I am trying to design a rocket fin in rocketpy..but it's not showing any output..i am using VS code IDE

[Manassadashiv]

import rocketpy as rp
import matplotlib.pyplot as plt

Define the rocket components

Body component

body = rp.BodyComponent(
Diameter=0.0762, # 3 inches in meters
Length=0.8636, # 34 inches in meters
Thickness=0.00635, # 0.25 inches in meters
Material="Cardboard",
Coating="None",
Shoulder=0.0508, # 2 inches in meters
Frusta=[]
)

Nose component

nose = rp.NoseComponent(
Length=0.2794, # 11 inches in meters
Shape="ogive",
Shoulder=0.0508, # 2 inches in meters
Material="Polystyrene"
)

Fin component

fins = rp.FinSet(
NFinSet=4,
Length=0.1270, # 5 inches in meters
Sweep=30, # Increased sweep angle for supersonic performance
Root=0.0635, # 2.5 inches in meters
Tip=0.0508, # 2 inches in meters
Thickness=0.00635, # 0.25 inches in meters
Protrusion=0,
Material="Plywood"
)

Create the rocket

rocket = rp.Rocket(
BodyComponent=body,
NoseComponent=nose,
FinSet=fins,
LaunchLug=None,
ShockCord=rp.ShockCord(
Material="Elastic Cord",
Diameter=0.0508, # 2 mm in meters
Length=5.715 # 225 inches in meters
),
Parachute=rp.Parachute(
Diameter=0.9144, # 36 inches in meters
CdS=0.48, # Parachute drag coefficient * area
DeploymentAltitude=1000, # Deploy parachute at 1000 meters
DeploymentVelocity=45 # Deploy parachute at 45 m/s
),
RecoveryDevice=None
)

Set the motor

motor_h268r = rp.Motor(
Manufacturer="Cesaroni",
MotorType="H268R-14",
Delay=10.2
)

motor_g74w = rp.Motor(
Manufacturer="Cesaroni",
MotorType="G74W-9",
Delay=7.4
)

Set the simulation parameters

env = rp.Environment(
WindSpeed=0,
WindDirection=0,
Temperature=15,
Pressure=101325,
Density=1.225
)

Run the simulation with the H268R-14 motor

rocket.motor = motor_h268r
results_h268r = rp.simulate(
rocket=rocket,
motor=motor_h268r,
environment=env,
latitude=0,
longitude=0,
altitude=0,
launchRod=5,
launchAngle=85,
date="2023-06-01"
)

Run the simulation with the G74W-9 motor

rocket.motor = motor_g74w
results_g74w = rp.simulate(
rocket=rocket,
motor=motor_g74w,
environment=env,
latitude=0,
longitude=0,
altitude=0,
launchRod=5,
launchAngle=85,
date="2023-06-01"
)

Print the simulation results

print(f"Apogee (H268R-14): {results_h268r.apogee * 0.3048} m")
print(f"Max Velocity (H268R-14): {results_h268r.maxVelocity * 0.3048} m/s")
print(f"Apogee (G74W-9): {results_g74w.apogee * 0.3048} m")
print(f"Max Velocity (G74W-9): {results_g74w.maxVelocity * 0.3048} m/s")

Plot the flight trajectories

plt.figure(figsize=(10, 6))
plt.plot(results_h268r.time, results_h268r.altitude * 0.3048, label="H268R-14")
plt.plot(results_g74w.time, results_g74w.altitude * 0.3048, label="G74W-9")
plt.xlabel("Time (s)")
plt.ylabel("Altitude (m)")
plt.title("Rocket Flight Trajectories")
plt.legend()
plt.grid()
plt.show()

Analyze the stability margin

print(f"Stability Margin (H268R-14): {(results_h268r.cp - results_h268r.cg) / 0.0762} calibers")
print(f"Stability Margin (G74W-9): {(results_g74w.cp - results_g74w.cg) / 0.0762} calibers")

[Gui-FernandesBR]

Hello @Manassadashiv , thanks for your question.

The syntax you have presented is not familiar to me. RocketPy doesn't have classes like BodyComponent, FinSet, or NoseComponent.
Are you sure you have opened your question in the right repo?

Please refer to our documentation to get complete instructions on how to run your trajectory simulations with rocketpy: docs.rocketpy.org