import matplotlib.pyplot as plt
import numpy as np
try:
from functools import cached_property
except ImportError:
from ..tools import cached_property
[docs]
class _FlightPlots:
"""Class that holds plot methods for Flight class.
Attributes
----------
_FlightPlots.flight : Flight
Flight object that will be used for the plots.
_FlightPlots.first_event_time : float
Time of first event.
_FlightPlots.first_event_time_index : int
Time index of first event.
"""
[docs]
def __init__(self, flight):
"""Initializes _FlightPlots class.
Parameters
----------
flight : Flight
Instance of the Flight class
Returns
-------
None
"""
self.flight = flight
return None
@cached_property
def first_event_time(self):
"""Time of the first flight event."""
if len(self.flight.parachute_events) > 0:
return (
self.flight.parachute_events[0][0]
+ self.flight.parachute_events[0][1].lag
)
else:
return self.flight.t_final
@cached_property
def first_event_time_index(self):
"""Time index of the first flight event."""
if len(self.flight.parachute_events) > 0:
return np.nonzero(self.flight.x[:, 0] == self.first_event_time)[0][0]
else:
return -1
[docs]
def trajectory_3d(self):
"""Plot a 3D graph of the trajectory
Returns
-------
None
"""
max_z = max(self.flight.altitude[:, 1])
min_z = min(self.flight.altitude[:, 1])
max_x = max(self.flight.x[:, 1])
min_x = min(self.flight.x[:, 1])
max_y = max(self.flight.y[:, 1])
min_y = min(self.flight.y[:, 1])
_ = plt.figure(figsize=(9, 9))
ax1 = plt.subplot(111, projection="3d")
ax1.plot(
self.flight.x[:, 1], self.flight.y[:, 1], zs=min_z, zdir="z", linestyle="--"
)
ax1.plot(
self.flight.x[:, 1],
self.flight.altitude[:, 1],
zs=min_y,
zdir="y",
linestyle="--",
)
ax1.plot(
self.flight.y[:, 1],
self.flight.altitude[:, 1],
zs=min_x,
zdir="x",
linestyle="--",
)
ax1.plot(
self.flight.x[:, 1],
self.flight.y[:, 1],
self.flight.altitude[:, 1],
linewidth="2",
)
ax1.scatter(
self.flight.x(0),
self.flight.y(0),
self.flight.z(0) - self.flight.env.elevation,
color="black",
)
ax1.scatter(
self.flight.x(self.flight.t_final),
self.flight.y(self.flight.t_final),
self.flight.z(self.flight.t_final) - self.flight.env.elevation,
color="red",
marker="X",
)
ax1.set_xlabel("X - East (m)")
ax1.set_ylabel("Y - North (m)")
ax1.set_zlabel("Z - Altitude Above Ground Level (m)")
ax1.set_title("Flight Trajectory")
ax1.set_xlim(min_x, max_x)
ax1.set_ylim(min_y, max_y)
ax1.set_zlim(min_z, max_z)
ax1.view_init(15, 45)
ax1.set_box_aspect(None, zoom=0.95) # 95% for label adjustment
plt.show()
[docs]
def linear_kinematics_data(self):
"""Prints out all Kinematics graphs available about the Flight
Returns
-------
None
"""
# Velocity and acceleration plots
fig2 = plt.figure(figsize=(9, 12))
ax1 = plt.subplot(414)
ax1.plot(self.flight.vx[:, 0], self.flight.vx[:, 1], color="#ff7f0e")
ax1.set_xlim(0, self.flight.t_final)
ax1.set_title("Velocity X | Acceleration X")
ax1.set_xlabel("Time (s)")
ax1.set_ylabel("Velocity X (m/s)", color="#ff7f0e")
ax1.tick_params("y", colors="#ff7f0e")
ax1.grid(True)
ax1up = ax1.twinx()
ax1up.plot(self.flight.ax[:, 0], self.flight.ax[:, 1], color="#1f77b4")
ax1up.set_ylabel("Acceleration X (m/s²)", color="#1f77b4")
ax1up.tick_params("y", colors="#1f77b4")
ax2 = plt.subplot(413)
ax2.plot(self.flight.vy[:, 0], self.flight.vy[:, 1], color="#ff7f0e")
ax2.set_xlim(0, self.flight.t_final)
ax2.set_title("Velocity Y | Acceleration Y")
ax2.set_xlabel("Time (s)")
ax2.set_ylabel("Velocity Y (m/s)", color="#ff7f0e")
ax2.tick_params("y", colors="#ff7f0e")
ax2.grid(True)
ax2up = ax2.twinx()
ax2up.plot(self.flight.ay[:, 0], self.flight.ay[:, 1], color="#1f77b4")
ax2up.set_ylabel("Acceleration Y (m/s²)", color="#1f77b4")
ax2up.tick_params("y", colors="#1f77b4")
ax3 = plt.subplot(412)
ax3.plot(self.flight.vz[:, 0], self.flight.vz[:, 1], color="#ff7f0e")
ax3.set_xlim(0, self.flight.t_final)
ax3.set_title("Velocity Z | Acceleration Z")
ax3.set_xlabel("Time (s)")
ax3.set_ylabel("Velocity Z (m/s)", color="#ff7f0e")
ax3.tick_params("y", colors="#ff7f0e")
ax3.grid(True)
ax3up = ax3.twinx()
ax3up.plot(self.flight.az[:, 0], self.flight.az[:, 1], color="#1f77b4")
ax3up.set_ylabel("Acceleration Z (m/s²)", color="#1f77b4")
ax3up.tick_params("y", colors="#1f77b4")
ax4 = plt.subplot(411)
ax4.plot(self.flight.speed[:, 0], self.flight.speed[:, 1], color="#ff7f0e")
ax4.set_xlim(0, self.flight.t_final)
ax4.set_title("Velocity Magnitude | Acceleration Magnitude")
ax4.set_xlabel("Time (s)")
ax4.set_ylabel("Velocity (m/s)", color="#ff7f0e")
ax4.tick_params("y", colors="#ff7f0e")
ax4.grid(True)
ax4up = ax4.twinx()
ax4up.plot(
self.flight.acceleration[:, 0],
self.flight.acceleration[:, 1],
color="#1f77b4",
)
ax4up.set_ylabel("Acceleration (m/s²)", color="#1f77b4")
ax4up.tick_params("y", colors="#1f77b4")
plt.subplots_adjust(hspace=0.5)
plt.show()
return None
[docs]
def attitude_data(self):
"""Prints out all Angular position graphs available about the Flight
Returns
-------
None
"""
# Angular position plots
fig3 = plt.figure(figsize=(9, 12))
ax1 = plt.subplot(411)
ax1.plot(self.flight.e0[:, 0], self.flight.e0[:, 1], label="$e_0$")
ax1.plot(self.flight.e1[:, 0], self.flight.e1[:, 1], label="$e_1$")
ax1.plot(self.flight.e2[:, 0], self.flight.e2[:, 1], label="$e_2$")
ax1.plot(self.flight.e3[:, 0], self.flight.e3[:, 1], label="$e_3$")
ax1.set_xlim(0, self.first_event_time)
ax1.set_xlabel("Time (s)")
ax1.set_ylabel("Euler Parameters")
ax1.set_title("Euler Parameters")
ax1.legend()
ax1.grid(True)
ax2 = plt.subplot(412)
ax2.plot(self.flight.psi[:, 0], self.flight.psi[:, 1])
ax2.set_xlim(0, self.first_event_time)
ax2.set_xlabel("Time (s)")
ax2.set_ylabel("ψ (°)")
ax2.set_title("Euler Precession Angle")
ax2.grid(True)
ax3 = plt.subplot(413)
ax3.plot(self.flight.theta[:, 0], self.flight.theta[:, 1], label="θ - Nutation")
ax3.set_xlim(0, self.first_event_time)
ax3.set_xlabel("Time (s)")
ax3.set_ylabel("θ (°)")
ax3.set_title("Euler Nutation Angle")
ax3.grid(True)
ax4 = plt.subplot(414)
ax4.plot(self.flight.phi[:, 0], self.flight.phi[:, 1], label="φ - Spin")
ax4.set_xlim(0, self.first_event_time)
ax4.set_xlabel("Time (s)")
ax4.set_ylabel("φ (°)")
ax4.set_title("Euler Spin Angle")
ax4.grid(True)
plt.subplots_adjust(hspace=0.5)
plt.show()
return None
[docs]
def flight_path_angle_data(self):
"""Prints out Flight path and Rocket Attitude angle graphs available
about the Flight
Returns
-------
None
"""
# Path, Attitude and Lateral Attitude Angle
# Angular position plots
fig5 = plt.figure(figsize=(9, 6))
ax1 = plt.subplot(211)
ax1.plot(
self.flight.path_angle[:, 0],
self.flight.path_angle[:, 1],
label="Flight Path Angle",
)
ax1.plot(
self.flight.attitude_angle[:, 0],
self.flight.attitude_angle[:, 1],
label="Rocket Attitude Angle",
)
ax1.set_xlim(0, self.first_event_time)
ax1.legend()
ax1.grid(True)
ax1.set_xlabel("Time (s)")
ax1.set_ylabel("Angle (°)")
ax1.set_title("Flight Path and Attitude Angle")
ax2 = plt.subplot(212)
ax2.plot(
self.flight.lateral_attitude_angle[:, 0],
self.flight.lateral_attitude_angle[:, 1],
)
ax2.set_xlim(0, self.first_event_time)
ax2.set_xlabel("Time (s)")
ax2.set_ylabel("Lateral Attitude Angle (°)")
ax2.set_title("Lateral Attitude Angle")
ax2.grid(True)
plt.subplots_adjust(hspace=0.5)
plt.show()
return None
[docs]
def angular_kinematics_data(self):
"""Prints out all Angular velocity and acceleration graphs available
about the Flight
Returns
-------
None
"""
# Angular velocity and acceleration plots
fig4 = plt.figure(figsize=(9, 9))
ax1 = plt.subplot(311)
ax1.plot(self.flight.w1[:, 0], self.flight.w1[:, 1], color="#ff7f0e")
ax1.set_xlim(0, self.first_event_time)
ax1.set_xlabel("Time (s)")
ax1.set_ylabel(r"Angular Velocity - ${\omega_1}$ (rad/s)", color="#ff7f0e")
ax1.set_title(
r"Angular Velocity ${\omega_1}$ | Angular Acceleration ${\alpha_1}$"
)
ax1.tick_params("y", colors="#ff7f0e")
ax1.grid(True)
ax1up = ax1.twinx()
ax1up.plot(self.flight.alpha1[:, 0], self.flight.alpha1[:, 1], color="#1f77b4")
ax1up.set_ylabel(
r"Angular Acceleration - ${\alpha_1}$ (rad/s²)", color="#1f77b4"
)
ax1up.tick_params("y", colors="#1f77b4")
ax2 = plt.subplot(312)
ax2.plot(self.flight.w2[:, 0], self.flight.w2[:, 1], color="#ff7f0e")
ax2.set_xlim(0, self.first_event_time)
ax2.set_xlabel("Time (s)")
ax2.set_ylabel(r"Angular Velocity - ${\omega_2}$ (rad/s)", color="#ff7f0e")
ax2.set_title(
r"Angular Velocity ${\omega_2}$ | Angular Acceleration ${\alpha_2}$"
)
ax2.tick_params("y", colors="#ff7f0e")
ax2.grid(True)
ax2up = ax2.twinx()
ax2up.plot(self.flight.alpha2[:, 0], self.flight.alpha2[:, 1], color="#1f77b4")
ax2up.set_ylabel(
r"Angular Acceleration - ${\alpha_2}$ (rad/s²)", color="#1f77b4"
)
ax2up.tick_params("y", colors="#1f77b4")
ax3 = plt.subplot(313)
ax3.plot(self.flight.w3[:, 0], self.flight.w3[:, 1], color="#ff7f0e")
ax3.set_xlim(0, self.first_event_time)
ax3.set_xlabel("Time (s)")
ax3.set_ylabel(r"Angular Velocity - ${\omega_3}$ (rad/s)", color="#ff7f0e")
ax3.set_title(
r"Angular Velocity ${\omega_3}$ | Angular Acceleration ${\alpha_3}$"
)
ax3.tick_params("y", colors="#ff7f0e")
ax3.grid(True)
ax3up = ax3.twinx()
ax3up.plot(self.flight.alpha3[:, 0], self.flight.alpha3[:, 1], color="#1f77b4")
ax3up.set_ylabel(
r"Angular Acceleration - ${\alpha_3}$ (rad/s²)", color="#1f77b4"
)
ax3up.tick_params("y", colors="#1f77b4")
plt.subplots_adjust(hspace=0.5)
plt.show()
return None
[docs]
def aerodynamic_forces(self):
"""Prints out all Forces and Moments graphs available about the Flight
Returns
-------
None
"""
# Aerodynamic force and moment plots
fig7 = plt.figure(figsize=(9, 12))
ax1 = plt.subplot(411)
ax1.plot(
self.flight.aerodynamic_lift[: self.first_event_time_index, 0],
self.flight.aerodynamic_lift[: self.first_event_time_index, 1],
label="Resultant",
)
ax1.plot(
self.flight.R1[: self.first_event_time_index, 0],
self.flight.R1[: self.first_event_time_index, 1],
label="R1",
)
ax1.plot(
self.flight.R2[: self.first_event_time_index, 0],
self.flight.R2[: self.first_event_time_index, 1],
label="R2",
)
ax1.set_xlim(0, self.first_event_time)
ax1.legend()
ax1.set_xlabel("Time (s)")
ax1.set_ylabel("Lift Force (N)")
ax1.set_title("Aerodynamic Lift Resultant Force")
ax1.grid()
ax2 = plt.subplot(412)
ax2.plot(
self.flight.aerodynamic_drag[: self.first_event_time_index, 0],
self.flight.aerodynamic_drag[: self.first_event_time_index, 1],
)
ax2.set_xlim(0, self.first_event_time)
ax2.set_xlabel("Time (s)")
ax2.set_ylabel("Drag Force (N)")
ax2.set_title("Aerodynamic Drag Force")
ax2.grid()
ax3 = plt.subplot(413)
ax3.plot(
self.flight.aerodynamic_bending_moment[: self.first_event_time_index, 0],
self.flight.aerodynamic_bending_moment[: self.first_event_time_index, 1],
label="Resultant",
)
ax3.plot(
self.flight.M1[: self.first_event_time_index, 0],
self.flight.M1[: self.first_event_time_index, 1],
label="M1",
)
ax3.plot(
self.flight.M2[: self.first_event_time_index, 0],
self.flight.M2[: self.first_event_time_index, 1],
label="M2",
)
ax3.set_xlim(0, self.first_event_time)
ax3.legend()
ax3.set_xlabel("Time (s)")
ax3.set_ylabel("Bending Moment (N m)")
ax3.set_title("Aerodynamic Bending Resultant Moment")
ax3.grid()
ax4 = plt.subplot(414)
ax4.plot(
self.flight.aerodynamic_spin_moment[: self.first_event_time_index, 0],
self.flight.aerodynamic_spin_moment[: self.first_event_time_index, 1],
)
ax4.set_xlim(0, self.first_event_time)
ax4.set_xlabel("Time (s)")
ax4.set_ylabel("Spin Moment (N m)")
ax4.set_title("Aerodynamic Spin Moment")
ax4.grid()
plt.subplots_adjust(hspace=0.5)
plt.show()
return None
[docs]
def energy_data(self):
"""Prints out all Energy components graphs available about the Flight
Returns
-------
None
"""
fig8 = plt.figure(figsize=(9, 9))
ax1 = plt.subplot(411)
ax1.plot(
self.flight.kinetic_energy[:, 0],
self.flight.kinetic_energy[:, 1],
label="Kinetic Energy",
)
ax1.plot(
self.flight.rotational_energy[:, 0],
self.flight.rotational_energy[:, 1],
label="Rotational Energy",
)
ax1.plot(
self.flight.translational_energy[:, 0],
self.flight.translational_energy[:, 1],
label="Translational Energy",
)
ax1.set_xlim(
0,
(
self.flight.apogee_time
if self.flight.apogee_time != 0.0
else self.flight.t_final
),
)
ax1.ticklabel_format(style="sci", axis="y", scilimits=(0, 0))
ax1.set_title("Kinetic Energy Components")
ax1.set_xlabel("Time (s)")
ax1.set_ylabel("Energy (J)")
ax1.legend()
ax1.grid()
ax2 = plt.subplot(412)
ax2.plot(
self.flight.total_energy[:, 0],
self.flight.total_energy[:, 1],
label="Total Energy",
)
ax2.plot(
self.flight.kinetic_energy[:, 0],
self.flight.kinetic_energy[:, 1],
label="Kinetic Energy",
)
ax2.plot(
self.flight.potential_energy[:, 0],
self.flight.potential_energy[:, 1],
label="Potential Energy",
)
ax2.set_xlim(
0,
(
self.flight.apogee_time
if self.flight.apogee_time != 0.0
else self.flight.t_final
),
)
ax2.ticklabel_format(style="sci", axis="y", scilimits=(0, 0))
ax2.set_title("Total Mechanical Energy Components")
ax2.set_xlabel("Time (s)")
ax2.set_ylabel("Energy (J)")
ax2.legend()
ax2.grid()
ax3 = plt.subplot(413)
ax3.plot(
self.flight.thrust_power[:, 0],
self.flight.thrust_power[:, 1],
label="|Thrust Power|",
)
ax3.set_xlim(0, self.flight.rocket.motor.burn_out_time)
ax3.ticklabel_format(style="sci", axis="y", scilimits=(0, 0))
ax3.set_title("Thrust Absolute Power")
ax3.set_xlabel("Time (s)")
ax3.set_ylabel("Power (W)")
ax3.legend()
ax3.grid()
ax4 = plt.subplot(414)
ax4.plot(
self.flight.drag_power[:, 0],
-self.flight.drag_power[:, 1],
label="|Drag Power|",
)
ax4.set_xlim(
0,
(
self.flight.apogee_time
if self.flight.apogee_time != 0.0
else self.flight.t_final
),
)
ax3.ticklabel_format(style="sci", axis="y", scilimits=(0, 0))
ax4.set_title("Drag Absolute Power")
ax4.set_xlabel("Time (s)")
ax4.set_ylabel("Power (W)")
ax4.legend()
ax4.grid()
plt.subplots_adjust(hspace=1)
plt.show()
return None
[docs]
def fluid_mechanics_data(self):
"""Prints out a summary of the Fluid Mechanics graphs available about
the Flight
Returns
-------
None
"""
# Trajectory Fluid Mechanics Plots
fig10 = plt.figure(figsize=(9, 12))
ax1 = plt.subplot(411)
ax1.plot(self.flight.mach_number[:, 0], self.flight.mach_number[:, 1])
ax1.set_xlim(0, self.flight.t_final)
ax1.set_title("Mach Number")
ax1.set_xlabel("Time (s)")
ax1.set_ylabel("Mach Number")
ax1.grid()
ax2 = plt.subplot(412)
ax2.plot(self.flight.reynolds_number[:, 0], self.flight.reynolds_number[:, 1])
ax2.set_xlim(0, self.flight.t_final)
ax2.ticklabel_format(style="sci", axis="y", scilimits=(0, 0))
ax2.set_title("Reynolds Number")
ax2.set_xlabel("Time (s)")
ax2.set_ylabel("Reynolds Number")
ax2.grid()
ax3 = plt.subplot(413)
ax3.plot(
self.flight.dynamic_pressure[:, 0],
self.flight.dynamic_pressure[:, 1],
label="Dynamic Pressure",
)
ax3.plot(
self.flight.total_pressure[:, 0],
self.flight.total_pressure[:, 1],
label="Total Pressure",
)
ax3.plot(
self.flight.pressure[:, 0],
self.flight.pressure[:, 1],
label="Static Pressure",
)
ax3.set_xlim(0, self.flight.t_final)
ax3.legend()
ax3.ticklabel_format(style="sci", axis="y", scilimits=(0, 0))
ax3.set_title("Total and Dynamic Pressure")
ax3.set_xlabel("Time (s)")
ax3.set_ylabel("Pressure (Pa)")
ax3.grid()
ax4 = plt.subplot(414)
ax4.plot(self.flight.angle_of_attack[:, 0], self.flight.angle_of_attack[:, 1])
ax4.set_title("Angle of Attack")
ax4.set_xlabel("Time (s)")
ax4.set_ylabel("Angle of Attack (°)")
ax4.set_xlim(self.flight.out_of_rail_time, self.first_event_time)
ax4.set_ylim(0, self.flight.angle_of_attack(self.flight.out_of_rail_time) + 15)
ax4.grid()
plt.subplots_adjust(hspace=0.5)
plt.show()
return None
[docs]
def stability_and_control_data(self):
"""Prints out Rocket Stability and Control parameters graphs available
about the Flight
Returns
-------
None
"""
fig9 = plt.figure(figsize=(9, 6))
ax1 = plt.subplot(211)
ax1.plot(self.flight.stability_margin[:, 0], self.flight.stability_margin[:, 1])
ax1.set_xlim(0, self.flight.stability_margin[:, 0][-1])
ax1.set_title("Stability Margin")
ax1.set_xlabel("Time (s)")
ax1.set_ylabel("Stability Margin (c)")
ax1.set_xlim(0, self.first_event_time)
ax1.axvline(
x=self.flight.out_of_rail_time,
color="r",
linestyle="--",
label="Out of Rail Time",
)
ax1.axvline(
x=self.flight.rocket.motor.burn_out_time,
color="g",
linestyle="--",
label="Burn Out Time",
)
ax1.axvline(
x=self.flight.apogee_time,
color="m",
linestyle="--",
label="Apogee Time",
)
ax1.legend()
ax1.grid()
ax2 = plt.subplot(212)
max_attitude = max(self.flight.attitude_frequency_response[:, 1])
max_attitude = max_attitude if max_attitude != 0 else 1
ax2.plot(
self.flight.attitude_frequency_response[:, 0],
self.flight.attitude_frequency_response[:, 1] / max_attitude,
label="Attitude Angle",
)
max_omega1 = max(self.flight.omega1_frequency_response[:, 1])
max_omega1 = max_omega1 if max_omega1 != 0 else 1
ax2.plot(
self.flight.omega1_frequency_response[:, 0],
self.flight.omega1_frequency_response[:, 1] / max_omega1,
label=r"$\omega_1$",
)
max_omega2 = max(self.flight.omega2_frequency_response[:, 1])
max_omega2 = max_omega2 if max_omega2 != 0 else 1
ax2.plot(
self.flight.omega2_frequency_response[:, 0],
self.flight.omega2_frequency_response[:, 1] / max_omega2,
label=r"$\omega_2$",
)
max_omega3 = max(self.flight.omega3_frequency_response[:, 1])
max_omega3 = max_omega3 if max_omega3 != 0 else 1
ax2.plot(
self.flight.omega3_frequency_response[:, 0],
self.flight.omega3_frequency_response[:, 1] / max_omega3,
label=r"$\omega_3$",
)
ax2.set_title("Frequency Response")
ax2.set_xlabel("Frequency (Hz)")
ax2.set_ylabel("Amplitude Magnitude Normalized")
ax2.set_xlim(0, 5)
ax2.legend()
ax2.grid()
plt.subplots_adjust(hspace=0.5)
plt.show()
return None
[docs]
def pressure_rocket_altitude(self):
"""Plots out pressure at rocket's altitude.
Returns
-------
None
"""
# self.flight.pressure()
plt.figure()
ax1 = plt.subplot(111)
ax1.plot(self.flight.pressure[:, 0], self.flight.pressure[:, 1])
ax1.set_title("Pressure at Rocket's Altitude")
ax1.set_xlabel("Time (s)")
ax1.set_ylabel("Pressure (Pa)")
ax1.set_xlim(0, self.flight.t_final)
ax1.grid()
plt.show()
return None
[docs]
def pressure_signals(self):
"""Plots out all Parachute Trigger Pressure Signals.
This function can be called also for plot pressure data for flights
without Parachutes, in this case the Pressure Signals will be simply
the pressure provided by the atmosphericModel, at Flight z positions.
This means that no noise will be considered if at least one parachute
has not been added.
This function aims to help the engineer to visually check if there
are anomalies with the Flight Simulation.
Returns
-------
None
"""
if len(self.flight.parachute_events) > 0:
for parachute in self.flight.rocket.parachutes:
print("\nParachute: ", parachute.name)
parachute.noise_signal_function()
parachute.noisy_pressure_signal_function()
parachute.clean_pressure_signal_function()
else:
print("\nRocket has no parachutes. No parachute plots available")
return None
[docs]
def all(self):
"""Prints out all plots available about the Flight.
Returns
-------
None
"""
print("\n\nTrajectory 3d Plot\n")
self.trajectory_3d()
print("\n\nTrajectory Kinematic Plots\n")
self.linear_kinematics_data()
print("\n\nAngular Position Plots\n")
self.flight_path_angle_data()
print("\n\nPath, Attitude and Lateral Attitude Angle plots\n")
self.attitude_data()
print("\n\nTrajectory Angular Velocity and Acceleration Plots\n")
self.angular_kinematics_data()
print("\n\nAerodynamic Forces Plots\n")
self.aerodynamic_forces()
print("\n\nRail Buttons Forces Plots\n")
self.rail_buttons_forces()
print("\n\nTrajectory Energy Plots\n")
self.energy_data()
print("\n\nTrajectory Fluid Mechanics Plots\n")
self.fluid_mechanics_data()
print("\n\nTrajectory Stability and Control Plots\n")
self.stability_and_control_data()
print("\n\nRocket and Parachute Pressure Plots\n")
self.pressure_rocket_altitude()
self.pressure_signals()
return None