Halcyon - Aerospace Team Graz - 2023¶
Launched at EuRoC'23, allowing the team to become the Overall Champions. Permission to use flight data given by Dorothea Krasser, 2024.
These results were extracted out of the flight card:
- Team number:
1 - Launch date:
October 13th, 2023. around 14hrs local time - Last simulated apogee before flight:
3163 m(this value differs from the simulation shown below because of the updates to rocketpy software) - Official recorded apogee:
3450 m
The relative error of altitude apogee is only 9.1%
In [93]:
%load_ext autoreload
%autoreload 2
The autoreload extension is already loaded. To reload it, use: %reload_ext autoreload
In [94]:
from rocketpy import Function, Environment, Flight, Rocket
from rocketpy.motors import CylindricalTank, Fluid, HybridMotor
from rocketpy.motors.tank import MassFlowRateBasedTank
import datetime
import matplotlib.pyplot as plt
plt.style.use("seaborn-v0_8-colorblind")
In [4]:
tomorrow = datetime.date(2023, 10, 13) + datetime.timedelta(days=1)
Env = Environment(
latitude=39.388692,
longitude=-8.287814,
elevation=130,
)
The team preferred to set a custom atmospheric model. However, for better resolution, this examples will only run the windy atmosphere that was registered in windy.
In [5]:
Env.set_date((tomorrow.year, tomorrow.month, tomorrow.day, 12))
Env.set_atmospheric_model(
type="custom_atmosphere",
pressure=None,
temperature=300,
wind_u=[(0, 8), (1000, 10)],
wind_v=[(0, 0), (500, 0), (1600, 0)],
)
In [6]:
Env.info()
Gravity Details Acceleration of gravity at surface level: 9.8008 m/s² Acceleration of gravity at 1.000 km (ASL): 9.7981 m/s² Launch Site Details Launch Date: 2023-10-14 12:00:00 UTC Launch Site Latitude: 39.38869° Launch Site Longitude: -8.28781° Reference Datum: SIRGAS2000 Launch Site UTM coordinates: 44507.97 W 4373270.52 N Launch Site UTM zone: 30S Launch Site Surface Elevation: 130.0 m Atmospheric Model Details Atmospheric Model Type: custom_atmosphere custom_atmosphere Maximum Height: 1.000 km Surface Atmospheric Conditions Surface Wind Speed: 8.29 m/s Surface Wind Direction: 270.00° Surface Wind Heading: 90.00° Surface Pressure: 997.99 hPa Surface Temperature: 300.00 K Surface Air Density: 1.159 kg/m³ Surface Speed of Sound: 347.22 m/s Earth Model Details Earth Radius at Launch site: 6369.57 km Semi-major Axis: 6378.14 km Semi-minor Axis: 6356.75 km Flattening: 0.0034 Atmospheric Model Plots
Environment¶
In [95]:
env = Environment(
gravity=9.80665,
date=(2023, 10, 13, 14),
latitude=39.388692,
longitude=-8.287814,
elevation=130,
datum="WGS84",
timezone="Portugal",
)
# env.set_atmospheric_model(type="Windy", file="ECMWF")
# env.max_expected_height = 4000
# env.info()
env.set_atmospheric_model(
type="Reanalysis",
file="../../data/weather/euroc_2023_all_windows.nc",
dictionary="ECMWF",
)
env.max_expected_height = 4000
env.info()
Gravity Details Acceleration of gravity at surface level: 9.8066 m/s² Acceleration of gravity at 4.000 km (ASL): 9.8066 m/s² Launch Site Details Launch Date: 2023-10-13 13:00:00 UTC | 2023-10-13 14:00:00 Portugal Launch Site Latitude: 39.38869° Launch Site Longitude: -8.28781° Reference Datum: WGS84 Launch Site UTM coordinates: 44507.97 W 4373270.52 N Launch Site UTM zone: 30S Launch Site Surface Elevation: 130.0 m Atmospheric Model Details Atmospheric Model Type: Reanalysis Reanalysis Maximum Height: 4.000 km Reanalysis Time Period: from 2023-10-12 08:00:00 to 2023-10-15 18:00:00 utc Reanalysis Hour Interval: 1 hrs Reanalysis Latitude Range: From 40.0° to 39.0° Reanalysis Longitude Range: From -9.0° to -7.0° Surface Atmospheric Conditions Surface Wind Speed: 160.86 m/s Surface Wind Direction: 340.86° Surface Wind Heading: 3.80° Surface Pressure: 1000.00 hPa Surface Temperature: 296.79 K Surface Air Density: 1.174 kg/m³ Surface Speed of Sound: 345.36 m/s Earth Model Details Earth Radius at Launch site: 6369.57 km Semi-major Axis: 6378.14 km Semi-minor Axis: 6356.75 km Flattening: 0.0034 Atmospheric Model Plots
Motor¶
In [96]:
oxidizer_liq = Fluid(name="N2O_l", density=960)
oxidizer_gas = Fluid(name="N2O_g", density=1.9277)
tank_shape = CylindricalTank(70 / 1000, 320 / 1000)
oxidizer_tank = MassFlowRateBasedTank(
name="oxidizer_tank",
geometry=tank_shape,
flux_time=(5),
initial_liquid_mass=4.2,
initial_gas_mass=0,
liquid_mass_flow_rate_in=0,
liquid_mass_flow_rate_out=4.2 / 5,
gas_mass_flow_rate_in=0,
gas_mass_flow_rate_out=0,
liquid=oxidizer_liq,
gas=oxidizer_gas,
)
hybrid_motor = HybridMotor(
thrust_source="../../data/astg/engine_Halcyon_4thHotfire.eng",
dry_mass=10670 / 1000,
dry_inertia=(1.668, 1.668, 0.026),
center_of_dry_mass_position=780 / 1000,
burn_time=5,
reshape_thrust_curve=False,
grain_number=1,
grain_separation=0,
grain_outer_radius=43 / 1000,
grain_initial_inner_radius=22.5 / 1000,
grain_initial_height=310 / 1000,
grain_density=920,
nozzle_radius=0.0141,
throat_radius=0.00677,
interpolation_method="linear",
grains_center_of_mass_position=385 / 1000,
coordinate_system_orientation="nozzle_to_combustion_chamber",
)
hybrid_motor.add_tank(tank=oxidizer_tank, position=934.75 / 1000)
In [97]:
hybrid_motor.info()
Nozzle Details Outlet Radius: 0.0141 m Throat Radius: 0.00677 m Outlet Area: 0.000625 m² Throat Area: 0.000144 m² Position: 0 m Grain Details Number of Grains: 1 Grain Spacing: 0 m Grain Density: 920 kg/m3 Grain Outer Radius: 0.043 m Grain Inner Radius: 0.0225 m Grain Height: 0.31 m Grain Volume: 0.001 m3 Grain Mass: 1.203 kg Motor Details Total Burning Time: 5 s Total Propellant Mass: 5.403 kg Average Propellant Exhaust Velocity: 1805.600 m/s Average Thrust: 1951.160 N Maximum Thrust: 2127.473 N at 0.2503 s after ignition. Total Impulse: 9755.800 Ns
Rocket and Aerodynamic surfaces¶
In [98]:
HALCYON = Rocket(
radius=152.4 / 2000,
mass=14613 / 1000,
inertia=(24.56, 24.56, 70.074),
center_of_mass_without_motor=2344 / 1000,
power_off_drag="../../data/astg/DragCoeffOR_off.csv",
power_on_drag="../../data/astg/DragCoeffOR_on.csv",
coordinate_system_orientation="tail_to_nose",
)
HALCYON.set_rail_buttons(2.808, 1.549)
HALCYON.add_motor(hybrid_motor, position=20 / 1000)
In [99]:
NoseCone = HALCYON.add_nose(length=0.46, kind="vonKarman", position=3556 / 1000)
FinSet = HALCYON.add_trapezoidal_fins(
n=4,
span=0.125,
root_chord=0.247,
tip_chord=0.045,
position=0.263,
)
Tail = HALCYON.add_tail(
top_radius=152.4 / 2000, bottom_radius=0.0496, length=0.254, position=0.254
)
In [100]:
Main = HALCYON.add_parachute(
name="Main",
cd_s=9.621,
trigger="apogee",
sampling_rate=100,
lag=5,
)
Flight Simulation Data¶
In [101]:
test_flight = Flight(
rocket=HALCYON, environment=env, inclination=85, heading=90, rail_length=12
)
In [102]:
test_flight.prints.apogee_conditions()
test_flight.plots.trajectory_3d()
Apogee State Apogee Time: 26.363 s Apogee Altitude: 3342.775 m (ASL) | 3212.775 m (AGL) Apogee Freestream Speed: 19.912 m/s Apogee X position: 768.210 m Apogee Y position: -349.074 m Apogee latitude: 39.3855517° Apogee longitude: -8.2788733°
Data analysis¶
In [103]:
from rocketpy.simulation.flight_data_importer import FlightDataImporter
columns_map = {
"ts": "time",
"filtered_altitude_AGL": "altitude",
"filtered_acceleration": "az",
}
cots_altimeter_flight = FlightDataImporter(
name="COTS Altimeter Flight",
paths="../../data/astg/altimeter_halcyon.csv",
columns_map=columns_map,
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']
In [104]:
Function.compare_plots(
[
(test_flight.altitude, "RocketPy"),
(cots_altimeter_flight.altitude, "COTS Altimeter"),
],
title="Altitude Comparison",
xlabel="Time (s)",
ylabel="Altitude (m)",
)
In [73]:
columns_map = {
"ts": "time",
"latitude": "latitude",
"longitude": "longitude",
}
cots_gnss_flight = FlightDataImporter(
name="COTS GNSS Flight",
paths="../../data/astg/gnss_halcyon.csv",
columns_map=columns_map,
interpolation="linear",
extrapolation="zero",
delimiter=",",
encoding="utf-8",
)
The following attributes were create and are now available to be used: ['time', 'latitude', 'longitude']
In [74]:
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)",
)
