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rocket_casadi_result.py
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rocket_casadi_result.py
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'''
Based on:
Gravity Turn Maneuver with direct multiple shooting using CVodes
(c) Mirko Hahn
https://mintoc.de/index.php/Gravity_Turn_Maneuver_(Casadi)
https://github.com/zegkljan/kos-stuff/tree/master/non-kos-tools/gturn
----------------------------------------------------------------
'''
import sys
from pathlib import Path
import pandas as pd
import matplotlib.pyplot as plt
from rocket_input import read_rocket_config
rad_degrees = 180.0 / 3.141592653589793
def plot(result_df, rocket, display):
FIGSIZE = (6, 8)
fig, axes = plt.subplots(nrows=3, ncols=2, figsize=FIGSIZE)
ax_vel, ax_beta = axes[0]
ax_alt, ax_theta = axes[1]
ax_throttle, ax_mass = axes[2]
time_series = result_df['time'].to_numpy()
vel_series = result_df['vel'].to_numpy()
ax_vel.set_xlim(0, display.flight_duration)
ax_vel.set_ylim(display.vel_min_max[0], display.vel_min_max[1])
vel_plot, = ax_vel.plot(time_series, vel_series, color='black', linewidth=1)
beta_series = result_df['ver_angle'].to_numpy() * rad_degrees
ax_beta.set_xlim(0, display.flight_duration)
ax_beta.set_ylim(display.beta_min_max[0], display.beta_min_max[1])
beta_plot, = ax_beta.plot(time_series, beta_series, color='black', linewidth=1)
alt_series = result_df['alt'].to_numpy()
ax_alt.set_xlim(0, display.flight_duration)
ax_alt.set_ylim(0, display.alt_min_max[1])
alt_plot, = ax_alt.plot(time_series, alt_series, color='black', linewidth=1)
theta_series = result_df['hor_angle'].to_numpy() * rad_degrees
ax_theta.set_xlim(0, display.flight_duration)
ax_theta.set_ylim(display.theta_min_max[0], display.theta_min_max[1])
theta_plot, = ax_theta.plot(time_series, theta_series, color='black', linewidth=1)
# ax_acc.set_xlim(0, display.flight_duration)
# ax_acc.set_ylim(display.acc_min_max[0], display.acc_min_max[1])
# acc_plot, = ax_acc.plot([0], [0], color='black', linewidth=1)
mass_series = result_df['mass'].to_numpy()
ax_mass.set_xlim(0, display.flight_duration)
ax_mass.set_ylim(0, rocket.dry_mass + rocket.fuel_mass)
mass_plot, = ax_mass.plot(time_series, mass_series, color='red', linewidth=3)
throttle_series = result_df['control'].to_numpy()
ax_throttle.set_xlim(0, display.flight_duration)
ax_throttle.set_ylim(0, 1.2)
throttle_plot, = ax_throttle.plot(time_series, throttle_series, color='red', linewidth=3)
plt.show()
def main(config_file_name):
rocket_params, _, model_params, display_params = read_rocket_config(config_file_name)
result_df = pd.read_excel(model_params.model_file)
plot(result_df, rocket_params, display_params)
if __name__ == '__main__':
config_file_name = 'None'
if len(sys.argv) == 2:
config_file_name = sys.argv[1]
config_file_name = Path(config_file_name)
if not config_file_name.is_file():
print(f'incorrect config file: {config_file_name}')
exit()
main(config_file_name)