Launch Vehicle 3 (LV3) Electromechanical Recovery System (ERS) Drogue Release Documentation

Work in Progress



In [2]:

    
# NECESSARY GARGIN

#########################################

import numpy as np
import matplotlib.pyplot as plt
import pandas as pd
from scipy.integrate import simps
%matplotlib inline

# Graphing helper function
def setup_graph(title='',x_label='', y_label='', fig_size=None):
    fig = plt.figure()
    if fig_size != None:
        fig.set_size_inches(fig_size[0],
                            fig_size[1])
    ax = fig.add_subplot(111)
    ax.set_title(title)
    ax.set_xlabel(x_label)
    ax.set_ylabel(y_label)









    



---------------------------------------------------------------------------
ModuleNotFoundError                       Traceback (most recent call last)
<ipython-input-2-490b77f2444b> in <module>
      3 #########################################
      4 
----> 5 import numpy as np
      6 import matplotlib.pyplot as plt
      7 import pandas as pd

ModuleNotFoundError: No module named 'numpy'



In [1]:

    
# KNOWN INFORMATION

## *Dimensions given in basic metric units*

#########################################

# Basic constants (units in m,s,N)

g = 9.81

#########################################

# Drogue Parachute Dimensions

## Diameter (m)
diaP = 1.524

## Mass (kg)
Pm = 10.70

## Drag coefficient (unitless)
Cd = 1.85

#########################################

# Airframe Dimensions

## Overall length (m)
totL = 3.528

## Outer diameter (m)
OD = .168

## Dry and wet mass (kg)
Dm = 21.8
Wm = 30.5

#########################################

# Expected Operations

## Max thrust (N)
thrust = 3500

## Apogee (m)
Ap = 5500

## Time to apogee (s)
tAp = 32

## Max speed (m/s)
spdmax = 425
Machmax = 1.3

## Max acceleration (m/s^2)
accelmax = 105



In [ ]:

    
# ASSUMPTIONS

# Time until nose cone release actuation (s)
tnc = 1

# Time until drogue parachute is fully deployed (s)
tdeploy = 3

# Total free fall time after apogee (s)
tTot = tnc + tdeploy

# Time span that the impulse from parachute deployment experiences (s)
timp = 0.5

# Velocity at apogee (m/s)
vAp = 0



In [ ]:

    
# BASIC CALCULATIONS

## *Dimensions given in basic metric units*

#########################################

# Weight of parachute (N)
Pw = Pm * g

# Dry and wet weight of airframe (N)
Dw = Dm * g
Ww = Wm * g

# Velocity at full deployment (m/s)
vdeploy = vAp + (g*tTot)

# Impulse experienced at full deployment (N*s)
Imp = Wm * vdeploy

# Force generated from the impulse (N)
F = Imp / timp



In [ ]:

    
# DESIGN PARAMETERS

## *Dimensions given in basic metric units*

#########################################