Flight Data Visualization Example¶

This notebook demonstrates comprehensive flight data visualization for water rocket simulations. You'll learn how to:

• Run a complete water rocket simulation
• Identify different flight phases (thrust, ballistic, descent)
• Create multiple organized plots showing all aspects of flight performance
• Analyze trajectory, forces, propellant usage, and exhaust properties

Setup and Imports¶

In [1]:

import numpy as np
import matplotlib.pyplot as plt
from matplotlib.gridspec import GridSpec
import matplotlib.patches as patches

from waterrocketpy.core.simulation import WaterRocketSimulator
from waterrocketpy.rocket.builder import RocketBuilder, create_standard_rocket
from waterrocketpy.core.constants import ATMOSPHERIC_PRESSURE, INITIAL_TEMPERATURE
from waterrocketpy.visualization.plot_flight_data import (
    setup_plot_style,
    identify_flight_phases,
    plot_trajectory_and_velocity,
    plot_forces_and_acceleration,
    plot_propellant_and_pressure,
    plot_exhaust_properties,
    plot_air_exit_conditions,
    print_flight_summary
)

print("✓ All imports successful!")

import numpy as np import matplotlib.pyplot as plt from matplotlib.gridspec import GridSpec import matplotlib.patches as patches from waterrocketpy.core.simulation import WaterRocketSimulator from waterrocketpy.rocket.builder import RocketBuilder, create_standard_rocket from waterrocketpy.core.constants import ATMOSPHERIC_PRESSURE, INITIAL_TEMPERATURE from waterrocketpy.visualization.plot_flight_data import ( setup_plot_style, identify_flight_phases, plot_trajectory_and_velocity, plot_forces_and_acceleration, plot_propellant_and_pressure, plot_exhaust_properties, plot_air_exit_conditions, print_flight_summary ) print("✓ All imports successful!")

✓ All imports successful!

Setup Plotting Style¶

Configure matplotlib for professional-looking plots.

In [2]:

# Setup plotting style for consistent, professional plots
setup_plot_style()

print("✓ Plot style configured")

# Setup plotting style for consistent, professional plots setup_plot_style() print("✓ Plot style configured")

✓ Plot style configured

Create and Configure Rocket¶

Set up a standard water rocket configuration for our simulation.

In [3]:

# Create a standard rocket configuration
print("Creating standard rocket...")
rocket = create_standard_rocket()

print(f"✓ Rocket created: {rocket.name}")
print(f"  - Empty mass: {rocket.empty_mass:.3f} kg")
print(f"  - Water fraction: {rocket.water_fraction:.3f}")
print(f"  - Initial pressure: {rocket.initial_pressure:.0f} Pa")
print(f"  - Nozzle diameter: {rocket.nozzle_diameter*1000:.2f} mm")

# Create a standard rocket configuration print("Creating standard rocket...") rocket = create_standard_rocket() print(f"✓ Rocket created: {rocket.name}") print(f" - Empty mass: {rocket.empty_mass:.3f} kg") print(f" - Water fraction: {rocket.water_fraction:.3f}") print(f" - Initial pressure: {rocket.initial_pressure:.0f} Pa") print(f" - Nozzle diameter: {rocket.nozzle_diameter*1000:.2f} mm")

Creating standard rocket...
✓ Rocket created: Standard 2L Rocket
  - Empty mass: 0.250 kg
  - Water fraction: 0.330
  - Initial pressure: 810600 Pa
  - Nozzle diameter: 15.00 mm

Setup and Run Simulation¶

Configure the simulation parameters and run the water rocket simulation.

In [4]:

# Convert rocket to simulation parameters
print("Setting up simulation...")
builder = RocketBuilder.from_dict(rocket.__dict__)
sim_params = builder.to_simulation_params()

# Create simulator and define settings
simulator = WaterRocketSimulator()
sim_settings = {
    "max_time": 100.0,    # Maximum simulation time (seconds)
    "time_step": 0.01,    # Time step for integration (seconds)
    "solver": "RK45"      # Numerical integration method
}

print("Running simulation...")
flight_data = simulator.simulate(sim_params, sim_settings)

print(f"✓ Simulation completed! {len(flight_data.time)} data points generated")
print(f"  - Flight duration: {flight_data.time[-1]:.2f} seconds")
print(f"  - Maximum altitude: {max(flight_data.altitude):.2f} meters")

# Convert rocket to simulation parameters print("Setting up simulation...") builder = RocketBuilder.from_dict(rocket.__dict__) sim_params = builder.to_simulation_params() # Create simulator and define settings simulator = WaterRocketSimulator() sim_settings = { "max_time": 100.0, # Maximum simulation time (seconds) "time_step": 0.01, # Time step for integration (seconds) "solver": "RK45" # Numerical integration method } print("Running simulation...") flight_data = simulator.simulate(sim_params, sim_settings) print(f"✓ Simulation completed! {len(flight_data.time)} data points generated") print(f" - Flight duration: {flight_data.time[-1]:.2f} seconds") print(f" - Maximum altitude: {max(flight_data.altitude):.2f} meters")

Setting up simulation...
Running simulation...
Starting water expulsion phase...
Water depleted at t=0.123s, starting air expulsion phase...
Air depleted at t=0.199s, starting coasting phase...
✓ Simulation completed! 752 data points generated
  - Flight duration: 7.19 seconds
  - Maximum altitude: 61.45 meters

Analyze Flight Phases¶

Identify the different phases of the rocket's flight: thrust phase, ballistic phase, and descent.

In [5]:

# Identify flight phases
print("Analyzing flight phases...")
phases = identify_flight_phases(flight_data)

# Print detailed flight summary
print_flight_summary(flight_data, phases)

# Identify flight phases print("Analyzing flight phases...") phases = identify_flight_phases(flight_data) # Print detailed flight summary print_flight_summary(flight_data, phases)

Analyzing flight phases...

============================================================
WATER ROCKET FLIGHT ANALYSIS SUMMARY
============================================================

Flight Performance:
------------------
  Maximum Altitude         : 61.45 m
  Maximum Velocity         : 44.60 m/s
  Total Flight Time        : 7.19 s
  Time to Apogee           : 3.29 s

Phase Durations:
---------------
  Water Phase              : 0.12 s
  Air Phase                : 0.08 s
  Coasting Phase           : 6.99 s

Initial Conditions:
------------------
  Initial Water Mass       : 660.0 g
  Initial Air Mass         : 12.6 g
  Initial Pressure         : 8.11 bar
  Initial Temperature      : 300.0 K

============================================================

Visualization 1: Trajectory and Velocity¶

Plot the rocket's altitude and velocity over time, with flight phases highlighted.

In [6]:

# Create trajectory and velocity plots
print("Generating trajectory and velocity plots...")
fig1 = plot_trajectory_and_velocity(flight_data, phases)
plt.show()

# Create trajectory and velocity plots print("Generating trajectory and velocity plots...") fig1 = plot_trajectory_and_velocity(flight_data, phases) plt.show()

Generating trajectory and velocity plots...

Visualization 2: Forces and Acceleration¶

Analyze the forces acting on the rocket and the resulting acceleration.

In [7]:

# Create forces and acceleration plots
print("Generating forces and acceleration plots...")
fig2 = plot_forces_and_acceleration(flight_data, phases)
plt.show()

# Create forces and acceleration plots print("Generating forces and acceleration plots...") fig2 = plot_forces_and_acceleration(flight_data, phases) plt.show()

Generating forces and acceleration plots...

Visualization 3: Propellant and Pressure¶

Track the water mass consumption and internal pressure changes during the thrust phase.

In [8]:

# Create propellant and pressure plots with zoomed-in x-axis
print("Generating propellant and pressure plots...")
fig3 = plot_propellant_and_pressure(flight_data, phases)

# Zoom in on x-axis to show only until the end of air exhaust phase
# Get the end time of the air phase from phases data
air_end_time = phases.get('air_end_time', phases.get('thrust_end_time', 1.0))

# Apply zoom to all subplots in the figure
for ax in fig3.get_axes():
    ax.set_xlim(0, air_end_time * 1.1)  # Add 10% margin for better visibility

plt.tight_layout()
plt.show()

print(f"✓ Propellant and pressure plot zoomed to t = {air_end_time:.3f}s (end of air phase)")

# Create propellant and pressure plots with zoomed-in x-axis print("Generating propellant and pressure plots...") fig3 = plot_propellant_and_pressure(flight_data, phases) # Zoom in on x-axis to show only until the end of air exhaust phase # Get the end time of the air phase from phases data air_end_time = phases.get('air_end_time', phases.get('thrust_end_time', 1.0)) # Apply zoom to all subplots in the figure for ax in fig3.get_axes(): ax.set_xlim(0, air_end_time * 1.1) # Add 10% margin for better visibility plt.tight_layout() plt.show() print(f"✓ Propellant and pressure plot zoomed to t = {air_end_time:.3f}s (end of air phase)")

Generating propellant and pressure plots...

✓ Propellant and pressure plot zoomed to t = 1.000s (end of air phase)

Visualization 4: Exhaust Properties¶

Examine the properties of the exhaust flow during the thrust phase.

In [9]:

# Create exhaust properties plots with zoomed-in x-axis
print("Generating exhaust properties plots...")
fig4 = plot_exhaust_properties(flight_data, phases)

# Zoom in on x-axis to show only until the end of air exhaust phase
# Get the end time of the air phase from phases data
air_end_time = phases.get('air_end_time', phases.get('thrust_end_time', 1.0))

# Apply zoom to all subplots in the figure
for ax in fig4.get_axes():
    ax.set_xlim(0, air_end_time * 1.1)  # Add 10% margin for better visibility

plt.tight_layout()
plt.show()

print(f"✓ Exhaust properties plot zoomed to t = {air_end_time:.3f}s (end of air phase)")

# Create exhaust properties plots with zoomed-in x-axis print("Generating exhaust properties plots...") fig4 = plot_exhaust_properties(flight_data, phases) # Zoom in on x-axis to show only until the end of air exhaust phase # Get the end time of the air phase from phases data air_end_time = phases.get('air_end_time', phases.get('thrust_end_time', 1.0)) # Apply zoom to all subplots in the figure for ax in fig4.get_axes(): ax.set_xlim(0, air_end_time * 1.1) # Add 10% margin for better visibility plt.tight_layout() plt.show() print(f"✓ Exhaust properties plot zoomed to t = {air_end_time:.3f}s (end of air phase)")

Generating exhaust properties plots...

✓ Exhaust properties plot zoomed to t = 1.000s (end of air phase)

Visualization 5: Air Exit Conditions¶

Analyze the conditions of air as it exits the nozzle during the air-only thrust phase.

In [10]:

# Create air exit conditions plots
print("Generating air exit conditions plots...")
fig5 = plot_air_exit_conditions(flight_data, phases)
plt.show()

# Create air exit conditions plots print("Generating air exit conditions plots...") fig5 = plot_air_exit_conditions(flight_data, phases) plt.show()

Generating air exit conditions plots...

Key Insights from the Visualization¶

From these comprehensive plots, you can observe:

Five different visualization categories:

• Trajectory and velocity plots
• Forces and acceleration analysis
• Propellant consumption and pressure dynamics
• Exhaust properties visualization
• Air exit conditions analysis

Next Steps¶

Try experimenting with:

• Various simulation settings (time step, solver method)
• Comparing multiple rocket designs side by side