Juno III - Projeto Jupiter 2023¶
Launched at Spaceport America Cup 2023 edition. Projeto Jupiter is a rocket design team from the University of São Paulo, Brazil. Permission to use flight data given by Juliana Carloni, 2023.
These results were extracted out of the flight card:
- Team number:
138 - Launch date:
June 23rd, 2023. around 17hrs local time - Last simulated apogee before flight:
3026.054 m - Official recorded apogee:
3213 m
If we divided the simulation error (3213 - 3026.054) and divide by the actual
apogee, we have a relative error of 8.08%
In [3]:
%load_ext autoreload
%autoreload 2
The autoreload extension is already loaded. To reload it, use: %reload_ext autoreload
In [4]:
from rocketpy import Function, Rocket, SolidMotor, Flight, Environment
from rocketpy.simulation.flight_data_importer import FlightDataImporter
import matplotlib.pyplot as plt
plt.style.use("seaborn-v0_8-colorblind")
In [5]:
env = Environment(
latitude=32.939377,
longitude=-106.911986,
elevation=1480,
)
In [6]:
env.set_date(date=(2023, 6, 23, 17), timezone="America/Denver")
env.set_atmospheric_model(
type="Reanalysis",
file="../../data/weather/spaceport_america_pressure_levels_2023_hourly.nc",
dictionary="ECMWF",
)
env.max_expected_height = 6000
In [7]:
env.info()
Gravity Details Acceleration of gravity at surface level: 9.7910 m/s² Acceleration of gravity at 6.000 km (ASL): 9.7771 m/s² Launch Site Details Launch Date: 2023-06-23 23:00:00 UTC | 2023-06-23 17:00:00 America/Denver Launch Site Latitude: 32.93938° Launch Site Longitude: -106.91199° Reference Datum: SIRGAS2000 Launch Site UTM coordinates: 321254.52 W 3646188.36 N Launch Site UTM zone: 13S Launch Site Surface Elevation: 1480.0 m Atmospheric Model Details Atmospheric Model Type: Reanalysis Reanalysis Maximum Height: 6.000 km Reanalysis Time Period: From 2023-06-19 00:00:00 to 2023-06-24 23:00:00 UTC Reanalysis Hour Interval: 1 hrs Reanalysis Latitude Range: From 36.75 ° To 29.0 ° Reanalysis Longitude Range: From -108.87999725341797 ° To -105.12999725341797 ° Surface Atmospheric Conditions Surface Wind Speed: 10.77 m/s Surface Wind Direction: 244.23° Surface Wind Heading: 64.23° Surface Pressure: 849.92 hPa Surface Temperature: 306.95 K Surface Air Density: 0.965 kg/m³ Surface Speed of Sound: 351.22 m/s Earth Model Details Earth Radius at Launch site: 6371.85 km Semi-major Axis: 6378.14 km Semi-minor Axis: 6356.75 km Flattening: 0.0034 Atmospheric Model Plots
In [8]:
mandioca = SolidMotor(
thrust_source="../../data/motors/mandioca/thrustCurve.csv",
reshape_thrust_curve=(5.8, 8800),
grain_number=5,
grain_separation=0.006,
grain_outer_radius=0.0465,
grain_initial_inner_radius=0.016,
grain_initial_height=0.156,
grain_density=1748.9,
nozzle_radius=0.0335,
throat_radius=0.0114,
interpolation_method="linear",
dry_mass=0.00000000001,
grains_center_of_mass_position=-0.683,
center_of_dry_mass_position=-0.683,
dry_inertia=(0.0000000000001, 0.0000000000001, 0.0000000000001),
nozzle_position=-1.294,
)
mandioca.draw()
In [9]:
mandioca.info()
Nozzle Details Nozzle Radius: 0.0335 m Nozzle Throat Radius: 0.0114 m Grain Details Number of Grains: 5 Grain Spacing: 0.006 m Grain Density: 1748.9 kg/m3 Grain Outer Radius: 0.0465 m Grain Inner Radius: 0.016 m Grain Height: 0.156 m Grain Volume: 0.001 m3 Grain Mass: 1.634 kg Motor Details Total Burning Time: 5.8 s Total Propellant Mass: 8.169 kg Average Propellant Exhaust Velocity: 1077.193 m/s Average Thrust: 1517.241 N Maximum Thrust: 2472.691294388508 N at 3.26701244813278 s after ignition. Total Impulse: 8800.000 Ns
In [10]:
# this drag curve comes from RASAero II
drag_curve = "../../data/juno3/drag_curve.csv"
juno = Rocket(
radius=0.0655,
mass=24.05,
inertia=(15.07, 15.07, 0.067),
power_off_drag=drag_curve,
power_on_drag=drag_curve,
center_of_mass_without_motor=0,
coordinate_system_orientation="tail_to_nose",
)
juno.add_motor(mandioca, 0)
In [11]:
juno.add_nose(
length=0.565,
kind="vonKarman",
position=1.477,
).draw()
In [12]:
juno.add_trapezoidal_fins(
n=4,
root_chord=0.20,
tip_chord=0.12,
span=0.130,
position=-0.928,
cant_angle=0,
airfoil=(Function([[0, 0.0002], [2, 0.3320], [4, 0.6335], [6, 0.6877]]), "degrees"),
).draw()
In [13]:
tail = juno.add_tail(
top_radius=0.0655, bottom_radius=0.0535, length=0.068, position=-1.226
)
In [14]:
rail_buttons = juno.set_rail_buttons(
upper_button_position=0.24,
lower_button_position=-1.17,
angular_position=45,
)
In [15]:
drogue = juno.add_parachute(
"Drogue",
cd_s=0.885,
trigger="apogee",
sampling_rate=105,
noise=(0, 8.3, 0.5),
lag=0.5,
)
In [16]:
factor = 0.38 / juno.power_off_drag(0.6) # From CFD analysis
juno.power_on_drag *= factor
juno.power_off_drag *= factor
In [17]:
juno.info()
juno.draw()
Inertia Details Rocket Mass: 24.050 kg (without motor) Rocket Dry Mass: 24.050 kg (with unloaded motor) Rocket Loaded Mass: 32.219 kg (with loaded motor) Rocket Inertia (with unloaded motor) 11: 15.070 kg*m2 Rocket Inertia (with unloaded motor) 22: 15.070 kg*m2 Rocket Inertia (with unloaded motor) 33: 0.067 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: 0.0655 m Rocket Frontal Area: 0.013478 m2 Rocket Distances Rocket Center of Dry Mass - Center of Mass without Motor: 0.000 m Rocket Center of Dry Mass - Nozzle Exit: 1.294 m Rocket Center of Dry Mass - Center of Propellant Mass: 0.683 m Rocket Center of Mass - Rocket Loaded Center of Mass: 0.173 m Aerodynamics Lift Coefficient Derivatives Nose Cone Lift Coefficient Derivative: 2.000/rad Fins Lift Coefficient Derivative: 9.797/rad Tail Lift Coefficient Derivative: -0.666/rad Center of Pressure Nose Cone Center of Pressure position: 1.195 m Fins Center of Pressure position: -1.006 m Tail Center of Pressure position: -1.259 m Stability Center of Mass position (time=0): -0.173 m Initial Static Margin (mach=0, time=0): 3.221 c Final Static Margin (mach=0, time=burn_out): 4.543 c Rocket Center of Mass (time=0) - Center of Pressure (mach=0): 0.422 m Parachute Details Parachute Drogue with a cd_s of 0.8850 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: 0.5 s
In [18]:
test_flight = Flight(
rocket=juno,
environment=env,
inclination=85,
heading=105,
rtol=1e-6,
atol=1e-6,
max_time=600,
rail_length=5.2,
)
In [19]:
test_flight.prints.out_of_rail_conditions()
test_flight.prints.burn_out_conditions()
test_flight.prints.apogee_conditions()
test_flight.prints.impact_conditions()
test_flight.plots.trajectory_3d()
Rail Departure State Rail Departure Time: 0.892 s Rail Departure Velocity: 15.692 m/s Rail Departure Stability Margin: 3.305 c Rail Departure Angle of Attack: 35.750° Rail Departure Thrust-Weight Ratio: 5.212 Rail Departure Reynolds Number: 1.241e+05 Burn out State Burn out time: 5.800 s Altitude at burn out: 750.976 m (AGL) Rocket velocity at burn out: 243.882 m/s Freestream velocity at burn out: 247.849 m/s Mach Number at burn out: 0.714 Kinetic energy at burn out: 7.152e+05 J Apogee State Apogee Altitude: 4485.553 m (ASL) | 3005.553 m (AGL) Apogee Time: 26.463 s Apogee Freestream Speed: 60.736 m/s Impact Conditions X Impact: 608.608 m Y Impact: -148.294 m Latitude: 32.9380434° Longitude: -106.9054652° Time of Impact: 150.181 s Velocity at Impact: -23.531 m/s
In [32]:
columns_map = {
"time": "time",
"altitude": "altitude",
"velocity": "vz",
}
cots_altimeter_flight = FlightDataImporter(
name="COTS Altimeter Flight",
paths="../../data/juno3/cots_altimeter.csv",
columns_map=columns_map,
units=None,
interpolation="linear",
extrapolation="zero",
separator=",",
encoding="utf-8",
)
The following attributes were create and are now available to be used: ['time', 'altitude', 'vz', 'static_pressure']
In [37]:
Function.compare_plots(
[
(test_flight.altitude, "RocketPy"),
(cots_altimeter_flight.altitude, "COTS Altimeter"),
],
title="Altitude Comparison",
xlabel="Time (s)",
ylabel="Altitude (m)",
lower=0,
upper=30,
)
Function.compare_plots(
[
(test_flight.vz, "RocketPy"),
(cots_altimeter_flight.vz, "COTS Altimeter"),
],
title="Vertical Velocity Comparison",
xlabel="Time (s)",
ylabel="Velocity (m/s)",
lower=0,
upper=30,
)
In [58]:
columns_map = {
"ALT": "z",
"VERTV": "vz",
"LAT": "latitude",
"LON": "longitude",
}
units = {
"ALT": "ft",
"VERTV": "ft/s",
}
cots_gnss_flight = FlightDataImporter(
name="COTS GNSS Flight",
paths="../../data/juno3/cots_GNSS.csv",
columns_map=columns_map,
units=units,
interpolation="linear",
extrapolation="zero",
separator=",",
encoding="utf-8",
)
Attribute 'z' converted from ft to SI Attribute 'vz' converted from ft/s to SI The following attributes were create and are now available to be used: ['z', 'vz', 'latitude', 'longitude']
In [59]:
Function.compare_plots(
[(test_flight.latitude, "RocketPy"), (cots_gnss_flight.latitude, "Actual - GNSS")],
title="Latitude Comparison",
xlabel="Time (s)",
ylabel="Latitude (deg)",
)
Function.compare_plots(
[
(test_flight.longitude, "RocketPy"),
(cots_gnss_flight.longitude, "Actual - GNSS"),
],
title="Longitude Comparison",
xlabel="Time (s)",
ylabel="Longitude (deg)",
)
Function.compare_plots(
[(test_flight.z, "RocketPy"), (cots_gnss_flight.z, "Actual - GNSS")],
title="Altitude ASL Comparison",
xlabel="Time (s)",
ylabel="Altitude ASL (m)",
)
