MNT: black

rocketpy/environment/environment.py

@@ -362,7 +362,7 @@ def __init__(
 
     def __initialize_constants(self):
         """Sets some important constants and atmospheric variables."""
-        self.earth_radius = 6.3781 * (10 ** 6)
+        self.earth_radius = 6.3781 * (10**6)
         self.air_gas_constant = 287.05287  # in J/K/kg
         self.standard_g = 9.80665
         self.__weather_model_map = WeatherModelMapping()
@@ -563,7 +563,7 @@ def __reset_barometric_height_function(self):
 
     def __reset_wind_speed_function(self):
         # NOTE: assume wind_velocity_x and wind_velocity_y as Function objects
-        self.wind_speed = (self.wind_velocity_x ** 2 + self.wind_velocity_y ** 2) ** 0.5
+        self.wind_speed = (self.wind_velocity_x**2 + self.wind_velocity_y**2) ** 0.5
         self.wind_speed.set_inputs("Height Above Sea Level (m)")
         self.wind_speed.set_outputs("Wind Speed (m/s)")
         self.wind_speed.set_title("Wind Speed Profile")
@@ -850,7 +850,7 @@ def somigliana_gravity(self, height):
         height_correction = (
             1
             - height * 2 / a * (1 + f + m_rot - 2 * f * sin_lat_sqrd)
-            + 3 * height ** 2 / a ** 2
+            + 3 * height**2 / a**2
         )
 
         return height_correction * gravity_somgl
@@ -2802,8 +2802,8 @@ def calculate_earth_radius(
         # Calculate the Earth Radius in meters
         e_radius = np.sqrt(
             (
-                (np.cos(lat) * (semi_major_axis ** 2)) ** 2
-                + (np.sin(lat) * (semi_minor_axis ** 2)) ** 2
+                (np.cos(lat) * (semi_major_axis**2)) ** 2
+                + (np.sin(lat) * (semi_minor_axis**2)) ** 2
             )
             / (
                 (np.cos(lat) * semi_major_axis) ** 2

rocketpy/environment/environment_analysis.py

@@ -891,10 +891,10 @@ def __parse_surface_data(self):  # pylint: disable=too-many-statements
             # Extract data from weather file
             indices = (time_index, lon_index, lat_index)
             for key, value in surface_file_dict.items():
-                dictionary[date_string][hour_string][
-                    key
-                ] = self.__extract_surface_data_value(
-                    surface_data, value, indices, lon_array, lat_array
+                dictionary[date_string][hour_string][key] = (
+                    self.__extract_surface_data_value(
+                        surface_data, value, indices, lon_array, lat_array
+                    )
                 )
 
         # Get elevation, time index does not matter, use last one
@@ -2040,7 +2040,7 @@ def __process_surface_wind_data(self):
                     vy = self.converted_surface_data[day][str(hour)][
                         "surface10m_wind_velocity_y"
                     ]
-                    wind_speed[hour][index] = (vx ** 2 + vy ** 2) ** 0.5
+                    wind_speed[hour][index] = (vx**2 + vy**2) ** 0.5
 
                     # Wind direction means where the wind is blowing from, 180 deg opposite from wind heading
                     direction = (180 + (np.arctan2(vy, vx) * 180 / np.pi)) % 360

rocketpy/environment/fetchers.py

@@ -135,7 +135,7 @@ def fetch_gfs_file_return_dataset(max_attempts=10, base_delay=2):
             return dataset
         except OSError:
             attempt_count += 1
-            time.sleep(base_delay ** attempt_count)
+            time.sleep(base_delay**attempt_count)
 
     if dataset is None:
         raise RuntimeError(
@@ -182,7 +182,7 @@ def fetch_nam_file_return_dataset(max_attempts=10, base_delay=2):
             return dataset
         except OSError:
             attempt_count += 1
-            time.sleep(base_delay ** attempt_count)
+            time.sleep(base_delay**attempt_count)
 
     if dataset is None:
         raise RuntimeError("Unable to load latest weather data for NAM through " + file)
@@ -227,7 +227,7 @@ def fetch_rap_file_return_dataset(max_attempts=10, base_delay=2):
             return dataset
         except OSError:
             attempt_count += 1
-            time.sleep(base_delay ** attempt_count)
+            time.sleep(base_delay**attempt_count)
 
     if dataset is None:
         raise RuntimeError("Unable to load latest weather data for RAP through " + file)
@@ -281,7 +281,7 @@ def fetch_hiresw_file_return_dataset(max_attempts=10, base_delay=2):
             return dataset
         except OSError:
             attempt_count += 1
-            time.sleep(base_delay ** attempt_count)
+            time.sleep(base_delay**attempt_count)
 
     if dataset is None:
         raise RuntimeError(
@@ -385,7 +385,7 @@ def fetch_gefs_ensemble():
             return dataset
         except OSError:
             attempt_count += 1
-            time.sleep(2 ** attempt_count)
+            time.sleep(2**attempt_count)
     if not success:
         raise RuntimeError(
             "Unable to load latest weather data for GEFS through " + file
@@ -427,6 +427,6 @@ def fetch_cmc_ensemble():
             return dataset
         except OSError:
             attempt_count += 1
-            time.sleep(2 ** attempt_count)
+            time.sleep(2**attempt_count)
     if not success:
         raise RuntimeError("Unable to load latest weather data for CMC through " + file)

rocketpy/environment/tools.py

@@ -106,7 +106,7 @@ def calculate_wind_speed(u, v, w=0.0):
     >>> calculate_wind_speed(3, 4, 0)
     np.float64(5.0)
     """
-    return np.sqrt(u ** 2 + v ** 2 + w ** 2)
+    return np.sqrt(u**2 + v**2 + w**2)
 
 
 ## These functions are meant to be used with netcdf4 datasets
@@ -482,7 +482,7 @@ def geodesic_to_utm(
 
     # Evaluate reference parameters
     K0 = 1 - 1 / 2500
-    e2 = 2 * flattening - flattening ** 2
+    e2 = 2 * flattening - flattening**2
     e2lin = e2 / (1 - e2)
 
     # Evaluate auxiliary parameters
@@ -505,9 +505,9 @@ def geodesic_to_utm(
 
     # Evaluate new auxiliary parameters
     J = (1 - t + c) * ag * ag * ag / 6
-    K = (5 - 18 * t + t * t + 72 * c - 58 * e2lin) * (ag ** 5) / 120
+    K = (5 - 18 * t + t * t + 72 * c - 58 * e2lin) * (ag**5) / 120
     L = (5 - t + 9 * c + 4 * c * c) * ag * ag * ag * ag / 24
-    M = (61 - 58 * t + t * t + 600 * c - 330 * e2lin) * (ag ** 6) / 720
+    M = (61 - 58 * t + t * t + 600 * c - 330 * e2lin) * (ag**6) / 720
 
     # Evaluate the final coordinates
     x = 500000 + K0 * n * (ag + J + K)
@@ -542,7 +542,7 @@ def utm_to_geodesic(  # pylint: disable=too-many-locals,too-many-statements
 
     # Calculate reference values
     K0 = 1 - 1 / 2500
-    e2 = 2 * flattening - flattening ** 2
+    e2 = 2 * flattening - flattening**2
     e2lin = e2 / (1 - e2)
     e1 = (1 - (1 - e2) ** 0.5) / (1 + (1 - e2) ** 0.5)
 
@@ -566,18 +566,18 @@ def utm_to_geodesic(  # pylint: disable=too-many-locals,too-many-statements
     t1 = np.tan(lat1) ** 2
     n1 = semi_major_axis / ((1 - e2 * (np.sin(lat1) ** 2)) ** 0.5)
     quoc = (1 - e2 * np.sin(lat1) * np.sin(lat1)) ** 3
-    r1 = semi_major_axis * (1 - e2) / (quoc ** 0.5)
+    r1 = semi_major_axis * (1 - e2) / (quoc**0.5)
     d = (x - 500000) / (n1 * K0)
 
     # Calculate other auxiliary values
     aux_i = (5 + 3 * t1 + 10 * c1 - 4 * c1 * c1 - 9 * e2lin) * d * d * d * d / 24
     J = (
         (61 + 90 * t1 + 298 * c1 + 45 * t1 * t1 - 252 * e2lin - 3 * c1 * c1)
-        * (d ** 6)
+        * (d**6)
         / 720
     )
     K = d - (1 + 2 * t1 + c1) * d * d * d / 6
-    L = (5 - 2 * c1 + 28 * t1 - 3 * c1 * c1 + 8 * e2lin + 24 * t1 * t1) * (d ** 5) / 120
+    L = (5 - 2 * c1 + 28 * t1 - 3 * c1 * c1 + 8 * e2lin + 24 * t1 * t1) * (d**5) / 120
 
     # Finally calculate the coordinates in lat/lot
     lat = lat1 - (n1 * np.tan(lat1) / r1) * (d * d / 2 - aux_i + J)

rocketpy/mathutils/vector_matrix.py

@@ -182,7 +182,7 @@ def cross_matrix(self):
 
     def __abs__(self):
         """R3 vector norm, magnitude or absolute value."""
-        return (self.x ** 2 + self.y ** 2 + self.z ** 2) ** 0.5
+        return (self.x**2 + self.y**2 + self.z**2) ** 0.5
 
     def __neg__(self):
         """-1 times R3 vector self."""
@@ -1033,9 +1033,9 @@ def transformation(quaternion):
         q_w, q_x, q_y, q_z = normalize_quaternions(quaternion)
 
         # pre-compute common terms
-        q_x2 = q_x ** 2
-        q_y2 = q_y ** 2
-        q_z2 = q_z ** 2
+        q_x2 = q_x**2
+        q_y2 = q_y**2
+        q_z2 = q_z**2
         q_wx = q_w * q_x
         q_wy = q_w * q_y
         q_wz = q_w * q_z

rocketpy/motors/motor.py

@@ -1287,7 +1287,7 @@ def propellant_I_11(self):
         """
         return (
             self.propellant_mass
-            * (3 * self.chamber_radius ** 2 + self.chamber_height ** 2)
+            * (3 * self.chamber_radius**2 + self.chamber_height**2)
             / 12
         )
 
@@ -1333,7 +1333,7 @@ def propellant_I_33(self):
         ----------
         https://en.wikipedia.org/wiki/Moment_of_inertia#Inertia_tensor
         """
-        return self.propellant_mass * self.chamber_radius ** 2 / 2
+        return self.propellant_mass * self.chamber_radius**2 / 2
 
     @funcify_method("Time (s)", "Inertia I_12 (kg m²)")
     def propellant_I_12(self):

rocketpy/motors/solid_motor.py

@@ -316,7 +316,7 @@ class Function. Thrust units are Newtons.
         )
         # Nozzle parameters
         self.throat_radius = throat_radius
-        self.throat_area = np.pi * throat_radius ** 2
+        self.throat_area = np.pi * throat_radius**2
 
         # Grain parameters
         self.grains_center_of_mass_position = grains_center_of_mass_position
@@ -331,7 +331,7 @@ class Function. Thrust units are Newtons.
         self.grain_initial_volume = (
             self.grain_initial_height
             * np.pi
-            * (self.grain_outer_radius ** 2 - self.grain_initial_inner_radius ** 2)
+            * (self.grain_outer_radius**2 - self.grain_initial_inner_radius**2)
         )
         self.grain_initial_mass = self.grain_density * self.grain_initial_volume
 
@@ -364,7 +364,7 @@ def grain_volume(self):
             Propellant volume as a function of time.
         """
         cross_section_area = np.pi * (
-            self.grain_outer_radius ** 2 - self.grain_inner_radius ** 2
+            self.grain_outer_radius**2 - self.grain_inner_radius**2
         )
         return cross_section_area * self.grain_height
 
@@ -481,8 +481,8 @@ def geometry_dot(t, y):
                 2
                 * np.pi
                 * (
-                    grain_outer_radius ** 2
-                    - grain_inner_radius ** 2
+                    grain_outer_radius**2
+                    - grain_inner_radius**2
                     + grain_inner_radius * grain_height
                 )
             )
@@ -502,8 +502,8 @@ def geometry_jacobian(t, y):
                 2
                 * np.pi
                 * (
-                    grain_outer_radius ** 2
-                    - grain_inner_radius ** 2
+                    grain_outer_radius**2
+                    - grain_inner_radius**2
                     + grain_inner_radius * grain_height
                 )
                 ** 2
@@ -578,8 +578,8 @@ def burn_area(self):
             2
             * np.pi
             * (
-                self.grain_outer_radius ** 2
-                - self.grain_inner_radius ** 2
+                self.grain_outer_radius**2
+                - self.grain_inner_radius**2
                 + self.grain_inner_radius * self.grain_height
             )
             * self.grain_number
@@ -649,8 +649,8 @@ def propellant_I_11(self):
         grain_mass = self.propellant_mass / self.grain_number
         grain_number = self.grain_number
         grain_inertia11 = grain_mass * (
-            (1 / 4) * (self.grain_outer_radius ** 2 + self.grain_inner_radius ** 2)
-            + (1 / 12) * self.grain_height ** 2
+            (1 / 4) * (self.grain_outer_radius**2 + self.grain_inner_radius**2)
+            + (1 / 12) * self.grain_height**2
         )
 
         # Calculate each grain's distance d to propellant center of mass
@@ -660,7 +660,7 @@ def propellant_I_11(self):
         d = d * (self.grain_initial_height + self.grain_separation)
 
         # Calculate inertia for all grains
-        I_11 = grain_number * grain_inertia11 + grain_mass * np.sum(d ** 2)
+        I_11 = grain_number * grain_inertia11 + grain_mass * np.sum(d**2)
 
         return I_11
 
@@ -709,7 +709,7 @@ def propellant_I_33(self):
         I_33 = (
             (1 / 2.0)
             * self.propellant_mass
-            * (self.grain_outer_radius ** 2 + self.grain_inner_radius ** 2)
+            * (self.grain_outer_radius**2 + self.grain_inner_radius**2)
         )
         return I_33
 

rocketpy/motors/tank.py

@@ -354,7 +354,7 @@ def liquid_inertia(self):
         Ix_volume = Ix_volume @ self.liquid_height
 
         # Steiner theorem to account for center of mass
-        Ix_volume -= self.liquid_volume * self.liquid_center_of_mass ** 2
+        Ix_volume -= self.liquid_volume * self.liquid_center_of_mass**2
         Ix_volume += (
             self.liquid_volume * (self.liquid_center_of_mass - self.center_of_mass) ** 2
         )
@@ -380,7 +380,7 @@ def gas_inertia(self):
         inertia_volume = upper_inertia_volume - lower_inertia_volume
 
         # Steiner theorem to account for center of mass
-        inertia_volume -= self.gas_volume * self.gas_center_of_mass ** 2
+        inertia_volume -= self.gas_volume * self.gas_center_of_mass**2
         inertia_volume += (
             self.gas_volume * (self.gas_center_of_mass - self.center_of_mass) ** 2
         )

rocketpy/motors/tank_geometry.py

@@ -175,7 +175,7 @@ def area(self):
         Function
             Tank cross sectional area as a function of height.
         """
-        return np.pi * self.radius ** 2
+        return np.pi * self.radius**2
 
     @funcify_method("Height (m)", "Volume (m³)", extrapolation="zero")
     def volume(self):
@@ -212,7 +212,7 @@ def inverse_volume(self):
             Tank height as a function of volume.
         """
         return self.volume.inverse_function(
-            lambda v: v / (np.pi * self.average_radius ** 2),
+            lambda v: v / (np.pi * self.average_radius**2),
         )
 
     @cache
@@ -278,7 +278,7 @@ def Ix_volume(self, lower, upper):
         # Tolerance of 1e-8 is used to avoid numerical errors
         upper = upper + 1e-12 if upper - lower < 1e-8 else upper
 
-        inertia = (self.area * (height2 + self.radius ** 2 / 4)).integral_function(
+        inertia = (self.area * (height2 + self.radius**2 / 4)).integral_function(
             lower, upper
         )
 
@@ -325,7 +325,7 @@ def Iz_volume(self, lower, upper):
         # Tolerance of 1e-8 is used to avoid numerical errors
         upper = upper + 1e-12 if upper - lower < 1e-8 else upper
 
-        inertia = (self.area * self.radius ** 2).integral_function(lower, upper) / 2
+        inertia = (self.area * self.radius**2).integral_function(lower, upper) / 2
 
         return inertia
 
@@ -402,10 +402,10 @@ def add_spherical_caps(self):
             upper_cap_range = (height / 2 - radius, height / 2)
 
             def bottom_cap_radius(h):
-                return abs(radius ** 2 - (h + (height / 2 - radius)) ** 2) ** 0.5
+                return abs(radius**2 - (h + (height / 2 - radius)) ** 2) ** 0.5
 
             def upper_cap_radius(h):
-                return abs(radius ** 2 - (h - (height / 2 - radius)) ** 2) ** 0.5
+                return abs(radius**2 - (h - (height / 2 - radius)) ** 2) ** 0.5
 
             self.add_geometry(bottom_cap_range, bottom_cap_radius)
             self.add_geometry(upper_cap_range, upper_cap_radius)
@@ -434,4 +434,4 @@ def __init__(self, radius, geometry_dict=None):
         """
         geometry_dict = geometry_dict or {}
         super().__init__(geometry_dict)
-        self.add_geometry((-radius, radius), lambda h: (radius ** 2 - h ** 2) ** 0.5)
+        self.add_geometry((-radius, radius), lambda h: (radius**2 - h**2) ** 0.5)

rocketpy/plots/aero_surface_plots.py

@@ -260,11 +260,11 @@ def draw(self):
             / (3 * (self.aero_surface.root_chord + self.aero_surface.tip_chord))
         )
         yma_end = (
-            2 * self.aero_surface.root_chord ** 2
+            2 * self.aero_surface.root_chord**2
             + self.aero_surface.root_chord * self.aero_surface.sweep_length
             + 2 * self.aero_surface.root_chord * self.aero_surface.tip_chord
             + 2 * self.aero_surface.sweep_length * self.aero_surface.tip_chord
-            + 2 * self.aero_surface.tip_chord ** 2
+            + 2 * self.aero_surface.tip_chord**2
         ) / (3 * (self.aero_surface.root_chord + self.aero_surface.tip_chord))
         yma_line = plt.Line2D(
             (yma_start, yma_end),