MNT: fix deprecations and warnings

CHANGELOG.md

@@ -37,6 +37,8 @@ Attention: The newest changes should be on top -->
 
 - ENH: _MotorPrints inheritance - issue #460 [#828](https://github.com/RocketPy-Team/RocketPy/pull/828)
 
+- MNT: fix deprecations and warnings [#829](https://github.com/RocketPy-Team/RocketPy/pull/829)
+
 ### Fixed
 
 
@@ -45,7 +47,7 @@ Attention: The newest changes should be on top -->
 ### Added
 - ENH: Support for ND arithmetic in Function class. [#810] (https://github.com/RocketPy-Team/RocketPy/pull/810)
 - ENH: allow users to provide custom samplers [#803](https://github.com/RocketPy-Team/RocketPy/pull/803)
-- ENH: Implement Multivariate Rejection Sampling (MRS) [#738] (https://github.com/RocketPy-Team/RocketPy/pull/738) 
+- ENH: Implement Multivariate Rejection Sampling (MRS) [#738] (https://github.com/RocketPy-Team/RocketPy/pull/738)
 - ENH: Create a rocketpy file to store flight simulations [#800](https://github.com/RocketPy-Team/RocketPy/pull/800)
 - ENH: Support for the RSE file format has been added to the library [#798](https://github.com/RocketPy-Team/RocketPy/pull/798)
 - ENH: Introduce Net Thrust with pressure corrections [#789](https://github.com/RocketPy-Team/RocketPy/pull/789)

requirements.txt

@@ -1,6 +1,6 @@
 numpy>=1.13
 scipy>=1.0
-matplotlib>=3.0
+matplotlib>=3.9.0  # Released May 15th 2024
 netCDF4>=1.6.4
 requests
 pytz

rocketpy/environment/environment.py

@@ -27,15 +27,14 @@
     find_latitude_index,
     find_longitude_index,
     find_time_index,
+    geodesic_to_utm,
     get_elevation_data_from_dataset,
     get_final_date_from_time_array,
     get_initial_date_from_time_array,
     get_interval_date_from_time_array,
     get_pressure_levels_from_file,
     mask_and_clean_dataset,
 )
-from rocketpy.environment.tools import geodesic_to_utm as geodesic_to_utm_tools
-from rocketpy.environment.tools import utm_to_geodesic as utm_to_geodesic_tools
 from rocketpy.environment.weather_model_mapping import WeatherModelMapping
 from rocketpy.mathutils.function import NUMERICAL_TYPES, Function, funcify_method
 from rocketpy.plots.environment_plots import _EnvironmentPlots
@@ -451,7 +450,7 @@ def __initialize_utm_coordinates(self):
                 self.initial_utm_letter,
                 self.initial_hemisphere,
                 self.initial_ew,
-            ) = self.geodesic_to_utm(
+            ) = geodesic_to_utm(
                 lat=self.latitude,
                 lon=self.longitude,
                 flattening=self.ellipsoid.flattening,
@@ -2523,98 +2522,7 @@ def set_earth_geometry(self, datum):
                 f"the following recognized datum: {available_datums}"
             ) from e
 
-    # Auxiliary functions - Geodesic Coordinates
-
-    @staticmethod
-    def geodesic_to_utm(
-        lat, lon, semi_major_axis=6378137.0, flattening=1 / 298.257223563
-    ):
-        """Function which converts geodetic coordinates, i.e. lat/lon, to UTM
-        projection coordinates. Can be used only for latitudes between -80.00°
-        and 84.00°
-
-        Parameters
-        ----------
-        lat : float
-            The latitude coordinates of the point of analysis, must be contained
-            between -80.00° and 84.00°
-        lon : float
-            The longitude coordinates of the point of analysis, must be
-            contained between -180.00° and 180.00°
-        semi_major_axis : float
-            The semi-major axis of the ellipsoid used to represent the Earth,
-            must be given in meters (default is 6,378,137.0 m, which corresponds
-            to the WGS84 ellipsoid)
-        flattening : float
-            The flattening of the ellipsoid used to represent the Earth, usually
-            between 1/250 and 1/150 (default is 1/298.257223563, which
-            corresponds to the WGS84 ellipsoid)
-
-        Returns
-        -------
-        x : float
-            East coordinate, always positive
-        y : float
-            North coordinate, always positive
-        utm_zone : int
-            The number of the UTM zone of the point of analysis, can vary
-            between 1 and 60
-        utm_letter : string
-            The letter of the UTM zone of the point of analysis, can vary
-            between C and X, omitting the letters "I" and "O"
-        hemis : string
-            Returns "S" for southern hemisphere and "N" for Northern hemisphere
-        EW : string
-            Returns "W" for western hemisphere and "E" for eastern hemisphere
-        """
-        warnings.warn(
-            "This function is deprecated and will be removed in v1.10.0. "
-            "Please use the new method `tools.geodesic_to_utm` instead.",
-            DeprecationWarning,
-        )
-        return geodesic_to_utm_tools(lat, lon, semi_major_axis, flattening)
-
-    @staticmethod
-    def utm_to_geodesic(
-        x, y, utm_zone, hemis, semi_major_axis=6378137.0, flattening=1 / 298.257223563
-    ):
-        """Function to convert UTM coordinates to geodesic coordinates
-        (i.e. latitude and longitude).
-
-        Parameters
-        ----------
-        x : float
-            East UTM coordinate in meters
-        y : float
-            North UTM coordinate in meters
-        utm_zone : int
-            The number of the UTM zone of the point of analysis, can vary
-            between 1 and 60
-        hemis : string
-            Equals to "S" for southern hemisphere and "N" for Northern
-            hemisphere
-        semi_major_axis : float
-            The semi-major axis of the ellipsoid used to represent the Earth,
-            must be given in meters (default is 6,378,137.0 m, which corresponds
-            to the WGS84 ellipsoid)
-        flattening : float
-            The flattening of the ellipsoid used to represent the Earth, usually
-            between 1/250 and 1/150 (default is 1/298.257223563, which
-            corresponds to the WGS84 ellipsoid)
-
-        Returns
-        -------
-        lat : float
-            latitude of the analyzed point
-        lon : float
-            latitude of the analyzed point
-        """
-        warnings.warn(
-            "This function is deprecated and will be removed in v1.10.0. "
-            "Please use the new method `tools.utm_to_geodesic` instead.",
-            DeprecationWarning,
-        )
-        return utm_to_geodesic_tools(x, y, utm_zone, hemis, semi_major_axis, flattening)
+    # Auxiliary functions
 
     @staticmethod
     def calculate_earth_radius(

rocketpy/motors/motor.py

@@ -1151,7 +1151,7 @@ def vacuum_thrust(self):
         Returns
         -------
         vacuum_thrust : Function
-            The rocket's thrust in a vaccum.
+            The rocket's thrust in a vacuum.
         """
         if self.reference_pressure is None:
             warnings.warn(

rocketpy/plots/monte_carlo_plots.py

@@ -183,6 +183,7 @@ def all(self, keys=None):
             ax2 = fig.add_subplot(gs[1])
 
             # Plot boxplot
+            # TODO: changes vert to orientation="horizontal" when support for Py3.9 ends
             ax1.boxplot(self.monte_carlo.results[key], vert=False)
             ax1.set_title(f"Box Plot of {key}")
             ax1.set_yticks([])

rocketpy/rocket/aero_surface/air_brakes.py

@@ -131,7 +131,8 @@ def deployment_level(self, value):
                 warnings.warn(
                     f"Deployment level of {self.name} is smaller than 0 or "
                     + "larger than 1. Extrapolation for the drag coefficient "
-                    + "curve will be used."
+                    + "curve will be used.",
+                    UserWarning,
                 )
         self._deployment_level = value
 

rocketpy/simulation/flight.py

@@ -155,8 +155,6 @@ class Flight:
         Current integration time.
     Flight.y : list
         Current integration state vector u.
-    Flight.post_processed : bool
-        Defines if solution data has been post processed.
     Flight.initial_solution : list
         List defines initial condition - [tInit, x_init,
         y_init, z_init, vx_init, vy_init, vz_init, e0_init, e1_init,
@@ -1102,7 +1100,6 @@ def __init_solution_monitors(self):
         self.impact_velocity = 0
         self.impact_state = np.array([0])
         self.parachute_events = []
-        self.post_processed = False
         self.__post_processed_variables = []
 
     def __init_flight_state(self):
@@ -3055,14 +3052,16 @@ def __calculate_rail_button_forces(self):  # TODO: complex method.
         null_force = Function(0)
         if self.out_of_rail_time_index == 0:  # No rail phase, no rail button forces
             warnings.warn(
-                "Trying to calculate rail button forces without a rail phase defined."
-                + "The rail button forces will be set to zero."
+                "Trying to calculate rail button forces without a rail phase defined. "
+                + "The rail button forces will be set to zero.",
+                UserWarning,
             )
             return null_force, null_force, null_force, null_force
         if len(self.rocket.rail_buttons) == 0:
             warnings.warn(
-                "Trying to calculate rail button forces without rail buttons defined."
-                + "The rail button forces will be set to zero."
+                "Trying to calculate rail button forces without rail buttons defined. "
+                + "The rail button forces will be set to zero.",
+                UserWarning,
             )
             return null_force, null_force, null_force, null_force
 
@@ -3174,28 +3173,6 @@ def __evaluate_post_process(self):
 
         return np.array(self.__post_processed_variables)
 
-    def post_process(self, interpolation="spline", extrapolation="natural"):
-        """This method is **deprecated** and is only kept here for backwards
-        compatibility. All attributes that need to be post processed are
-        computed just in time.
-
-        Post-process all Flight information produced during
-        simulation. Includes the calculation of maximum values,
-        calculation of secondary values such as energy and conversion
-        of lists to Function objects to facilitate plotting.
-
-        Returns
-        -------
-        None
-        """
-        # pylint: disable=unused-argument
-        warnings.warn(
-            "The method post_process is deprecated and will be removed in v1.10. "
-            "All attributes that need to be post processed are computed just in time.",
-            DeprecationWarning,
-        )
-        self.post_processed = True
-
     def calculate_stall_wind_velocity(self, stall_angle):  # TODO: move to utilities
         """Function to calculate the maximum wind velocity before the angle of
         attack exceeds a desired angle, at the instant of departing rail launch.

rocketpy/utilities.py

@@ -1,8 +1,6 @@
-import ast
 import inspect
 import json
 import os
-import traceback
 import warnings
 from datetime import date
 from importlib.metadata import version
@@ -444,96 +442,6 @@ def _flutter_prints(
     print(f"Altitude of minimum Safety Factor: {altitude_min_sf:.3f} m (AGL)\n")
 
 
-def create_dispersion_dictionary(filename):  # pragma: no cover
-    """Creates a dictionary with the rocket data provided by a .csv file.
-    File should be organized in four columns: attribute_class, parameter_name,
-    mean_value, standard_deviation. The first row should be the header.
-    It is advised to use ";" as separator, but "," should work on most of cases.
-    The "," separator might cause problems if the data set contains lists where
-    the items are separated by commas.
-
-    Parameters
-    ----------
-    filename : string
-        String with the path to the .csv file. The file should follow the
-        following structure:
-
-        .. code-block::
-
-            attribute_class; parameter_name; mean_value; standard_deviation;
-
-            environment; ensemble_member; [0, 1, 2, 3, 4, 5, 6, 7, 8, 9];;
-
-            motor; impulse; 1415.15; 35.3;
-
-            motor; burn_time; 5.274; 1;
-
-            motor; nozzle_radius; 0.021642; 0.0005;
-
-            motor; throat_radius; 0.008; 0.0005;
-
-            motor; grain_separation; 0.006; 0.001;
-
-            motor; grain_density; 1707; 50;
-
-    Returns
-    -------
-    dictionary
-        Dictionary with all rocket data to be used in dispersion analysis. The
-        dictionary will follow the following structure:
-
-        .. code-block:: python
-
-            analysis_parameters = {
-                'environment': {
-                    'ensemble_member': [0, 1, 2, 3, 4, 5, 6, 7, 8, 9]
-                },
-                'motor': {
-                    'impulse': (1415.15, 35.3),
-                    'burn_time': (5.274, 1),
-                    'nozzle_radius': (0.021642, 0.0005),
-                    'throat_radius': (0.008, 0.0005),
-                    'grain_separation': (0.006, 0.001),
-                    'grain_density': (1707, 50),
-                    }
-            }
-    """
-    warnings.warn(
-        "This function is deprecated and will be removed in v1.10.0.",
-        DeprecationWarning,
-    )
-    try:
-        file = np.genfromtxt(
-            filename, usecols=(1, 2, 3), skip_header=1, delimiter=";", dtype=str
-        )
-    except ValueError:
-        warnings.warn(
-            "Error caught: the recommended delimiter is ';'. If using ',' "
-            "instead, be aware that some resources might not work as "
-            "expected if your data set contains lists where the items are "
-            "separated by commas. Please consider changing the delimiter to "
-            "';' if that is the case."
-        )
-        warnings.warn(traceback.format_exc())
-        file = np.genfromtxt(
-            filename, usecols=(1, 2, 3), skip_header=1, delimiter=",", dtype=str
-        )
-    analysis_parameters = {}
-    for row in file:
-        if row[0] != "":
-            if row[2] == "":
-                try:
-                    analysis_parameters[row[0].strip()] = float(row[1])
-                except ValueError:
-                    analysis_parameters[row[0].strip()] = ast.literal_eval(row[1])
-            else:
-                try:
-                    analysis_parameters[row[0].strip()] = (float(row[1]), float(row[2]))
-                except ValueError:
-                    analysis_parameters[row[0].strip()] = ""
-    return analysis_parameters
-
-
 def apogee_by_mass(flight, min_mass, max_mass, points=10, plot=True):
     """Returns a Function object that estimates the apogee of a rocket given
     its mass (no motor). The function will use the rocket's mass as the

tests/acceptance/test_bella_lui_rocket.py

@@ -182,7 +182,6 @@ def drogue_trigger(p, h, y):
         inclination=parameters.get("inclination")[0],
         heading=parameters.get("heading")[0],
     )
-    test_flight.post_process()
 
     # Comparison with Real Data
     flight_data = np.loadtxt(

tests/unit/test_environment.py

@@ -6,6 +6,7 @@
 import pytz
 
 from rocketpy import Environment
+from rocketpy.environment.tools import geodesic_to_utm, utm_to_geodesic
 
 
 @pytest.mark.parametrize(
@@ -78,7 +79,7 @@ def test_geodesic_coordinate_geodesic_to_utm_converts_coordinate():
         utm_letter,
         north_south_hemis,
         east_west_hemis,
-    ) = Environment.geodesic_to_utm(
+    ) = geodesic_to_utm(
         lat=32.990254,
         lon=-106.974998,
         semi_major_axis=6378137.0,  # WGS84
@@ -98,7 +99,7 @@ class and checks the conversion results from UTM to geodesic
     coordinates.
     """
 
-    lat, lon = Environment.utm_to_geodesic(
+    lat, lon = utm_to_geodesic(
         x=315468.64,
         y=3651938.65,
         utm_zone=13,