MNT: apply isort and black to all the files

docs/examples/ndrt_2020_flight_sim.ipynb

@@ -81,7 +81,7 @@
    "source": [
     "parameters = {\n",
     "    # Mass Details\n",
-    "    \"rocket_mass\": (18.998, 0.010), # Rocket dry mass: 20.846 kg\n",
+    "    \"rocket_mass\": (18.998, 0.010),  # Rocket dry mass: 20.846 kg\n",
     "    # propulsion details\n",
     "    \"motor_structure_mass\": (1.848, 0.1),\n",
     "    \"burn_time\": (3.433, 0.1),\n",
@@ -222,7 +222,7 @@
     "    throat_radius=parameters.get(\"throat_radius\")[0],\n",
     "    interpolation_method=\"linear\",\n",
     "    nozzle_position=parameters.get(\"nozzle_position\")[0],\n",
-    "    coordinate_system_orientation=\"combustion_chamber_to_nozzle\" #combustion_chamber_to_nozzle\"\n",
+    "    coordinate_system_orientation=\"combustion_chamber_to_nozzle\",  # combustion_chamber_to_nozzle\"\n",
     ")"
    ]
   },
@@ -329,9 +329,7 @@
     ")\n",
     "ndrt2020.set_rail_buttons(1.5, 2, 45)\n",
     "\n",
-    "ndrt2020.add_motor(\n",
-    "    motor=motor_l1395, position=parameters.get(\"motor_position\")[0]\n",
-    ")"
+    "ndrt2020.add_motor(motor=motor_l1395, position=parameters.get(\"motor_position\")[0])"
    ]
   },
   {
@@ -358,7 +356,7 @@
     "nose_cone = ndrt2020.add_nose(\n",
     "    length=parameters.get(\"nose_length\")[0],\n",
     "    kind=\"tangent\",\n",
-    "    position=parameters.get(\"nose_position\")[0]\n",
+    "    position=parameters.get(\"nose_position\")[0],\n",
     ")\n",
     "fin_set = ndrt2020.add_trapezoidal_fins(\n",
     "    4,\n",
@@ -700,7 +698,7 @@
     "    outputs=\"Altitude above ground level (m)\",\n",
     "    interpolation=\"linear\",\n",
     "    extrapolation=\"zero\",\n",
-    ") # the division by 3.281 is to convert from feet to meters"
+    ")  # the division by 3.281 is to convert from feet to meters"
    ]
   },
   {
@@ -740,7 +738,7 @@
    ],
    "source": [
     "Function.compare_plots(\n",
-    "    plot_list=[(actual_vz, \"Actual\"),(actual_vz_filtered, \"Filtered\")],\n",
+    "    plot_list=[(actual_vz, \"Actual\"), (actual_vz_filtered, \"Filtered\")],\n",
     "    ylabel=\"Vertical velocity (m/s)\",\n",
     "    title=\"Vertical velocity\",\n",
     "    xlabel=\"Time (s)\",\n",
@@ -785,11 +783,11 @@
    ],
    "source": [
     "Function.compare_plots(\n",
-    "    plot_list=[(actual_az, \"Actual\"),(actual_az_filtered, \"Filtered\")],\n",
+    "    plot_list=[(actual_az, \"Actual\"), (actual_az_filtered, \"Filtered\")],\n",
     "    ylabel=\"Vertical acceleration (m/s^2)\",\n",
     "    title=\"Vertical acceleration\",\n",
     "    xlabel=\"Time (s)\",\n",
-    ")\n"
+    ")"
    ]
   },
   {

docs/notebooks/air_brakes_example.ipynb

@@ -204,14 +204,14 @@
     "    altitude_ASL = state[2]\n",
     "    altitude_AGL = altitude_ASL - env.elevation\n",
     "    vx, vy, vz = state[3], state[4], state[5]\n",
-    "    \n",
+    "\n",
     "    # Get winds in x and y directions\n",
-    "    wind_x, wind_y = env.wind_velocity_x(altitude_ASL), env.wind_velocity_y(altitude_ASL)\n",
-    "    \n",
+    "    wind_x, wind_y = env.wind_velocity_x(altitude_ASL), env.wind_velocity_y(\n",
+    "        altitude_ASL\n",
+    "    )\n",
+    "\n",
     "    # Calculate Mach number\n",
-    "    free_stream_speed = (\n",
-    "        (wind_x - vx) ** 2 + (wind_y - vy) ** 2 + (vz) ** 2\n",
-    "    ) ** 0.5\n",
+    "    free_stream_speed = ((wind_x - vx) ** 2 + (wind_y - vy) ** 2 + (vz) ** 2) ** 0.5\n",
     "    mach_number = free_stream_speed / env.speed_of_sound(altitude_ASL)\n",
     "\n",
     "    # Get previous state from state_history\n",

docs/notebooks/compare_flights_usage.ipynb

@@ -72,7 +72,7 @@
     "env = Environment(latitude=-23, longitude=-49, date=after_tomorrow)\n",
     "env.set_atmospheric_model(type=\"Forecast\", file=\"GFS\")\n",
     "\n",
-    "Pro75M1670 =  SolidMotor(\n",
+    "Pro75M1670 = SolidMotor(\n",
     "    thrust_source=\"../../data/motors/Cesaroni_M1670.eng\",\n",
     "    dry_mass=1.815,\n",
     "    dry_inertia=(0.125, 0.125, 0.002),\n",
@@ -109,9 +109,7 @@
     "\n",
     "calisto.add_motor(Pro75M1670, position=-1.255)\n",
     "\n",
-    "nosecone = calisto.add_nose(\n",
-    "    length=0.55829, kind=\"vonKarman\", position=1.278\n",
-    ")\n",
+    "nosecone = calisto.add_nose(length=0.55829, kind=\"vonKarman\", position=1.278)\n",
     "\n",
     "fin_set = calisto.add_trapezoidal_fins(\n",
     "    n=4,\n",
@@ -120,7 +118,7 @@
     "    span=0.110,\n",
     "    position=-1.04956,\n",
     "    cant_angle=0.5,\n",
-    "    airfoil=(\"../../data/calisto/NACA0012-radians.csv\",\"radians\"),\n",
+    "    airfoil=(\"../../data/calisto/NACA0012-radians.csv\", \"radians\"),\n",
     ")\n",
     "\n",
     "tail = calisto.add_tail(\n",
@@ -194,7 +192,7 @@
     "            heading=heading,\n",
     "            name=f\"Incl {inclination} Head {heading}\",\n",
     "        )\n",
-    "        flights.append(flight)\n"
+    "        flights.append(flight)"
    ]
   },
   {

docs/notebooks/deployable_payload_example.ipynb

@@ -116,9 +116,7 @@
    "metadata": {},
    "outputs": [],
    "source": [
-    "env = Environment(\n",
-    "    latitude=32.990254, longitude=-106.974998, elevation=1400\n",
-    ")"
+    "env = Environment(latitude=32.990254, longitude=-106.974998, elevation=1400)"
    ]
   },
   {
@@ -140,7 +138,9 @@
     "\n",
     "tomorrow = datetime.date.today() + datetime.timedelta(days=1)\n",
     "\n",
-    "env.set_date((tomorrow.year, tomorrow.month, tomorrow.day, 12))  # Hour given in UTC time\n",
+    "env.set_date(\n",
+    "    (tomorrow.year, tomorrow.month, tomorrow.day, 12)\n",
+    ")  # Hour given in UTC time\n",
     "\n",
     "env.set_atmospheric_model(type=\"Forecast\", file=\"GFS\")\n",
     "env.max_expected_height = 8000"
@@ -345,7 +345,11 @@
     "payload_mass = 4.5  # in kg\n",
     "rocket_mass = 14.426 - payload_mass  # in kg\n",
     "\n",
-    "print(\"Rocket Mass Without Motor: {:.4} kg (with Payload)\".format(rocket_mass + payload_mass))\n",
+    "print(\n",
+    "    \"Rocket Mass Without Motor: {:.4} kg (with Payload)\".format(\n",
+    "        rocket_mass + payload_mass\n",
+    "    )\n",
+    ")\n",
     "print(\"Loaded Motor Mass: {:.4} kg\".format(Pro75M1670.total_mass(0)))\n",
     "print(\"Payload Mass: {:.4} kg\".format(payload_mass))\n",
     "print(\n",
@@ -398,9 +402,7 @@
     "    angular_position=45,\n",
     ")\n",
     "\n",
-    "rocket_with_payload.add_nose(\n",
-    "    length=0.55829, kind=\"von karman\", position=1.278\n",
-    ")\n",
+    "rocket_with_payload.add_nose(length=0.55829, kind=\"von karman\", position=1.278)\n",
     "\n",
     "rocket_with_payload.add_trapezoidal_fins(\n",
     "    n=4,\n",
@@ -409,7 +411,7 @@
     "    span=0.110,\n",
     "    position=-1.04956,\n",
     "    cant_angle=0.5,\n",
-    "    airfoil=(\"NACA0012-radians.csv\",\"radians\"),\n",
+    "    airfoil=(\"NACA0012-radians.csv\", \"radians\"),\n",
     ")\n",
     "\n",
     "rocket_with_payload.add_tail(\n",
@@ -642,7 +644,7 @@
     "flight_without_payload = Flight(\n",
     "    rocket=rocket_without_payload,\n",
     "    environment=env,\n",
-    "    rail_length=5.2, # does not matter since the flight is starting at apogee\n",
+    "    rail_length=5.2,  # does not matter since the flight is starting at apogee\n",
     "    inclination=0,\n",
     "    heading=0,\n",
     "    initial_solution=flight_with_payload,\n",
@@ -680,10 +682,10 @@
     "payload_rocket = Rocket(\n",
     "    radius=127 / 2000,\n",
     "    mass=payload_mass,\n",
-    "    inertia=(0.1,0.1,0.001),\n",
+    "    inertia=(0.1, 0.1, 0.001),\n",
     "    power_off_drag=0.5,\n",
     "    power_on_drag=0.5,\n",
-    "    center_of_mass_without_motor=0\n",
+    "    center_of_mass_without_motor=0,\n",
     ")\n",
     "\n",
     "payload_drogue = payload_rocket.add_parachute(\n",
@@ -722,7 +724,7 @@
     "payload_flight = Flight(\n",
     "    rocket=payload_rocket,\n",
     "    environment=env,\n",
-    "    rail_length=5.2, # does not matter since the flight is starting at apogee\n",
+    "    rail_length=5.2,  # does not matter since the flight is starting at apogee\n",
     "    inclination=0,\n",
     "    heading=0,\n",
     "    initial_solution=flight_with_payload,\n",
@@ -770,7 +772,9 @@
    "metadata": {},
    "outputs": [],
    "source": [
-    "comparison = CompareFlights([flight_with_payload, flight_without_payload, payload_flight])"
+    "comparison = CompareFlights(\n",
+    "    [flight_with_payload, flight_without_payload, payload_flight]\n",
+    ")"
    ]
   },
   {

docs/notebooks/dispersion_analysis/dispersion_analysis.ipynb

@@ -12894,9 +12894,7 @@
     ")\n",
     "\n",
     "plt.figure()\n",
-    "plt.hist(\n",
-    "    dispersion_results[\"initial_static_margin\"], label=\"Initial\", bins=int(N**0.5)\n",
-    ")\n",
+    "plt.hist(dispersion_results[\"initial_static_margin\"], label=\"Initial\", bins=int(N**0.5))\n",
     "plt.hist(\n",
     "    dispersion_results[\"out_of_rail_static_margin\"],\n",
     "    label=\"Out of Rail\",\n",