogee_time):.7f}°")
         print(
-            "Apogee Freestream Speed: {:.3f} m/s".format(
-                self.flight.apogee_freestream_speed
-            )
+            f"Apogee longitude: {self.flight.longitude(self.flight.apogee_time):.7f}°"
         )
 
-        return None
-
     def events_registered(self):
         """Prints out the Events Registered available about the flight.
 
@@ -255,8 +228,6 @@ def events_registered(self):
         -------
         None
         """
-        if self.flight.post_processed is False:
-            self.flight.post_process()
         print("\nParachute Events\n")
         if len(self.flight.parachute_events) == 0:
             print("No Parachute Events Were Triggered.")
@@ -264,24 +235,17 @@ def events_registered(self):
             trigger_time = event[0]
             parachute = event[1]
             open_time = trigger_time + parachute.lag
-            velocity = self.flight.free_stream_speed(open_time)
+            speed = self.flight.free_stream_speed(open_time)
             altitude = self.flight.z(open_time)
             name = parachute.name.title()
-            print(name + " Ejection Triggered at: {:.3f} s".format(trigger_time))
-            print(name + " Parachute Inflated at: {:.3f} s".format(open_time))
-            print(
-                name
-                + " Parachute Inflated with Freestream Speed of: {:.3f} m/s".format(
-                    velocity
-                )
-            )
+            print(f"Parachute: {name}")
+            print(f"\tEjection time: {trigger_time:.3f} s")
+            print(f"\tInflation time: {open_time:.3f} s")
+            print(f"\tFreestream speed at inflation: {speed:.3f} m/s")
             print(
-                name
-                + " Parachute Inflated at Height of: {:.3f} m (AGL)".format(
-                    altitude - self.flight.env.elevation
-                )
+                f"\tAltitude at inflation: {altitude:.3f} m (ASL) | "
+                f"{self.flight.altitude(trigger_time):.3f} m (AGL)"
             )
-        return None
 
     def impact_conditions(self):
         """Prints out the Impact Conditions available about the flight.
@@ -290,27 +254,36 @@ def impact_conditions(self):
         -------
         None
         """
-        if self.flight.post_processed is False:
-            self.flight.post_process()
         if len(self.flight.impact_state) != 0:
             print("\nImpact Conditions\n")
-            print("X Impact: {:.3f} m".format(self.flight.x_impact))
-            print("Y Impact: {:.3f} m".format(self.flight.y_impact))
-            print("Latitude: {:.7f}°".format(self.flight.latitude(self.flight.t_final)))
+            print(f"Time of impact: {self.flight.t_final:.3f} s")
+            print(f"X impact: {self.flight.x_impact:.3f} m")
+            print(f"Y impact: {self.flight.y_impact:.3f} m")
             print(
-                "Longitude: {:.7f}°".format(self.flight.longitude(self.flight.t_final))
+                f"Altitude impact: {self.flight.z(self.flight.t_final):.3f} m (ASL) | "
+                f"{self.flight.altitude(self.flight.t_final):.3f} m (AGL) "
+            )
+            print(f"Latitude: {self.flight.latitude(self.flight.t_final):.7f}°")
+            print(f"Longitude: {self.flight.longitude(self.flight.t_final):.7f}°")
+            print(f"Vertical velocity at impact: {self.flight.impact_velocity:.3f} m/s")
+            num_parachute_events = sum(
+                1
+                for event in self.flight.parachute_events
+                if event[0] < self.flight.t_final
+            )
+            print(
+                f"Number of parachutes triggered until impact: {num_parachute_events}"
             )
-            print("Time of Impact: {:.3f} s".format(self.flight.t_final))
-            print("Velocity at Impact: {:.3f} m/s".format(self.flight.impact_velocity))
         elif self.flight.terminate_on_apogee is False:
             print("End of Simulation")
-            t_final = self.flight.solution[-1][0]
-            print("Time: {:.3f} s".format(t_final))
-            print("Altitude: {:.3f} m".format(self.flight.solution[-1][3]))
-            print("Latitude: {:.3f}°".format(self.flight.latitude(t_final)))
-            print("Longitude: {:.3f}°".format(self.flight.longitude(t_final)))
-
-        return None
+            t_final = self.flight.time[-1]
+            print(f"Time: {t_final:.3f} s")
+            print(
+                f"Altitude: {self.flight.z(t_final)} m (ASL) | "
+                f"{self.flight.altitude(t_final):.3f} m (AGL)"
+            )
+            print(f"Latitude: {self.flight.latitude(t_final):.7f}°")
+            print(f"Longitude: {self.flight.longitude(t_final):.7f}°")
 
     def maximum_values(self):
         """Prints out the Maximum Values available about the flight.
@@ -321,53 +294,44 @@ def maximum_values(self):
         """
         print("\nMaximum Values\n")
         print(
-            "Maximum Speed: {:.3f} m/s at {:.2f} s".format(
-                self.flight.max_speed, self.flight.max_speed_time
-            )
+            f"Maximum Speed: {self.flight.max_speed:.3f} m/s "
+            f"at {self.flight.max_speed_time:.2f} s"
         )
         print(
-            "Maximum Mach Number: {:.3f} Mach at {:.2f} s".format(
-                self.flight.max_mach_number, self.flight.max_mach_number_time
-            )
+            f"Maximum Mach Number: {self.flight.max_mach_number:.3f} Mach "
+            f"at {self.flight.max_mach_number_time:.2f} s"
         )
         print(
-            "Maximum Reynolds Number: {:.3e} at {:.2f} s".format(
-                self.flight.max_reynolds_number, self.flight.max_reynolds_number_time
-            )
+            f"Maximum Reynolds Number: {self.flight.max_reynolds_number:.3e} "
+            f"at {self.flight.max_reynolds_number_time:.2f} s"
         )
         print(
-            "Maximum Dynamic Pressure: {:.3e} Pa at {:.2f} s".format(
-                self.flight.max_dynamic_pressure, self.flight.max_dynamic_pressure_time
-            )
+            f"Maximum Dynamic Pressure: {self.flight.max_dynamic_pressure:.3e} Pa "
+            f"at {self.flight.max_dynamic_pressure_time:.2f} s"
         )
         print(
-            "Maximum Acceleration During Motor Burn: {:.3f} m/s² at {:.2f} s".format(
-                self.flight.max_acceleration_power_on,
-                self.flight.max_acceleration_power_on_time,
-            )
+            "Maximum Acceleration During Motor Burn: "
+            f"{self.flight.max_acceleration_power_on:.3f} m/s² "
+            f"at {self.flight.max_acceleration_power_on_time:.2f} s"
         )
         print(
-            "Maximum Gs During Motor Burn: {:.3f} g at {:.2f} s".format(
-                self.flight.max_acceleration_power_on / self.flight.env.standard_g,
-                self.flight.max_acceleration_power_on_time,
-            )
+            "Maximum Gs During Motor Burn: "
+            f"{self.flight.max_acceleration_power_on / self.flight.env.standard_g:.3f} "
+            f"g at {self.flight.max_acceleration_power_on_time:.2f} s"
         )
         print(
-            "Maximum Acceleration After Motor Burn: {:.3f} m/s² at {:.2f} s".format(
-                self.flight.max_acceleration_power_off,
-                self.flight.max_acceleration_power_off_time,
-            )
+            "Maximum Acceleration After Motor Burn: "
+            f"{self.flight.max_acceleration_power_off:.3f} m/s² "
+            f"at {self.flight.max_acceleration_power_off_time:.2f} s"
         )
         print(
-            "Maximum Gs After Motor Burn: {:.3f} g at {:.2f} s".format(
-                self.flight.max_acceleration_power_off / self.flight.env.standard_g,
-                self.flight.max_acceleration_power_off_time,
-            )
+            "Maximum Gs After Motor Burn: "
+            f"{self.flight.max_acceleration_power_off / self.flight.env.standard_g:.3f}"
+            f" Gs at {self.flight.max_acceleration_power_off_time:.2f} s"
         )
         print(
-            "Maximum Stability Margin: {:.3f} c at {:.2f} s".format(
-                self.flight.max_stability_margin, self.flight.max_stability_margin_time
-            )
+            f"Maximum Stability Margin: {self.flight.max_stability_margin:.3f} c "
+            f"at {self.flight.max_stability_margin_time:.2f} s"
         )
 
         if (
@@ -377,30 +341,35 @@ def maximum_values(self):
             pass
         else:
             print(
-                "Maximum Upper Rail Button Normal Force: {:.3f} N".format(
-                    self.flight.max_rail_button1_normal_force
-                )
+                "Maximum Upper Rail Button Normal Force: "
+                f"{self.flight.max_rail_button1_normal_force:.3f} N"
             )
             print(
-                "Maximum Upper Rail Button Shear Force: {:.3f} N".format(
-                    self.flight.max_rail_button1_shear_force
-                )
+                "Maximum Upper Rail Button Shear Force: "
+                f"{self.flight.max_rail_button1_shear_force:.3f} N"
             )
             print(
-                "Maximum Lower Rail Button Normal Force: {:.3f} N".format(
-                    self.flight.max_rail_button2_normal_force
-                )
+                "Maximum Lower Rail Button Normal Force: "
+                f"{self.flight.max_rail_button2_normal_force:.3f} N"
             )
             print(
-                "Maximum Lower Rail Button Shear Force: {:.3f} N".format(
-                    self.flight.max_rail_button2_shear_force
-                )
+                "Maximum Lower Rail Button Shear Force: "
+                f"{self.flight.max_rail_button2_shear_force:.3f} N"
             )
-        return None
 
     def stability_margin(self):
-        """Prints out the maximum and minimum stability margin available
-        about the flight."""
+        """Prints out the stability margins of the flight at different times.
+
+        This method prints the following: Initial Stability Margin, Out of Rail
+        Stability Margin, Maximum Stability Margin, and Minimum Stability Margin
+
+        Each stability margin is printed along with the time it occurred.
+
+        Notes
+        -----
+        The stability margin is typically measured in calibers (c), where 1
+        caliber is the diameter of the rocket.
+        """
         print("\nStability Margin\n")
         print(
             f"Initial Stability Margin: {self.flight.initial_stability_margin:.3f} c "
@@ -412,62 +381,52 @@ def stability_margin(self):
             f"at {self.flight.out_of_rail_time:.2f} s"
         )
         print(
-            "Minimum Stability Margin: {:.3f} c at {:.2f} s".format(
-                self.flight.min_stability_margin, self.flight.min_stability_margin_time
-            )
+            f"Maximum Stability Margin: {self.flight.max_stability_margin:.3f} c "
+            f"at {self.flight.max_stability_margin_time:.2f} s"
+        )
+        print(
+            f"Minimum Stability Margin: {self.flight.min_stability_margin:.3f} c "
+            f"at {self.flight.min_stability_margin_time:.2f} s"
         )
-        return None
 
     def all(self):
-        """Prints out all data available about the Flight.
+        """Prints out all data available about the Flight. This method invokes
+        all other print methods in the class.
 
         Returns
         -------
         None
         """
 
-        # Print initial conditions
         self.initial_conditions()
         print()
 
-        # Print surface wind conditions
         self.surface_wind_conditions()
         print()
 
-        # Print launch rail orientation
         self.launch_rail_conditions()
         print()
 
-        # Print out of rail conditions
         self.out_of_rail_conditions()
         print()
 
-        # Print burn out conditions
         self.burn_out_conditions()
         print()
 
-        # Print apogee conditions
         self.apogee_conditions()
         print()
 
-        # Print events registered
         self.events_registered()
         print()
 
-        # Print impact conditions
         self.impact_conditions()
         print()
 
-        # Print stability margin
         self.stability_margin()
         print()
 
-        # Print maximum values
         self.maximum_values()
         print()
 
-        # Print Numerical Integration Information
         self.numerical_integration_settings()
         print()
-
-        return None

From ad189a8a16c4e7f7f2039105e1e6630d226ed12e Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Sat, 23 Mar 2024 22:26:15 -0400
Subject: [PATCH 19/20] MNT: fix number in CHANGELOG

---
 CHANGELOG.md | 2 +-
 1 file changed, 1 insertion(+), 1 deletion(-)

diff --git a/CHANGELOG.md b/CHANGELOG.md
index f366f5abd..a0d80e57c 100644
--- a/CHANGELOG.md
+++ b/CHANGELOG.md
@@ -37,7 +37,7 @@ and this project adheres to [Semantic Versioning](http://semver.org/).
 
 ### Changed
 
-- MNT: Refactor flight prints module [#758](https://github.com/RocketPy-Team/RocketPy/pull/578)
+- MNT: Refactor flight prints module [#579](https://github.com/RocketPy-Team/RocketPy/pull/579)
 - DOC: Convert CompareFlights example notebooks to .rst files [#576](https://github.com/RocketPy-Team/RocketPy/pull/576)
 - ENH: Optional argument to show the plot in Function.compare_plots [#563](https://github.com/RocketPy-Team/RocketPy/pull/563)
 

From 2a85ce8a40584d7a8f5cd95da12d3fed15fbc64f Mon Sep 17 00:00:00 2001
From: Gui-FernandesBR <guilherme_fernandes@usp.br>
Date: Sat, 23 Mar 2024 22:26:56 -0400
Subject: [PATCH 20/20] ENH: add altitude ASL and AGL to burn out state prints

---
 rocketpy/prints/flight_prints.py | 1 +
 1 file changed, 1 insertion(+)

diff --git a/rocketpy/prints/flight_prints.py b/rocketpy/prints/flight_prints.py
index 4a31b5c28..06db442f8 100644
--- a/rocketpy/prints/flight_prints.py
+++ b/rocketpy/prints/flight_prints.py
@@ -175,6 +175,7 @@ def burn_out_conditions(self):
         print(f"Burn out time: {self.flight.rocket.motor.burn_out_time:.3f} s")
         print(
             "Altitude at burn out: "
+            f"{self.flight.z(self.flight.rocket.motor.burn_out_time):.3f} m (ASL) | "
             f"{self.flight.altitude(self.flight.rocket.motor.burn_out_time):.3f} "
             "m (AGL)"
         )