Hedy - TU Wien Space Team - 2025#
Team: TUST
Project: Lamarr
Rocket: Hedy
Launched on 12.10.2025 at EuRoC
Installs#
In this section all needed libraries are installed and the needed classes imported
[ ]:
%pip install rocketpy
[ ]:
%pip install CoolProp
[24]:
import CoolProp.CoolProp as CP
from rocketpy import (
CompareFlights,
CylindricalTank,
Environment,
Flight,
Fluid,
FreeFormFins,
LiquidMotor,
MassFlowRateBasedTank,
NoseCone,
Parachute,
Rocket,
Tail,
)
Configuration#
The length unit chosen here is millimeters to keep the values more readable. If necessary, values should be converted accordingly.
[37]:
# Rocket configuration data
env_config = {
"date": (2025, 10, 12, 17, 00, 00), # yyyy, mm, dd, hh, mm, ss # preset
"latitude": 39.39046096801758, # Launch latitude # preset
"longitude": -8.288534164428711, # Launch longitude # preset
"max_height": 9000, # m # preset
"timezone": "Europe/Lisbon", # GMT+1 # preset
}
motor_config = {
"holddown_time": 1.4, # s # preset
"nitrogen_tank": {
"length": 235, # mm # measured
"CG_lox": 2653, # mm # measured # CG lox nitrogen tank
"CG_ethanol": 1450, # mm # measured # CG ethanol nitrogen tank
"outer_diameter": 93, # mm # measured
"volume": 1.2, # l # measured
"massflow": 0.03, # kg/s # estimated
},
"ethanol_tank": {
"length": 573, # mm # measured
"CG": 852, # mm # measured
"outer_diameter": 115, # mm # measured
"volume": 5.27, # l # measured
"massflow": 0.45, # kg/s # tested
},
"lox_tank": {
"length": 573, # mm # measured
"CG": 1960, # mm # measured
"outer_diameter": 115, # mm # measured
"volume": 5.27, # l # measured
"massflow": 0.56, # kg/s # tested
},
"nozzle": {
"diameter": 75, # mm # measured
"position": -40, # mm # measured
},
"thrust": "../../data/rockets/tust/hedy_thrust_euroc_launch.csv", # N # measured
"temperature": {
"ethanol": 298.15, # K # preset (= 25°C)
"lox": 93.15, # K # preset (= -180°C)
"nitrogen": 298.15, # K # preset (= 25°C)
},
"pressure": {
"ethanol": 3000000, # Pa # preset
"lox": 3000000, # Pa # preset
"nitrogen": 30000000, # Pa # preset
},
}
rocket_config = {
"total_weight": 17200, # g # weighed dry mass
"total_length": 3707, # mm # measured
"total_CG": 1813, # mm # measured
"moment_of_intertia_Z": 0.0255, # kg*m^2 # calculated
"moment_of_intertia_XY": 16.8, # kg*m^2 # calculated
"nosecone": {
"length": 561, # mm # measured # 575 + 66 - 80 = 561
"kind": "lv haack",
},
"railbuttons": {
"upper": 1646, # mm # measured
"lower": 305, # mm # measured
},
"tailcone": {
"diameter": 108, # mm # measured
"length": 245, # mm # measured
"cylindrical_height": 35, # mm # measured
},
"rocket": {
"thickness": 1.4, # mm # measured
"diameter": 132.8, # mm # measured
},
"fins": {
"name": "Biconvex-Freeform",
"amount": 4,
"position": 250, # mm # measured
"shape_points": (
(0, 0),
(0.250, -0.012),
(0.250, 0.108),
(0.195, 0.108),
(0, 0),
), # m # measured
},
"parachutes": {
"main": {
"cd_s": 6.911503837897546, # calculated
"trigger": 450, # m # preset
"sampling_rate": 105, # hz # preset
"lag": 4, # s # measured
"noise": (0, 8.3, 0.5), # (pa, pa, pa) # preset
},
"drogue": {
"cd_s": 0.5336875,
"trigger": "apogee", # m # preset
"sampling_rate": 105, # hz # preset
"lag": 1, # s # measured
"noise": (0, 8.3, 0.5), # (pa, pa, pa) # preset
},
},
}
flight_config = {
"rail_length": 11, # m #Preset
"inclination": 84, # ° #Preset
"heading": 184, # ° #Preset
"terminate_on_apogee": False,
}
Environments Initialization#
In this section the environments are initialized.
envReanalysis: environment with the weather data from the location and date of EuRoc’25
[38]:
# Ponte de Sor: 39.12368, -8.03333
# Launch date: 12.10.2025, 17:00
latitude = env_config["latitude"]
longitude = env_config["longitude"]
timezone = env_config["timezone"]
date = env_config["date"]
max_height = env_config["max_height"]
# Environment based on weather data of the EuRoC 2025
envReanalysis = Environment(max_expected_height=max_height)
envReanalysis.set_location(latitude=latitude, longitude=longitude)
envReanalysis.set_elevation("Open-Elevation")
envReanalysis.set_date(date, timezone=timezone)
envReanalysis.set_atmospheric_model(
type="Reanalysis",
file="../../data/weather/hedy_euroc_2025_weather_data.nc",
dictionary="ECMWF",
)
envReanalysis.info()
Fetching elevation from open-elevation.com for lat=39.39046096801758, lon=-8.288534164428711...
Elevation received: 160.0 m
Gravity Details
Acceleration of gravity at surface level: 9.7798 m/s²
Acceleration of gravity at 6.555 km (ASL): 9.7601 m/s²
Launch Site Details
Launch Date: 2025-10-12 16:00:00 UTC | 2025-10-12 17:00:00 Europe/Lisbon
Launch Site Latitude: 39.39046°
Launch Site Longitude: -8.28853°
Reference Datum: SIRGAS2000
Launch Site UTM coordinates: 166021.44 W|E 0.00 N
Launch Site UTM zone: 31N
Launch Site Surface Elevation: 160.0 m
Atmospheric Model Details
Atmospheric Model Type: Reanalysis
Reanalysis Maximum Height: 6.555 km
Reanalysis Time Period: from 2025-10-12 15:00:00 to 2025-10-12 20:00:00 utc
Reanalysis Hour Interval: 1 hrs
Reanalysis Latitude Range: From 42.0° to 36.0°
Reanalysis Longitude Range: From -10.0° to -6.0°
Surface Atmospheric Conditions
Surface Wind Speed: 2.23 m/s
Surface Wind Direction: 67.67°
Surface Wind Heading: 247.67°
Surface Pressure: 996.64 hPa
Surface Temperature: 298.82 K
Surface Air Density: 1.162 kg/m³
Surface Speed of Sound: 346.54 m/s
Earth Model Details
Earth Radius at Launch site: 6378.14 km
Semi-major Axis: 6378.14 km
Semi-minor Axis: 6356.75 km
Flattening: 0.0034
Atmospheric Model Plots
Simulation#
Tanks / Engine#
[39]:
# holddown time
t_holddown = motor_config["holddown_time"]
# tank height
h_nitrogen_tank = motor_config["nitrogen_tank"]["length"] / 1000
h_ethanol_tank = motor_config["ethanol_tank"]["length"] / 1000
h_lox_tank = motor_config["lox_tank"]["length"] / 1000
# OuterDiameter
OD_nitrogen_tank = motor_config["nitrogen_tank"]["outer_diameter"] / 1000
OD_ethanol_tank = motor_config["ethanol_tank"]["outer_diameter"] / 1000
OD_lox_tank = motor_config["lox_tank"]["outer_diameter"] / 1000
# volume
v_nitrogen_tank = motor_config["nitrogen_tank"]["volume"] / 1000
v_ethanol_tank = motor_config["ethanol_tank"]["volume"] / 1000
v_lox_tank = motor_config["lox_tank"]["volume"] / 1000
# massflows
mdot_nitrogen = motor_config["nitrogen_tank"]["massflow"]
mdot_ethanol = motor_config["ethanol_tank"]["massflow"]
mdot_lox = motor_config["lox_tank"]["massflow"]
# nozzle
nozzle_diameter = motor_config["nozzle"]["diameter"] / 1000
# thrust
thrust = motor_config["thrust"]
# Temperature Lox & Ethanol
T_nitrogen = motor_config["temperature"]["nitrogen"]
T_ethanol = motor_config["temperature"]["ethanol"]
T_lox = motor_config["temperature"]["lox"]
# pressure LOX & Ethanol
p_nitrogen = motor_config["pressure"]["nitrogen"]
p_ethanol = motor_config["pressure"]["ethanol"]
p_lox = motor_config["pressure"]["lox"]
# Propellants
# define density
rho_nitrogen = CP.PropsSI("D", "T", T_nitrogen, "P|gas", p_nitrogen, "N2") # kg/m^3
rho_ethanol = CP.PropsSI(
"D", "T|liquid", T_ethanol, "P", p_ethanol, "ethanol"
) # kg/m^3
rho_lox = CP.PropsSI("D", "T|liquid", T_lox, "P", p_lox, "oxygen") # kg/m^3
# define fluids
nitrogen = Fluid(name="N2", density=rho_nitrogen)
ethanol = Fluid(name="ethanol", density=rho_ethanol)
lox = Fluid(name="LOX", density=rho_lox)
# define tanks geometry
nitrogen_tank_shape = CylindricalTank(
radius=OD_nitrogen_tank / 2, height=h_nitrogen_tank, spherical_caps=True
)
ethanol_tank_shape = CylindricalTank(
radius=OD_ethanol_tank / 2, height=h_ethanol_tank, spherical_caps=True
)
lox_tank_shape = CylindricalTank(
radius=OD_lox_tank / 2, height=h_lox_tank, spherical_caps=True
)
m_nitrogen = v_nitrogen_tank * rho_nitrogen # m
m_ethanol = v_ethanol_tank * rho_ethanol # m
m_lox = v_lox_tank * rho_lox # m
t_burn_nitrogen = (m_nitrogen / mdot_nitrogen) - 0.001 # s
t_burn_ethanol = m_ethanol / mdot_ethanol
t_burn_lox = m_lox / mdot_lox
if t_burn_ethanol < t_burn_lox:
t_burn = t_burn_ethanol
print(f"using ethanol burn time ({t_burn_ethanol}). LOX burntime is {t_burn_lox}")
else:
t_burn = t_burn_lox
print(f"using lox burn time ({t_burn_lox}). Ethanol burntime is {t_burn_ethanol}")
# account for holddown
t_burn -= t_holddown
m_lox = (
mdot_lox * t_burn + 0.0001
) # adding a little more so python does not throw an error
m_ethanol = mdot_ethanol * t_burn + 0.0001
m_nitrogen = mdot_nitrogen * t_burn + 0.0001
# define tanks
nitrogen_tank = MassFlowRateBasedTank(
name="nitrogen tank",
geometry=nitrogen_tank_shape,
flux_time=t_burn,
initial_liquid_mass=0, # kg
initial_gas_mass=m_nitrogen,
liquid_mass_flow_rate_in=0, # kg/s
liquid_mass_flow_rate_out=0, # kg/s
gas_mass_flow_rate_in=0, # kg/s
gas_mass_flow_rate_out=lambda t: mdot_nitrogen,
liquid=Fluid(name="liquid", density=0.0001), # ignore
gas=nitrogen,
)
ethanol_tank = MassFlowRateBasedTank(
name="fuel tank",
geometry=ethanol_tank_shape,
flux_time=t_burn,
initial_liquid_mass=m_ethanol,
initial_gas_mass=0, # kg
liquid_mass_flow_rate_in=0, # kg/s
liquid_mass_flow_rate_out=lambda t: mdot_ethanol,
gas_mass_flow_rate_in=lambda t: mdot_nitrogen,
gas_mass_flow_rate_out=0, # kg/s
liquid=ethanol,
gas=nitrogen,
)
lox_tank = MassFlowRateBasedTank(
name="oxidizer tank",
geometry=lox_tank_shape,
flux_time=t_burn,
initial_liquid_mass=m_lox,
initial_gas_mass=0, # kg
liquid_mass_flow_rate_in=0, # kg/s
liquid_mass_flow_rate_out=lambda t: mdot_lox,
gas_mass_flow_rate_in=lambda t: mdot_nitrogen,
gas_mass_flow_rate_out=0, # kg/s
liquid=lox,
gas=nitrogen,
)
skuld = LiquidMotor(
dry_mass=0, # kg
dry_inertia=(0, 0, 0), # kg*m^2
center_of_dry_mass_position=0, # m
nozzle_radius=nozzle_diameter / 2,
nozzle_position=0, # m
thrust_source=thrust,
burn_time=t_burn,
coordinate_system_orientation="nozzle_to_combustion_chamber",
)
skuld.add_tank(tank=ethanol_tank, position=motor_config["ethanol_tank"]["CG"] / 1000)
skuld.add_tank(tank=lox_tank, position=motor_config["lox_tank"]["CG"] / 1000)
skuld.add_tank(
tank=nitrogen_tank, position=motor_config["nitrogen_tank"]["CG_ethanol"] / 1000
)
skuld.add_tank(
tank=nitrogen_tank, position=motor_config["nitrogen_tank"]["CG_lox"] / 1000
)
skuld.all_info()
Warning: Adding spherical caps to the tank will not modify the total height of the tank 0.235 m. Its cylindrical portion height will be reduced to 0.142 m.
Warning: Adding spherical caps to the tank will not modify the total height of the tank 0.573 m. Its cylindrical portion height will be reduced to 0.45799999999999996 m.
Warning: Adding spherical caps to the tank will not modify the total height of the tank 0.573 m. Its cylindrical portion height will be reduced to 0.45799999999999996 m.
using ethanol burn time (9.225280880958138). LOX burntime is 10.662815399911576
Nozzle Details
Nozzle Radius: 0.0375 m
Motor Details
Total Burning Time: 7.825280880958138 s
Total Propellant Mass: 8.373 kg
Structural Mass Ratio: 0.000
Average Propellant Exhaust Velocity: 1363.917 m/s
Average Thrust: 1369.450 N
Maximum Thrust: 1561.34 N at 2.0 s after ignition.
Total Impulse: 10716.328 Ns
Rocket components#
[40]:
# rocket
rocket_length = rocket_config["total_length"] / 1000
rocket_diameter = rocket_config["rocket"]["diameter"] / 1000
rocket_thickness = rocket_config["rocket"]["thickness"] / 1000
nosecone_length = (
rocket_config["nosecone"]["length"] - 100
) / 1000 # -100 mm to adjust for cylindrical section
nosecone_kind = rocket_config["nosecone"]["kind"]
nose_cone = NoseCone(
length=nosecone_length, base_radius=rocket_diameter / 2, kind=nosecone_kind
)
tailcone_cylindrical = rocket_config["tailcone"]["cylindrical_height"] / 1000
tailcone_length = rocket_config["tailcone"]["length"] / 1000
tailcone_bottom_radius = rocket_config["tailcone"]["diameter"] / 2 / 1000
tail = Tail(
top_radius=rocket_diameter / 2,
bottom_radius=tailcone_bottom_radius,
length=tailcone_length,
rocket_radius=rocket_diameter / 2,
)
fin_amount = rocket_config["fins"]["amount"]
fin_shape_points = rocket_config["fins"]["shape_points"]
fin_name = rocket_config["fins"]["name"]
fin_set = FreeFormFins(
n=fin_amount,
shape_points=fin_shape_points,
rocket_radius=tailcone_bottom_radius,
name=fin_name,
)
fin_set.draw()
main_cd_s = rocket_config["parachutes"]["drogue"][
"cd_s"
] # main didn't deploy fully, so adding another drogue as approximation
main_trigger = rocket_config["parachutes"]["main"]["trigger"]
main_sampling_rate = rocket_config["parachutes"]["main"]["sampling_rate"]
main_lag = rocket_config["parachutes"]["main"]["lag"]
main_noise = rocket_config["parachutes"]["main"]["noise"]
drogue_cd_s = rocket_config["parachutes"]["drogue"]["cd_s"]
drogue_trigger = rocket_config["parachutes"]["drogue"]["trigger"]
drogue_sampling_rate = rocket_config["parachutes"]["drogue"]["sampling_rate"]
drogue_lag = rocket_config["parachutes"]["drogue"]["lag"]
drogue_noise = rocket_config["parachutes"]["drogue"]["noise"]
parachutes = {}
parachutes[0] = Parachute(
name="main",
cd_s=main_cd_s,
trigger=main_trigger,
sampling_rate=main_sampling_rate,
lag=main_lag,
noise=main_noise,
)
parachutes[1] = Parachute(
name="drogue",
cd_s=drogue_cd_s,
trigger=drogue_trigger,
sampling_rate=drogue_sampling_rate,
lag=drogue_lag,
noise=drogue_noise,
)
C:\Users\wattikan\AppData\Local\Packages\PythonSoftwareFoundation.Python.3.13_qbz5n2kfra8p0\LocalCache\local-packages\Python313\site-packages\rocketpy\rocket\aero_surface\fins\free_form_fins.py:143: UserWarning: Jagged fin shape detected. This may cause small inaccuracies center of pressure and pitch moment calculations.
warnings.warn(
Hedy#
[41]:
total_mass = rocket_config["total_weight"] / 1000
# inertia
inertia_x_y = rocket_config["moment_of_intertia_XY"]
inertia_z = rocket_config["moment_of_intertia_Z"]
upper_railbutton_position = rocket_config["railbuttons"]["upper"] / 1000
lower_railbutton_position = rocket_config["railbuttons"]["lower"] / 1000
fin_position = rocket_config["fins"]["position"] / 1000
nozzle_position = motor_config["nozzle"]["position"] / 1000
total_CG = rocket_config["total_CG"] / 1000
hedy = Rocket(
radius=rocket_diameter / 2,
mass=total_mass,
inertia=(inertia_x_y, inertia_x_y, inertia_z),
power_off_drag="../../data/rockets/tust/hedy_power_off_drag.csv",
power_on_drag="../../data/rockets/tust/hedy_power_on_drag.csv",
center_of_mass_without_motor=total_CG,
coordinate_system_orientation="tail_to_nose",
)
hedy.add_motor(skuld, position=nozzle_position)
hedy.set_rail_buttons(
upper_button_position=upper_railbutton_position,
lower_button_position=lower_railbutton_position,
)
hedy.add_surfaces(
surfaces=[nose_cone, fin_set, tail],
positions=[rocket_length, fin_position, tailcone_length],
)
hedy.parachutes = list(parachutes.values())
hedy.all_info()
Inertia Details
Rocket Mass: 17.200 kg (without motor)
Rocket Dry Mass: 17.200 kg (with unloaded motor)
Rocket Loaded Mass: 25.573 kg
Rocket Structural Mass Ratio: 0.673
Rocket Inertia (with unloaded motor) 11: 16.800 kg*m2
Rocket Inertia (with unloaded motor) 22: 16.800 kg*m2
Rocket Inertia (with unloaded motor) 33: 0.025 kg*m2
Rocket Inertia (with unloaded motor) 12: 0.000 kg*m2
Rocket Inertia (with unloaded motor) 13: 0.000 kg*m2
Rocket Inertia (with unloaded motor) 23: 0.000 kg*m2
Geometrical Parameters
Rocket Maximum Radius: 0.0664 m
Rocket Frontal Area: 0.013851 m2
Rocket Distances
Rocket Center of Dry Mass - Center of Mass without Motor: 0.000 m
Rocket Center of Dry Mass - Nozzle Exit: 1.853 m
Rocket Center of Dry Mass - Center of Propellant Mass: 0.421 m
Rocket Center of Mass - Rocket Loaded Center of Mass: 0.138 m
Aerodynamics Lift Coefficient Derivatives
Nose Cone Lift Coefficient Derivative: 2.000/rad
Biconvex-Freeform Lift Coefficient Derivative: 6.930/rad
Tail Lift Coefficient Derivative: -0.677/rad
Center of Pressure
Nose Cone Center of Pressure position: 3.447 m
Biconvex-Freeform Center of Pressure position: 0.131 m
Tail Center of Pressure position: 0.127 m
Stability
Center of Mass position (time=0): 1.675 m
Center of Pressure position (time=0): 0.935 m
Initial Static Margin (mach=0, time=0): 5.573 c
Final Static Margin (mach=0, time=burn_out): 6.476 c
Rocket Center of Mass (time=0) - Center of Pressure (mach=0): 0.740 m
Parachute Details
Parachute Main with a cd_s of 0.5337 m2
Ejection signal trigger: 450 m (AGL)
Ejection system refresh rate: 105.000 Hz
Time between ejection signal is triggered and the parachute is fully opened: 4.0 s
Parachute Details
Parachute Drogue with a cd_s of 0.5337 m2
Ejection signal trigger: At Apogee
Ejection system refresh rate: 105.000 Hz
Time between ejection signal is triggered and the parachute is fully opened: 1.0 s
Rocket Draw
----------------------------------------
Mass Plots
----------------------------------------
Aerodynamics Plots
----------------------------------------
Drag Plots
--------------------
Stability Plots
--------------------
Thrust-to-Weight Plot
----------------------------------------
Flight#
[42]:
rail_length = flight_config["rail_length"]
inclination = flight_config["inclination"]
heading = flight_config["heading"]
terminate_on_apogee = flight_config["terminate_on_apogee"]
flight_reanalysis = Flight(
rocket=hedy,
environment=envReanalysis,
rail_length=rail_length,
inclination=inclination,
heading=heading,
terminate_on_apogee=terminate_on_apogee,
name="Reanalysis",
)
print(
f"Takeoff mass: \t\t\t {hedy.total_mass(flight_reanalysis.out_of_rail_time):.2f} kg"
)
print(
f"Propellant used during holddown: {hedy.total_mass(0) - hedy.total_mass(flight_reanalysis.out_of_rail_time):.2f} kg"
)
flight_reanalysis.prints.out_of_rail_conditions()
flight_reanalysis.prints.apogee_conditions()
# flight_reanalysis.prints.impact_conditions()
flight_reanalysis.prints.maximum_values()
flight_reanalysis.plots.trajectory_3d()
flight_reanalysis.plots.stability_and_control_data()
# flight_reanalysis.prints.all()
# flight_reanalysis.plots.all()
# flight_reanalysis.all_info()
Takeoff mass: 24.85 kg
Propellant used during holddown: 0.72 kg
Rail Departure State
Rail Departure Time: 0.712 s
Rail Departure Velocity: 28.027 m/s
Rail Departure Stability Margin: 5.601 c
Rail Departure Angle of Attack: 4.616°
Rail Departure Thrust-Weight Ratio: 5.807
Rail Departure Reynolds Number: 2.347e+05
Apogee State
Apogee Time: 33.412 s
Apogee Altitude: 5406.918 m (ASL) | 5246.918 m (AGL)
Apogee Freestream Speed: 33.724 m/s
Apogee X position: 419.184 m
Apogee Y position: -1080.044 m
Apogee latitude: 39.3807587°
Apogee longitude: -8.2836624°
Maximum Values
Maximum Speed: 365.662 m/s at 7.83 s
Maximum Mach Number: 1.081 Mach at 7.83 s
Maximum Reynolds Number: 2.810e+06 at 7.83 s
Maximum Dynamic Pressure: 6.857e+04 Pa at 7.83 s
Maximum Acceleration During Motor Burn: 55.421 m/s² at 2.00 s
Maximum Gs During Motor Burn: 5.651 g at 2.00 s
Maximum Acceleration After Motor Burn: 31.722 m/s² at 0.00 s
Maximum Gs After Motor Burn: 3.235 Gs at 0.00 s
Maximum Stability Margin: 7.061 c at 7.83 s
Maximum Upper Rail Button Normal Force: 0.692 N
Maximum Upper Rail Button Shear Force: 1.423 N
Maximum Lower Rail Button Normal Force: 1.146 N
Maximum Lower Rail Button Shear Force: 2.347 N
Comparsion#
Initialization#
[43]:
from rocketpy import Function
from rocketpy.simulation.flight_data_importer import FlightDataImporter
columns_map_cats_vega = {
"ts": "time",
"filteredAltitudeAGL": "altitude",
"filteredAcceleration": "az",
"latitude": "latitude",
"longitude": "longitude",
"Ax": "acceleration_x",
"Ay": "acceleration_y",
"Az": "acceleration_z",
"Gx": "gyro_x",
"Gy": "gyro_y",
"Gz": "gyro_z",
"velocity": "speed",
"P": "pressure",
}
path = "../../data/rockets/tust/cats_tust/"
cats_vega_flight = FlightDataImporter(
name="CATS Vega Flight Data",
paths=[
path + "filteredDataInfo.csv",
path + "gnssInfo.csv",
path + "flightInfo.csv",
path + "imu.csv",
path + "baro.csv",
],
columns_map=columns_map_cats_vega,
units=None,
interpolation="linear",
extrapolation="zero",
delimiter=",",
encoding="utf-8",
)
The following attributes were create and are now available to be used: ['time', 'altitude', 'az']
The following attributes were create and are now available to be used: ['time', 'latitude', 'longitude']
The following attributes were create and are now available to be used: ['time', 'speed']
The following attributes were create and are now available to be used: ['time', 'acceleration_x', 'acceleration_y', 'acceleration_z', 'gyro_x', 'gyro_y', 'gyro_z']
The following attributes were create and are now available to be used: ['time', 'pressure']
Altitude#
[44]:
apogee_actual = cats_vega_flight.altitude.max
apogee_simulated = flight_reanalysis.apogee
apogee_error = abs(apogee_actual - apogee_simulated)
apogee_percentage_error = apogee_error / apogee_actual * 100
print(f"Actual apogee: {apogee_actual:.2f} m")
print(f"Simulated apogee: {apogee_simulated:.2f} m")
print(f"Error: {apogee_error:.2f} m")
print(f"Percentage Error: {apogee_percentage_error:.2f}%")
Function.compare_plots(
[
(flight_reanalysis.altitude, "RocketPy"),
(cats_vega_flight.altitude, "CATS Vega"),
],
title="Altitude Comparison",
xlabel="Time (s)",
ylabel="Altitude (m)",
)
Actual apogee: 5231.53 m
Simulated apogee: 5406.92 m
Error: 175.38 m
Percentage Error: 3.35%
GNSS#
[45]:
Function.compare_plots(
[(flight_reanalysis.latitude, "RocketPy"), (cats_vega_flight.latitude, "CATS")],
title="Latitude Comparison",
xlabel="Time (s)",
ylabel="Latitude (deg)",
)
Function.compare_plots(
[(flight_reanalysis.longitude, "RocketPy"), (cats_vega_flight.longitude, "CATS")],
title="Longitude Comparison",
xlabel="Time (s)",
ylabel="Longitude (deg)",
)
Pressure#
[46]:
pressure_actual = cats_vega_flight.pressure.min
pressure_simulated = flight_reanalysis.pressure.min
pressure_error = abs(pressure_actual - pressure_simulated)
pressure_percentage_error = pressure_error / pressure_actual * 100
print(f"Actual min pressure: {pressure_actual:.2f} Pa")
print(f"Simulated min pressure: {pressure_simulated:.2f} Pa")
print(f"Error: {pressure_error:.2f} Pa")
print(f"Percentage Error: {pressure_percentage_error:.2f}%")
Function.compare_plots(
[
(flight_reanalysis.pressure, "RocketPy"),
(cats_vega_flight.pressure, "CATS vega"),
],
title="Pressure Comparison",
xlabel="Time (s)",
ylabel="Pressure (Pa)",
)
Actual min pressure: 51343.00 Pa
Simulated min pressure: 52452.57 Pa
Error: 1109.57 Pa
Percentage Error: 2.16%
Acceleration#
[47]:
acceleration_actual = cats_vega_flight.az.crop([(0, 20)]).max
acceleration_simulated = flight_reanalysis.acceleration.crop([(0, 20)]).max
acceleration_error = abs(acceleration_actual - acceleration_simulated)
acceleration_percentage_error = acceleration_error / acceleration_actual * 100
print(f"Actual max acceleration during burn: {acceleration_actual:.2f} m/s2")
print(f"Simulated max acceleration during burn: {acceleration_simulated:.2f} m/s2")
print(f"Error: {acceleration_error:.2f} m/s2")
print(f"Percentage Error: {acceleration_percentage_error:.2f}%")
Function.compare_plots(
[
(flight_reanalysis.ay.crop([(0, 100)]), "RocketPy"),
(cats_vega_flight.az.crop([(0, 100)]) / 10 * (-1), "CATS Vega"),
],
title="Acceleration Comparison",
xlabel="Time (s)",
ylabel="Vertical acceleration (m/s^2)",
)
Actual max acceleration during burn: 56.77 m/s2
Simulated max acceleration during burn: 55.42 m/s2
Error: 1.35 m/s2
Percentage Error: 2.38%
Speed#
[48]:
speed_actual = cats_vega_flight.speed.max
speed_simulated = flight_reanalysis.speed.max
speed_error = abs(speed_actual - speed_simulated)
speed_percentage_error = speed_error / speed_actual * 100
print(f"Actual max speed: {speed_actual:.2f} m/s2")
print(f"Simulated max speed: {speed_simulated:.2f} m/s2")
print(f"Error: {speed_error:.2f} m/s2")
print(f"Percentage Error: {speed_percentage_error:.2f}%")
Function.compare_plots(
[
(flight_reanalysis.vz.crop([(0, 100)]), "RocketPy"),
(cats_vega_flight.speed.crop([(0, 100)]), "CATS Vega"),
],
title="Speed Comparison",
xlabel="Time (s)",
ylabel="Speed (m/s)",
)
Actual max speed: 302.54 m/s2
Simulated max speed: 365.66 m/s2
Error: 63.12 m/s2
Percentage Error: 20.86%
