Astra - Faraday Rocketry UPV - 2022¶

Launched at EUROC'22. Achieved an apogee close to the target 3000m, however had a balistic descent. Permission to use flight data given by Nacho Coello, 2024.

These results were extracted out of the flight card:

Team number: 13
Launch date: October 13th, 2022. 16hrs local time
Simulated apogee: 3043.07 m
Official recorded apogee: 3250 m

The relative error of altitude apogee is only 6.37%!

In [2]:

%load_ext autoreload
%autoreload 2

In [ ]:

import matplotlib.pyplot as plt

from rocketpy import Environment, Flight, Function, Rocket, SolidMotor

plt.style.use("seaborn-v0_8-colorblind")

Environment registered by windy¶

In [4]:

env = Environment(
    gravity=9.80665,
    date=(2022, 10, 13, 16),
    latitude=39.3897,
    longitude=-8.2889639,
    elevation=160,
    datum="WGS84",
    timezone="Portugal",
)

env.set_atmospheric_model(
    type="Reanalysis",
    file="../../data/weather/euroc_2022_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: 2022-10-13 15:00:00 UTC | 2022-10-13 16:00:00 Portugal
Launch Site Latitude: 39.38970°
Launch Site Longitude: -8.28896°
Reference Datum: WGS84
Launch Site UTM coordinates: 44415.44 W    4373388.30 N
Launch Site UTM zone: 30S
Launch Site Surface Elevation: 160.0 m


Atmospheric Model Details

Atmospheric Model Type: Reanalysis
Reanalysis Maximum Height: 4.000 km
Reanalysis Time Period: from 2022-10-13 10:00:00 to 2022-10-17 17:00:00 utc
Reanalysis Hour Interval: 2 hrs
Reanalysis Latitude Range: From 40.0° to 39.0°
Reanalysis Longitude Range: From -9.0° to -8.0°

Surface Atmospheric Conditions

Surface Wind Speed: 3.43 m/s
Surface Wind Direction: 316.09°
Surface Wind Heading: 136.09°
Surface Pressure: 1000.00 hPa
Surface Temperature: 298.96 K
Surface Air Density: 1.165 kg/m³
Surface Speed of Sound: 346.62 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 [16]:

Motor = SolidMotor(
    thrust_source="../../data/motors/cesaroni/Cesaroni_4263L1350-P.eng",
    burn_time=3.284,
    grain_number=1,
    grain_density=1256.7753406541794,
    grain_initial_inner_radius=0.01875,
    grain_outer_radius=0.0375,
    grain_initial_height=0.486,
    nozzle_radius=0.028125,
    nozzle_position=0,
    throat_radius=0.01875,
    grain_separation=0,
    grains_center_of_mass_position=0.243,
    dry_inertia=(0, 0, 0),
    center_of_dry_mass_position=0,
    dry_mass=0,
)

In [17]:

Motor.info()
Motor.draw()

Nozzle Details
Nozzle Radius: 0.028125 m
Nozzle Throat Radius: 0.01875 m

Grain Details
Number of Grains: 1
Grain Spacing: 0 m
Grain Density: 1256.7753406541794 kg/m3
Grain Outer Radius: 0.0375 m
Grain Inner Radius: 0.01875 m
Grain Height: 0.486 m
Grain Volume: 0.002 m3
Grain Mass: 2.024 kg

Motor Details
Total Burning Time: 3.284 s
Total Propellant Mass: 2.024 kg
Structural Mass Ratio: 0.000
Average Propellant Exhaust Velocity: 2114.916 m/s
Average Thrust: 1303.340 N
Maximum Thrust: 1540.732 N at 1.28 s after ignition.
Total Impulse: 4280.167 Ns

Rocket and Aerodynamic surfaces¶

In [18]:

Astra = Rocket(
    radius=0.047,
    mass=10.6462,
    inertia=(6.6986, 6.6986, 0.040824),
    center_of_mass_without_motor=1.3957,
    power_off_drag="../../data/rockets/astra/drag_coefficient.csv",
    power_on_drag="../../data/rockets/astra/drag_coefficient.csv",
    coordinate_system_orientation="tail_to_nose",
)

Astra.set_rail_buttons(1.5957, 1.1957)

Astra.add_motor(Motor, position=0.7146163949)

In [19]:

NoseCone = Astra.add_nose(
    length=0.27,
    kind="vonKarman",
    position=2.5214,
)

FinSet = Astra.add_trapezoidal_fins(
    n=4,
    span=0.117,
    root_chord=0.2,
    tip_chord=0.118,
    position=0.9134,
)

In [20]:

Astra.draw()

Flight Simulation DATA¶

In [21]:

test_flight = Flight(
    rocket=Astra, environment=env, inclination=84, heading=133, rail_length=12
)

In [22]:

test_flight.prints.apogee_conditions()
test_flight.plots.trajectory_3d()

Apogee State

Apogee Time: 24.007 s
Apogee Altitude: 3203.066 m (ASL) | 3043.066 m (AGL)
Apogee Freestream Speed: 12.046 m/s
Apogee X position: 279.694 m
Apogee Y position: -262.193 m
Apogee latitude: 39.3873415°
Apogee longitude: -8.2857086°

Data analysis¶

In [12]:

from rocketpy.simulation.flight_data_importer import FlightDataImporter

columns_map = {"t": "time", "alt": "altitude"}

telemetry_data = FlightDataImporter(
    name="COTS Altimeter Flight",
    paths="../../data/rockets/astra/flight_data.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']

In [13]:

Function.compare_plots(
    [
        (test_flight.altitude, "RocketPy"),
        (telemetry_data.altitude, "Telemetry"),
    ],
    title="Altitude Comparison",
    xlabel="Time (s)",
    ylabel="Altitude (m)",
)