diff --git a/tests/fixtures/acceptance/EPFL_Bella_Lui/bella_lui_flight_sim.py b/tests/fixtures/acceptance/EPFL_Bella_Lui/bella_lui_flight_sim.py
deleted file mode 100644
index f118389f4..000000000
--- a/tests/fixtures/acceptance/EPFL_Bella_Lui/bella_lui_flight_sim.py
+++ /dev/null
@@ -1,242 +0,0 @@
-# Bella Lui Kaltbrunn Mission from ERT (EPFL Rocket Team)
-# Permission to use flight data given by Antoine Scardigli, 2020
-
-# Importing libraries
-from rocketpy import Environment, SolidMotor, Rocket, Flight, Function
-import numpy as np
-import matplotlib.pyplot as plt
-
-# Defining all parameters
-parameters = {
-    # Mass Details
-    "rocket_mass": (18.227, 0.010),  # 1.373 = propellant mass
-    # Propulsion Details
-    "impulse": (2157, 0.03 * 2157),
-    "burn_time": (2.43, 0.1),
-    "nozzle_radius": (44.45 / 1000, 0.001),
-    "throat_radius": (21.4376 / 1000, 0.001),
-    "grain_separation": (3 / 1000, 1 / 1000),
-    "grain_density": (782.4, 30),
-    "grain_outer_radius": (85.598 / 2000, 0.001),
-    "grain_initial_inner_radius": (33.147 / 1000, 0.002),
-    "grain_initial_height": (152.4 / 1000, 0.001),
-    # Aerodynamic Details
-    "inertia_i": (0.78267, 0.03 * 0.78267),
-    "inertia_z": (0.064244, 0.03 * 0.064244),
-    "radius": (156 / 2000, 0.001),
-    "distance_rocket_nozzle": (-1.1356, 0.100),
-    "distance_rocket_propellant": (-1, 0.100),
-    "power_off_drag": (1, 0.05),
-    "power_on_drag": (1, 0.05),
-    "nose_length": (0.242, 0.001),
-    "nose_distance_to_cm": (1.3, 0.100),
-    "fin_span": (0.200, 0.001),
-    "fin_root_chord": (0.280, 0.001),
-    "fin_tip_chord": (0.125, 0.001),
-    "fin_distance_to_cm": (-0.75, 0.100),
-    "tail_top_radius": (156 / 2000, 0.001),
-    "tail_bottom_radius": (135 / 2000, 0.001),
-    "tail_length": (0.050, 0.001),
-    "tail_distance_to_cm": (-1.0856, 0.001),
-    # Launch and Environment Details
-    "wind_direction": (0, 5),
-    "wind_speed": (1, 0.05),
-    "inclination": (89, 1),
-    "heading": (45, 5),
-    "rail_length": (4.2, 0.001),
-    # Parachute Details
-    "CdS_drogue": (np.pi / 4, 0.20 * np.pi / 4),
-    "lag_rec": (1, 0.020),
-}
-
-# Environment conditions
-env = Environment(
-    gravity=9.81,
-    latitude=47.213476,
-    longitude=9.003336,
-    date=(2020, 2, 22, 13, 0, 1),
-    elevation=407,
-)
-env.set_atmospheric_model(
-    type="Reanalysis",
-    file="tests/fixtures/acceptance/EPFL_Bella_Lui/bella_lui_weather_data_ERA5.nc",
-    dictionary="ECMWF",
-)
-env.max_expected_height = 2000
-
-# Motor Information
-K828FJ = SolidMotor(
-    thrust_source="tests/fixtures/acceptance/EPFL_Bella_Lui/bella_lui_motor_AeroTech_K828FJ.eng",
-    burn_time=parameters.get("burn_time")[0],
-    grains_center_of_mass_position=parameters.get("distanceRocketPropellant")[0],
-    grain_number=3,
-    grain_separation=parameters.get("grain_separation")[0],
-    grain_density=parameters.get("grain_density")[0],
-    grain_outer_radius=parameters.get("grain_outer_radius")[0],
-    grain_initial_inner_radius=parameters.get("grain_initial_inner_radius")[0],
-    grain_initial_height=parameters.get("grain_initial_height")[0],
-    nozzle_radius=parameters.get("nozzle_radius")[0],
-    throat_radius=parameters.get("throat_radius")[0],
-    interpolation_method="linear",
-    nozzle_position=parameters.get("distanceRocketNozzle")[0],
-)
-
-# Rocket information
-BellaLui = Rocket(
-    radius=parameters.get("radius")[0],
-    mass=parameters.get("rocket_mass")[0],
-    inertia=(
-        parameters.get("inertia_i")[0],
-        parameters.get("inertia_i")[0],
-        parameters.get("inertia_z")[0],
-    ),
-    power_off_drag=0.43,
-    power_on_drag=0.43,
-)
-BellaLui.set_rail_buttons(0.1, -0.5)
-BellaLui.add_motor(K828FJ, parameters.get("distance_rocket_nozzle")[0])
-NoseCone = BellaLui.add_nose(
-    length=parameters.get("nose_length")[0],
-    kind="tangent",
-    position=parameters.get("nose_distance_to_cm")[0]
-    + parameters.get("nose_length")[0],
-)
-fin_set = BellaLui.add_trapezoidal_fins(
-    3,
-    span=parameters.get("fin_span")[0],
-    root_chord=parameters.get("fin_root_chord")[0],
-    tip_chord=parameters.get("fin_tip_chord")[0],
-    position=parameters.get("fin_distance_to_cm")[0],
-)
-tail = BellaLui.add_tail(
-    top_radius=parameters.get("tail_top_radius")[0],
-    bottom_radius=parameters.get("tail_bottom_radius")[0],
-    length=parameters.get("tail_length")[0],
-    position=parameters.get("tail_distance_to_cm")[0],
-)
-
-
-# Parachute set-up
-def drogue_trigger(p, h, y):
-    # p = pressure
-    # y = [x, y, z, vx, vy, vz, e0, e1, e2, e3, w1, w2, w3]
-    # activate drogue when vz < 0 m/s.
-    return True if y[5] < 0 else False
-
-
-drogue = BellaLui.add_parachute(
-    "Drogue",
-    cd_s=parameters.get("CdS_drogue")[0],
-    trigger=drogue_trigger,
-    sampling_rate=105,
-    lag=parameters.get("lag_rec")[0],
-    noise=(0, 8.3, 0.5),
-)
-
-# Define aerodynamic drag coefficients
-BellaLui.power_off_drag = Function(
-    [
-        (0.01, 0.51),
-        (0.02, 0.46),
-        (0.04, 0.43),
-        (0.28, 0.43),
-        (0.29, 0.44),
-        (0.45, 0.44),
-        (0.49, 0.46),
-    ],
-    "Mach Number",
-    "Drag Coefficient with Power Off",
-    "linear",
-    "constant",
-)
-BellaLui.power_on_drag = Function(
-    [
-        (0.01, 0.51),
-        (0.02, 0.46),
-        (0.04, 0.43),
-        (0.28, 0.43),
-        (0.29, 0.44),
-        (0.45, 0.44),
-        (0.49, 0.46),
-    ],
-    "Mach Number",
-    "Drag Coefficient with Power On",
-    "linear",
-    "constant",
-)
-BellaLui.power_off_drag *= parameters.get("power_off_drag")[0]
-BellaLui.power_on_drag *= parameters.get("power_on_drag")[0]
-
-# Flight
-test_flight = Flight(
-    rocket=BellaLui,
-    environment=env,
-    rail_length=parameters.get("rail_length")[0],
-    inclination=parameters.get("inclination")[0],
-    heading=parameters.get("heading")[0],
-)
-test_flight.post_process()
-
-# Comparision with Real Data
-flight_data = np.loadtxt(
-    "tests/fixtures/acceptance/EPFL_Bella_Lui/bella_lui_flight_data_filtered.csv",
-    skiprows=1,
-    delimiter=",",
-    usecols=(2, 3, 4),
-)
-time_kalt = flight_data[:573, 0]
-altitude_kalt = flight_data[:573, 1]
-vert_vel_kalt = flight_data[:573, 2]
-
-# Make sure that all vectors have the same length
-time_rcp = []
-altitude_rcp = []
-velocity_rcp = []
-acceleration_rcp = []
-i = 0
-while i <= int(test_flight.t_final):
-    time_rcp.append(i)
-    altitude_rcp.append(test_flight.z(i) - test_flight.env.elevation)
-    velocity_rcp.append(test_flight.vz(i))
-    acceleration_rcp.append(test_flight.az(i))
-    i += 0.005
-
-time_rcp.append(test_flight.t_final)
-altitude_rcp.append(0)
-velocity_rcp.append(test_flight.vz(test_flight.t_final))
-acceleration_rcp.append(test_flight.az(test_flight.t_final))
-
-# Acceleration comparison (will not be used in our publication)
-from scipy.signal import savgol_filter
-
-# Calculate the acceleration as a velocity derivative
-acceleration_kalt = [0]
-for i in range(1, len(vert_vel_kalt), 1):
-    acc = (vert_vel_kalt[i] - vert_vel_kalt[i - 1]) / (time_kalt[i] - time_kalt[i - 1])
-    acceleration_kalt.append(acc)
-
-acceleration_kalt_filt = savgol_filter(acceleration_kalt, 51, 3)  # Filter our data
-
-# Summary
-print("Apogee (AGL)")
-print("RocketPy: {:.2f} meters".format(test_flight.apogee - test_flight.env.elevation))
-print("Real data: {:.2f} meters".format(max(altitude_kalt)))
-print(
-    "RocketPy - Real data: {:.2f} meters".format(
-        abs(max(altitude_kalt) - test_flight.apogee + test_flight.env.elevation)
-    )
-)
-print()
-print("Max Velocity")
-print("RocketPy:  {:.2f} m/s".format(max(velocity_rcp)))
-print("Real data: {:.2f} m/s".format(max(vert_vel_kalt)))
-print("RocketPy - Real data: {:.2f} m/s".format(max(velocity_rcp) - max(vert_vel_kalt)))
-print()
-print("Max Acceleration")
-print("RocketPy:  {:.2f} m/s²".format(max(acceleration_rcp)))
-print("Real data (derivative): {:.2f} m/s²".format(max(acceleration_kalt_filt)))
-print(
-    "RocketPy - Real data: {:.2f} m/s^2".format(
-        max(acceleration_rcp) - max(acceleration_kalt_filt)
-    )
-)
diff --git a/tests/fixtures/acceptance/NDRT_2020/ndrt_2020_flight_sim.py b/tests/fixtures/acceptance/NDRT_2020/ndrt_2020_flight_sim.py
deleted file mode 100644
index 376661c81..000000000
--- a/tests/fixtures/acceptance/NDRT_2020/ndrt_2020_flight_sim.py
+++ /dev/null
@@ -1,214 +0,0 @@
-# Notre Dame Rocket Team 2020 Flight
-# Launched at 19045-18879 Avery Rd, Three Oaks, MI 49128
-# Permission to use flight data given by Brooke Mumma, 2020
-#
-# IMPORTANT RESULTS  (23rd feb)
-# Measured Stability Margin 2.875 cal
-# Official Target Altitude 4,444 ft
-# Measured Altitude 4,320 ft or 1316.736 m
-# Drift: 2275 ft
-
-# Importing libraries
-from rocketpy import Environment, SolidMotor, Rocket, Flight, Function
-from scipy.signal import savgol_filter
-import numpy as np
-import pandas as pd
-
-# Defining all parameters
-parameters = {
-    # Mass Details
-    "rocket_mass": (23.321 - 2.475, 0.010),
-    # Propulsion Details
-    "impulse": (4895.050, 0.033 * 4895.050),
-    "burn_time": (3.51, 0.1),
-    "nozzle_radius": (49.5 / 2000, 0.001),
-    "throat_radius": (21.5 / 2000, 0.001),
-    "grain_separation": (3 / 1000, 0.001),
-    "grain_density": (1519.708, 30),
-    "grain_outer_radius": (33 / 1000, 0.001),
-    "grain_initial_inner_radius": (15 / 1000, 0.002),
-    "grain_initial_height": (120 / 1000, 0.001),
-    # Aerodynamic Details
-    "drag_coefficient": (0.44, 0.1),
-    "inertia_i": (83.351, 0.3 * 83.351),
-    "inertia_z": (0.15982, 0.3 * 0.15982),
-    "radius": (203 / 2000, 0.001),
-    "distance_rocket_nozzle": (-1.255, 0.100),
-    "distance_rocket_propellant": (-0.85704, 0.100),
-    "power_off_drag": (1, 0.033),
-    "power_on_drag": (1, 0.033),
-    "nose_length": (0.610, 0.001),
-    "nose_distance_to_cm": (0.71971, 0.100),
-    "fin_span": (0.165, 0.001),
-    "fin_root_chord": (0.152, 0.001),
-    "fin_tip_chord": (0.0762, 0.001),
-    "fin_distance_to_cm": (-1.04956, 0.100),
-    "transition_top_radius": (203 / 2000, 0.010),
-    "transition_bottom_radius": (155 / 2000, 0.010),
-    "transition_length": (0.127, 0.010),
-    "transitiondistance_to_cm": (-1.194656, 0.010),
-    # Launch and Environment Details
-    "wind_direction": (0, 3),
-    "wind_speed": (1, 0.30),
-    "inclination": (90, 1),
-    "heading": (181, 3),
-    "rail_length": (3.353, 0.001),
-    # Parachute Details
-    "CdS_drogue": (1.5 * np.pi * (24 * 25.4 / 1000) * (24 * 25.4 / 1000) / 4, 0.1),
-    "CdS_main": (2.2 * np.pi * (120 * 25.4 / 1000) * (120 * 25.4 / 1000) / 4, 0.1),
-    "lag_rec": (1, 0.5),
-}
-
-# Environment conditions
-Env23 = Environment(
-    gravity=9.81,
-    latitude=41.775447,
-    longitude=-86.572467,
-    date=(2020, 2, 23, 16),
-    elevation=206,
-)
-Env23.set_atmospheric_model(
-    type="Reanalysis",
-    file="tests/fixtures/acceptance/NDRT_2020/ndrt_2020_weather_data_ERA5.nc",
-    dictionary="ECMWF",
-)
-Env23.max_expected_height = 2000
-
-# Motor Information
-L1395 = SolidMotor(
-    thrust_source="tests/fixtures/acceptance/NDRT_2020/ndrt_2020_motor_Cesaroni_4895L1395-P.eng",
-    burn_time=parameters.get("burn_time")[0],
-    grains_center_of_mass_position=parameters.get("distanceRocketPropellant")[0],
-    grain_number=5,
-    grain_separation=parameters.get("grain_separation")[0],
-    grain_density=parameters.get("grain_density")[0],
-    grain_outer_radius=parameters.get("grain_outer_radius")[0],
-    grain_initial_inner_radius=parameters.get("grain_initial_inner_radius")[0],
-    grain_initial_height=parameters.get("grain_initial_height")[0],
-    nozzle_radius=parameters.get("nozzle_radius")[0],
-    throat_radius=parameters.get("throat_radius")[0],
-    interpolation_method="linear",
-    nozzle_position=parameters.get("distanceRocketNozzle")[0],
-)
-
-# Rocket information
-NDRT2020 = Rocket(
-    radius=parameters.get("radius")[0],
-    mass=parameters.get("rocket_mass")[0],
-    inertia=(
-        parameters.get("inertia_i")[0],
-        parameters.get("inertia_i")[0],
-        parameters.get("inertia_z")[0],
-    ),
-    power_off_drag=parameters.get("dragCoefficient")[0],
-    power_on_drag=parameters.get("dragCoefficient")[0],
-)
-NDRT2020.set_rail_buttons(0.2, -0.5, 45)
-NDRT2020.add_motor(L1395, parameters.get("distance_rocket_nozzle")[0])
-NoseCone = NDRT2020.add_nose(
-    length=parameters.get("nose_length")[0],
-    kind="tangent",
-    position=parameters.get("nose_distance_to_cm")[0]
-    + parameters.get("nose_length")[0],
-)
-fin_set = NDRT2020.add_trapezoidal_fins(
-    3,
-    span=parameters.get("fin_span")[0],
-    root_chord=parameters.get("fin_root_chord")[0],
-    tip_chord=parameters.get("fin_tip_chord")[0],
-    position=parameters.get("fin_distance_to_cm")[0],
-)
-transition = NDRT2020.add_tail(
-    top_radius=parameters.get("transition_top_radius")[0],
-    bottom_radius=parameters.get("transition_bottom_radius")[0],
-    length=parameters.get("transition_length")[0],
-    position=parameters.get("transitiondistance_to_cm")[0],
-)
-
-
-# Parachute set-up
-def drogue_trigger(p, h, y):
-    # p = pressure
-    # y = [x, y, z, vx, vy, vz, e0, e1, e2, e3, w1, w2, w3]
-    # activate drogue when vz < 0 m/s.
-    return True if y[5] < 0 else False
-
-
-def main_trigger(p, h, y):
-    # p = pressure
-    # y = [x, y, z, vx, vy, vz, e0, e1, e2, e3, w1, w2, w3]
-    # activate main when vz < 0 m/s and z < 167.64 m (AGL) or 550 ft (AGL)
-    return True if y[5] < 0 and h < 167.64 else False
-
-
-Drogue = NDRT2020.add_parachute(
-    "Drogue",
-    cd_s=parameters.get("CdS_drogue")[0],
-    trigger=drogue_trigger,
-    sampling_rate=105,
-    lag=parameters.get("lag_rec")[0],
-    noise=(0, 8.3, 0.5),
-)
-Main = NDRT2020.add_parachute(
-    "Main",
-    cd_s=parameters.get("CdS_main")[0],
-    trigger=main_trigger,
-    sampling_rate=105,
-    lag=parameters.get("lag_rec")[0],
-    noise=(0, 8.3, 0.5),
-)
-
-# Flight
-Flight23 = Flight(
-    rocket=NDRT2020,
-    environment=Env23,
-    rail_length=parameters.get("rail_length")[0],
-    inclination=parameters.get("inclination")[0],
-    heading=parameters.get("heading")[0],
-)
-Flight23.post_process()
-df_ndrt_rocketpy = pd.DataFrame(Flight23.z[:, :], columns=["Time", "Altitude"])
-df_ndrt_rocketpy["Vertical Velocity"] = Flight23.vz[:, 1]
-df_ndrt_rocketpy["Altitude"] -= Env23.elevation
-
-# Reading data from the flightData (sensors: Raven)
-df_ndrt_raven = pd.read_csv(
-    "tests/fixtures/acceptance/NDRT_2020/ndrt_2020_flight_data.csv"
-)
-# convert feet to meters
-df_ndrt_raven[" Altitude (m-AGL)"] = df_ndrt_raven[" Altitude (Ft-AGL)"] / 3.28084
-df_ndrt_raven[" Time (s)"]
-# Calculate the vertical velocity as a derivative of the altitude
-velocity_raven = [0]
-for i in range(1, len(df_ndrt_raven[" Altitude (m-AGL)"]), 1):
-    v = (
-        df_ndrt_raven[" Altitude (m-AGL)"][i]
-        - df_ndrt_raven[" Altitude (m-AGL)"][i - 1]
-    ) / (df_ndrt_raven[" Time (s)"][i] - df_ndrt_raven[" Time (s)"][i - 1])
-    if (
-        v != 92.85844059786486
-        and v != -376.85000927682034
-        and v != -57.00530169566588
-        and v != -52.752200796647145
-        and v != 63.41561104540437
-    ):
-        # This way we remove the outliers
-        velocity_raven.append(v)
-    else:
-        velocity_raven.append(velocity_raven[-1])
-
-# Filter the data for a better resolution:
-velocity_raven_filt = savgol_filter(velocity_raven, 51, 3)
-
-# Output comparison between flight and simulation data: summary
-print("Apogee raven NDRT: ", max(df_ndrt_raven[" Altitude (m-AGL)"]), "m")
-print("Apogee RocketPy: ", max(df_ndrt_rocketpy["Altitude"]), "m")
-print(
-    "Relative error:",
-    100
-    * (max(df_ndrt_rocketpy["Altitude"]) - max(df_ndrt_raven[" Altitude (m-AGL)"]))
-    / max(df_ndrt_raven[" Altitude (m-AGL)"]),
-)
-print("Apogee time raven NDRT: ", 17.095, "s")
-print("Apogee time Rocketpy: ", 16.77, "s")
-print("Relative error:", 100 * (16.77 - 17.095) / 17.095, "%")
diff --git a/tests/fixtures/acceptance/PJ_Valetudo/valetudo_flight_sim.py b/tests/fixtures/acceptance/PJ_Valetudo/valetudo_flight_sim.py
deleted file mode 100644
index 4a73eb460..000000000
--- a/tests/fixtures/acceptance/PJ_Valetudo/valetudo_flight_sim.py
+++ /dev/null
@@ -1,159 +0,0 @@
-# Valetudo Flight from Projeto Jupiter
-# Launched at LASC 2019
-# Permission to use flight data given by Projeto Jupiter, 2020
-
-# Importing libraries
-from rocketpy import Environment, SolidMotor, Rocket, Flight, Function
-from scipy.signal import savgol_filter
-import numpy as np
-import os
-
-# Import parachute trigger algorithm named SisRec
-if os.name == "nt":
-    from SisRecWindows import SisRec
-else:
-    from SisRecLinux import SisRec
-
-# Defining all parameters
-analysis_parameters = {
-    # Mass Details
-    "rocket_mass": (8.257, 0.001),
-    # Propulsion Details
-    "impulse": (1415.15, 35.3),
-    "burn_time": (5.274, 1),
-    "nozzle_radius": (21.642 / 1000, 0.5 / 1000),
-    "throat_radius": (8 / 1000, 0.5 / 1000),
-    "grain_separation": (6 / 1000, 1 / 1000),
-    "grain_density": (1707, 50),
-    "grain_outer_radius": (21.4 / 1000, 0.375 / 1000),
-    "grain_initial_inner_radius": (9.65 / 1000, 0.375 / 1000),
-    "grain_initial_height": (120 / 1000, 1 / 1000),
-    # Aerodynamic Details
-    "inertia_i": (3.675, 0.03675),
-    "inertia_z": (0.007, 0.00007),
-    "radius": (40.45 / 1000, 0.001),
-    "distance_rocket_nozzle": (-1.024, 0.001),
-    "distance_rocket_propellant": (-0.571, 0.001),
-    "power_off_drag": (0.9081 / 1.05, 0.033),
-    "power_on_drag": (0.9081 / 1.05, 0.033),
-    "nose_length": (0.274, 0.001),
-    "nose_distance_to_cm": (1.134, 0.001),
-    "fin_span": (0.077, 0.0005),
-    "fin_root_chord": (0.058, 0.0005),
-    "fin_tip_chord": (0.018, 0.0005),
-    "fin_distance_to_cm": (-0.906, 0.001),
-    # Launch and Environment Details
-    "wind_direction": (0, 2),
-    "wind_speed": (1, 0.033),
-    "inclination": (84.7, 1),
-    "heading": (53, 2),
-    "rail_length": (5.7, 0.0005),
-    # "ensemble_member": list(range(10)),
-    # Parachute Details
-    "CdS_drogue": (0.349 * 1.3, 0.07),
-    "lag_rec": (1, 0.5),
-    # Electronic Systems Details
-    "lag_se": (0.73, 0.16),
-}
-
-# Environment conditions
-env = Environment(
-    gravity=9.8,
-    date=(2019, 8, 10, 21),
-    latitude=-23.363611,
-    longitude=-48.011389,
-)
-env.set_elevation(668)
-env.max_expected_height = 1500
-env.set_atmospheric_model(
-    type="Reanalysis",
-    file="tests/fixtures/acceptance/PJ_Valetudo/valetudo_weather_data_ERA5.nc",
-    dictionary="ECMWF",
-)
-
-# Create motor
-Keron = SolidMotor(
-    thrust_source="tests/fixtures/acceptance/PJ_Valetudo/valetudo_motor_Keron.csv",
-    burn_time=5.274,
-    grains_center_of_mass_position=analysis_parameters.get(
-        "distance_rocket_propellant"
-    )[0],
-    reshape_thrust_curve=(
-        analysis_parameters.get("burn_time")[0],
-        analysis_parameters.get("impulse")[0],
-    ),
-    nozzle_radius=analysis_parameters.get("nozzle_radius")[0],
-    throat_radius=analysis_parameters.get("throat_radius")[0],
-    grain_number=6,
-    grain_separation=analysis_parameters.get("grain_separation")[0],
-    grain_density=analysis_parameters.get("grain_density")[0],
-    grain_outer_radius=analysis_parameters.get("grain_outer_radius")[0],
-    grain_initial_inner_radius=analysis_parameters.get("grain_initial_inner_radius")[0],
-    grain_initial_height=analysis_parameters.get("grain_initial_height")[0],
-    interpolation_method="linear",
-    nozzle_position=analysis_parameters.get("distance_rocket_nozzle")[0],
-)
-
-# Create rocket
-Valetudo = Rocket(
-    motor=Keron,
-    radius=analysis_parameters.get("radius")[0],
-    mass=analysis_parameters.get("rocket_mass")[0],
-    inertia=(
-        analysis_parameters.get("inertia_i")[0],
-        analysis_parameters.get("inertia_i")[0],
-        analysis_parameters.get("inertia_z")[0],
-    ),
-    power_off_drag="tests/fixtures/acceptance/PJ_Valetudo/valetudo_drag_power_off.csv",
-    power_on_drag="tests/fixtures/acceptance/PJ_Valetudo/valetudo_drag_power_on.csv",
-)
-Valetudo.power_off_drag *= analysis_parameters.get("power_off_drag")[0]
-Valetudo.power_on_drag *= analysis_parameters.get("power_on_drag")[0]
-Valetudo.add_motor(Keron, analysis_parameters.get("distance_rocket_nozzle")[0])
-nosecone = Valetudo.add_nose(
-    length=analysis_parameters.get("nose_length")[0],
-    kind="vonKarman",
-    position=analysis_parameters.get("nose_distance_to_cm")[0]
-    + analysis_parameters.get("nose_length")[0],
-)
-fin_set = Valetudo.add_trapezoidal_fins(
-    n=3,
-    root_chord=analysis_parameters.get("fin_root_chord")[0],
-    tip_chord=analysis_parameters.get("fin_tip_chord")[0],
-    span=analysis_parameters.get("fin_span")[0],
-    position=analysis_parameters.get("fin_distance_to_cm")[0],
-)
-Valetudo.set_rail_buttons(0.224, -0.93, 30)
-
-# Set up parachutes
-sis_rec_drogue = SisRec.SisRecSt(0.8998194205245451, 0.2)
-
-
-def drogue_trigger(p, h, y):
-    return True if sis_rec_drogue.update(p / 100000) == 2 else False
-
-
-drogue = Valetudo.add_parachute(
-    "Drogue",
-    cd_s=analysis_parameters["CdS_drogue"][0],
-    trigger=drogue_trigger,
-    sampling_rate=105,
-    lag=analysis_parameters["lag_rec"][0] + analysis_parameters["lag_se"][0],
-    noise=(0, 8.3, 0.5),
-)
-# Prepare parachutes
-sis_rec_drogue.reset()
-sis_rec_drogue.enable()
-
-test_flight = Flight(
-    rocket=Valetudo,
-    environment=env,
-    rail_length=analysis_parameters.get("rail_length")[0],
-    inclination=analysis_parameters.get("inclination")[0],
-    heading=analysis_parameters.get("heading")[0],
-    max_time=600,
-)
-test_flight.post_process()
-
-# Print summary
-test_flight.info()