example.py

import campyros as pyro
import csv
import time
import numpy as np
import pandas as pd

"""Import motor data to use for the mass model"""
motor_csv = pd.read_csv("novus_sim_6.1/motor_out.csv")
time_array = motor_csv["Time"]
smass_array = motor_csv["Solid Fuel Mass (kg)"]
S_DEN = motor_csv["Solid Fuel Density (kg/m^3)"][0]
S_L = motor_csv["Solid Fuel Length (m)"][0]
S_ROUT = motor_csv["Solid Fuel Outer Diameter (m)"][0]
vmass_array = motor_csv["Vapour Mass (kg)"]
vden_array = motor_csv["Vapour Density (kg/m^3)"]
lmass_array = motor_csv["Liquid Mass (kg)"]
lden_array = motor_csv["Liquid Density (kg/m^3)"]

"""Rocket parameters"""
DRY_MASS = 60  # Rocket dry mass (kg)
ROCKET_L = 6.529  # Rocket length (m)
ROCKET_R = 98.5e-3  # Rocket radius (m)
ROCKET_T = 1e-2  # Rocket wall thickness (m) - used when approximating the rocket airframe as a thin walled cylinder
POS_TANK_BOTTOM = (
    4.456  # Distance between the nose tip and the bottom of the nitrous tank (m)
)
POS_SOLIDFUEL_BOTTOM = (
    4.856 + S_L
)  # Distance between the nose tip and bottom of the solid fuel grain (m)
REF_AREA = 0.0305128422  # Reference area for aerodynamic coefficients (m^2)

"""Set up aerodynamic properties"""
# Get approximate values for the rotational damping coefficients
C_DAMP_PITCH = pyro.pitch_damping_coefficient(
    ROCKET_L, ROCKET_R, fin_number=4, area_per_fin=0.07369928
)
C_DAMP_ROLL = 0

# Import drag coefficients from RASAero II
aero_data = pyro.AeroData.from_rasaero(
    "data/Martlet4RasAeroII.CSV", REF_AREA, C_DAMP_PITCH, C_DAMP_ROLL
)
# aero_data.show_plot()   #Show plots of how the program interpreted the data, so you can visually check if it's correct

"""Set up the mass model"""
mass_model = pyro.MassModel()
mass_model.add_hollowcylinder(
    DRY_MASS, ROCKET_R, ROCKET_R - ROCKET_T, ROCKET_L, ROCKET_L / 2
)
mass_model.add_liquidtank(
    lmass_array,
    lden_array,
    time_array,
    ROCKET_R,
    POS_TANK_BOTTOM,
    vmass_array,
    vden_array,
)
mass_model.add_solidfuel(
    smass_array, time_array, S_DEN, S_ROUT, S_L, POS_SOLIDFUEL_BOTTOM
)

"""Create the other objects needed to initialise the Rocket object"""
pulsar = pyro.Motor.from_novus("novus_sim_6.1/motor_out.csv", pos=ROCKET_L)

launch_site = pyro.LaunchSite(
    rail_length=5,
    rail_yaw=0,
    rail_pitch=0,
    alt=10,
    longi=0.1,
    lat=52.1,
    variable_wind=True,
    cache_Wind=True
) 

parachute_Data = pd.read_csv("data/Sample_Parachute_Cd.csv")
mach_array = parachute_Data["Mach_Number"].to_numpy()
main_cd_array = parachute_Data["Main_Cd"].to_numpy()
dro_cd_array = parachute_Data["Drogue_Cd"].to_numpy()

parachute = pyro.Parachute(
    main_s=13.9,
    drogue_s=1.13,
    main_c_d=(mach_array, main_cd_array),
    drogue_c_d=(mach_array, dro_cd_array),
    main_alt=1000,
    attach_distance=0,
)
"""
parachute = pyro.Parachute(
    main_s=13.9,
    drogue_s=1.13,
    main_cd=0.78,
    dro_cd=0.78,
    main_alt=1000,
    attach_distance=0,
)"""

"""Create the Rocket object"""
martlet4 = pyro.Rocket(
    mass_model,
    pulsar,
    aero_data,
    launch_site,
    h=0.05,
    variable=True,
    alt_poll_interval=1,
    parachute=parachute,
)

"""Run the simulation"""
t = time.time()
simulation_output = martlet4.run(debug=True, to_json="data/pyro.json")
print(f"Simulation run time: {time.time()-t:.2f} s")

"""Example of how you can import data from a .csv file"""
imported_data = pyro.from_json("data/trajectory.json")

"""Plot the results"""
pyro.plot_launch_trajectory_3d(
    imported_data, martlet4, show_orientation=False
)  # Could have also used simulation_output instead of imported_data
pyro.plot_altitude_time(imported_data, martlet4)
pyro.plot_ypr(imported_data, martlet4)
# pyro.animate_orientation(imported_data)