Utilities module usage¶

[1]:

from rocketpy.utilities import *

[ ]:

%matplotlib notebook

1. Estimations for your CdS¶

[2]:

compute_CdS_from_drop_test(
    terminal_velocity=10,  # The desired terminal velocity (m/s)
    rocket_mass=20,  # kg
    air_density=1.225,
    g=9.80665,
)

[2]:

3.202171428571428

2. Altitude of Terminal Velocity being reached¶

[3]:

a, b, c = calculateEquilibriumAltitude(
    rocket_mass=20,
    CdS=5,
    z0=1000,
    v0=-20,
    env=None,
    eps=1e-3,
    max_step=0.1,
    seeGraphs=True,
    g=9.80665,
    estimated_final_time=10,
)

altitudeFunction, velocityFunction, final_sol = a, b, c

../_images/notebooks_utilities_usage_6_0.png

../_images/notebooks_utilities_usage_6_1.png

[4]:

final_sol

[4]:

{'time': 3.017253750404491,
 'altitude': 972.1969610464328,
 'velocity': -8.007887255820947}

[12]:

print(
    f"The terminal velocity of {final_sol['velocity']:.3} m/s is reached after {final_sol['time']:.3} seconds at altitude of {final_sol['altitude']:.6} meters."
)

The terminal velocity of -8.01 m/s is reached after 3.02 seconds at altitude of 972.197 meters.

Topography with RocketPy MATLAB® Tutorial