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simulator.py
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simulator.py
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import math
import tkinter as tk
from tkinter import ttk
from tkinter import filedialog
from tkinter import messagebox
from matplotlib.backends.backend_tkagg import FigureCanvasTkAgg
import matplotlib.pyplot as plt
# Constants declaration
delta_t = 0.0001
P_atm = float(1*101325)
# Simulation output data
array_time = []
array_h = []
array_Ft = []
array_mass = []
array_temperature = []
array_pressure = []
array_V_water = []
array_V_air = []
# Optimalization output data
array_opt_x = []
array_opt_Ic = []
array_opt_tc = []
array_opt_delta_v = []
array_opt_Ist = []
opt_variable_name = ""
# Export data
engine_name = ""
engine_diameter = 0
engine_lenght = 0
engine_dry_mass = 0
engine_full_mass = 0
engine_manufacturer = ""
# Efficiency data
efficiency_sim_rod = 1
efficiency_sim_water = 1
efficiency_sim_gas = 1
efficiency_opt_rod = 1
efficiency_opt_water = 1
efficiency_opt_gas = 1
# SIMULATION FOR OPTIMALIZATION FUNCTION
def opt_sim(k_const, Rs, water_density, P_ins, At, V_air, V_water, Roc_mass, T, rod_lenght, rod_inside_diameter):
try:
#print(str(k_const) + " " + str(Rs) + " " + str(water_density) + " "+ str(P_ins) + " " + str(At) + " " + str(V_water) + " " + str(V_air) + " " + str(Roc_mass) +" "+ str(T) + " " + str(rod_lenght) + " " + str(rod_inside_diameter)+ "\n")
# Local output variables declaration
Ic = float(0)
max_h = float(0)
total_time = float(0)
delta_v = float(0)
# Local variables for simulation
s = float(0.0)
vrod = float(0.0)
# V_air fix for existing rod
V_air = V_air - At * rod_lenght
# Define adiabatic constant
C_const = P_ins * pow(V_air, k_const)
# Calculate mass of air
mass_air = P_ins * V_air / (T * Rs)
mass_propelant = mass_air + V_water * water_density
total_time = 0
#print(str(Roc_mass) + " " + str(mass_propelant))
if(rod_inside_diameter > 0 and rod_lenght > 0):
while(s < rod_lenght):
# Update total_time
total_time = total_time + delta_t
# Calculate Ft and Ic
Ft = P_ins * At * efficiency_opt_rod
# Update impuls
Ic += Ft * delta_t
arod = Ft / Roc_mass
vrod += delta_t * arod
delta_v = vrod
s += vrod * delta_t + 0.5 * arod * delta_t * delta_t
#print(str(Roc_mass))
if(rod_inside_diameter == 0 and rod_lenght > 0):
while(s < rod_lenght):
# Array update
#array_time.append(total_time)
total_time = total_time + delta_t
#array_mass.append(Roc_mass)
#array_V_air.append(V_air)
#array_V_water.append(V_water)
#array_pressure.append(P_ins)
#array_temperature.append(T)
# Calculate Ft and Ic
Ft = P_ins * At * efficiency_opt_rod
#array_Ft.append(Ft)
Ic += Ft * delta_t
arod = Ft / Roc_mass
vrod += delta_t * arod
delta_v = vrod
s += vrod * delta_t + 0.5 * arod * delta_t * delta_t
delta_V = At * vrod * delta_t
V_air += delta_V
P_ins = C_const / pow(V_air, k_const)
T = (P_ins * V_air) / (mass_air * Rs)
#print(str(Roc_mass))
# Loop for water phase, handles models that push out only fraction of water inside
while(float(V_water) > float(0) and float(P_ins) > float(P_atm)):
# Update time array for plot
#array_time.append(total_time)
total_time = total_time + delta_t
# Calculate thurst
Ft = 2 * At * (P_ins - P_atm) * efficiency_opt_water
#array_Ft.append(Ft)
Ic += Ft * delta_t
ve = math.sqrt(2 * (P_ins - P_atm) / water_density)
# Calculate change of volume
delta_V = At * ve * delta_t
# Update volume arrays
#array_V_water.append(V_water)
#array_V_air.append(V_air)
# Calculate temperature
T = P_ins * V_air / (mass_air * Rs)
#array_temperature.append(T)
# Update mass array
#array_mass.append(Roc_mass)
Roc_mass = Roc_mass - delta_V * water_density
# Update delta_v
delta_v = delta_v + delta_t * Ft / Roc_mass
# Update volume values
V_air = V_air + delta_V
V_water = V_water - delta_V
# Calculate pressure and update array
#array_pressure.append(P_ins)
P_ins = C_const * pow(V_air, -k_const)
#print(str(Roc_mass))
# Loop for Mach 1 on exit
while(P_ins > P_atm and P_ins/P_atm >= pow((k_const+1)/2, k_const/(k_const-1))):
# Update time array for plot
#array_time.append(total_time)
total_time = total_time + delta_t
# Add values that are not changing for plot
#array_V_water.append(V_water)
#array_V_air.append(V_air)
Tt = T * 2 / (k_const + 1)
dot_m = P_ins * At * pow(2/(k_const+1), 0.5 * (k_const+1)/(k_const-1)) * math.sqrt(k_const/(Rs*T))
ve_air = math.sqrt(k_const * Rs * Tt)
P_throat = pow(2 / (k_const + 1), k_const / (k_const - 1)) * P_ins
Ft = (dot_m * ve_air + At * (P_throat - P_atm)) * efficiency_opt_gas
array_Ft.append(Ft)
Ic += Ft * delta_t
delta_m = dot_m * delta_t
# Update rocket mass
Roc_mass = Roc_mass - delta_m
#array_mass.append(Roc_mass)
# Update delta_v
delta_v = delta_v + delta_t * Ft / Roc_mass
mass_air = mass_air - delta_m
T = (P_ins / Rs) * pow(V_air / (mass_air + delta_m), k_const) * pow(V_air / mass_air, 1 - k_const)
#array_temperature.append(T)
P_ins = mass_air * Rs * T / V_air
#array_pressure.append(P_ins)
#print(str(Roc_mass))
while(P_ins > P_atm):
# Update time array for plot
#array_time.append(total_time)
total_time = total_time + delta_t
# Add values that are not changing for plot
#array_V_water.append(V_water)
#array_V_air.append(V_air)
Mach = math.sqrt(2 / (k_const-1) * (pow(P_ins / P_atm, (k_const-1) / k_const) - 1))
Tt = T / (1 + 0.5 * (k_const-1) * Mach * Mach)
ve_air = Mach * math.sqrt(k_const * Rs * Tt)
density_chamber = mass_air / V_air
density_throat = density_chamber / pow(1 + 0.5 * (k_const - 1) * Mach * Mach, 1 / (k_const-1))
dot_m = At * density_throat * ve_air
Ft = dot_m * ve_air * efficiency_opt_gas
#array_Ft.append(Ft)
Ic += Ft * delta_t
delta_m = dot_m * delta_t
# Update rocket mass
Roc_mass = Roc_mass - delta_m
#array_mass.append(Roc_mass)
# Update delta_v
delta_v = delta_v + delta_t * Ft / Roc_mass
mass_air = mass_air - delta_m
T = (P_ins / Rs) * pow(V_air / (mass_air + delta_m), k_const) * pow(V_air / mass_air, 1 - k_const)
#array_temperature.append(T)
P_ins = mass_air * Rs * T / V_air
#array_pressure.append(P_ins)
#print(str(Roc_mass))
#print(str(Ic) + "\n")
return [Ic, total_time, Ic / (mass_propelant * 9.81), delta_v]
except ValueError:
# Handle the case where entered value is not valid
error_label_r.config(text="Invalid input.")
# MAIN OPTIMALIZATION FUNCTION
def optimalize():
global opt_variable_name
array_opt_x.clear()
array_opt_Ic.clear()
array_opt_tc.clear()
array_opt_delta_v.clear()
array_opt_Ist.clear()
gas_name = choosen_gas_opt.get()
if(gas_name == "Air"):
k_const = 1.4
Rs = 287
if(gas_name == "Argon"):
k_const = 1.67
Rs = 208
if(gas_name == "Helium"):
k_const = 1.66
Rs = 2077
if(gas_name == "Hydrogen"):
k_const = 1.41
Rs = 4124
if(gas_name == "Nitrogen"):
k_const = 1.4
Rs = 297
if(gas_name == "CO2"):
k_const = 1.3
Rs = 188
if(gas_name == "Xenon"):
k_const = 1.65
Rs = 208
try:
if(gas_name == "Custom"):
k_const = float(entry_combobox1_opt.get())
Rs = float(entry_combobox2_opt.get())
water_density = float(entry_6_r.get())
# Entry values read
P_ins = float(entry_0_r.get())*100000
At = 3.1415*pow(0.001*float(entry_1_r.get())/2, 2)
V_total = float(entry_2_r.get())*0.001
water_content = float(entry_3_r.get()) * 0.01
V_air = float(V_total - water_content * V_total)
V_water = float(water_content * V_total)
dry_mass = float(entry_4_r.get())
T = float(entry_5_r.get())+273.15
rod_lenght = float(entry_launch_lenght_opt.get()) * 0.001
rod_inside_diameter = float(entry_launch_diameter_opt.get()) * 0.001
# Error safety net
if(P_ins <= 0):
raise ValueError
if(k_const <= 0):
raise ValueError
if(Rs <= 0):
raise ValueError
if(water_density <= 0):
raise ValueError
if(At <= 0):
raise ValueError
if(V_total <= 0):
raise ValueError
if(water_content < 0 or water_content >= 1):
raise ValueError
if(dry_mass <= 0):
raise ValueError
if(T <= 0):
raise ValueError
if(rod_inside_diameter < 0):
raise ValueError
if(rod_lenght < 0):
raise ValueError
if(rod_inside_diameter > 0.001 * float(entry_1_r.get())):
raise ValueError
s = float(0.0)
vrod = float(0.0)
# V_air fix for existing rod
V_air = V_air - At * rod_lenght
# Define adiabatic constant
C_const = P_ins * pow(V_air, k_const)
# Calculate mass of air
mass_air = P_ins * V_air / (T * Rs)
mass_propelant = mass_air + V_water * water_density
Roc_mass = dry_mass + mass_propelant
# Get Optimalization variables
opt_var = choosen_opt_variable.get()
opt_range_min = float(entry_opt_min.get())
opt_range_max = float(entry_opt_max.get())
opt_it = int(entry_opt_itteration.get())
# Error safety net for optimalization variables
if(opt_range_max <= opt_range_min):
raise ValueError
if(opt_var == "Water content"):
if(opt_range_min < 0 or opt_range_max >= 100):
raise ValueError
if(opt_range_min == 0 and (opt_var == "Throat" or opt_var == "Volume")):
raise ValueError
if(opt_it <= 0 and opt_var != "Gas temperature"):
raise ValueError
if(opt_var == "Gas temperature" and opt_range_min < -273):
raise ValueError
opt_variable_name = opt_var
if(opt_var == "Pressure"):
opt_range_min *= 100000
opt_range_max *= 100000
opt_eps = (opt_range_max - opt_range_min) / float(opt_it)
for i in range(opt_it + 1):
array_opt_x.append(opt_range_min)
#print(str(opt_range_min) + "\n")
mass_air = opt_range_min * V_air / (T * Rs)
mass_propelant = mass_air + V_water * water_density
Roc_mass = dry_mass + mass_propelant
temp_data_opt = opt_sim(k_const, Rs, water_density, opt_range_min, At, V_air, V_water, Roc_mass, T, rod_lenght, rod_inside_diameter)
array_opt_Ic.append(temp_data_opt[0])
array_opt_tc.append(temp_data_opt[1])
array_opt_Ist.append(temp_data_opt[2])
array_opt_delta_v.append(temp_data_opt[3])
opt_range_min += opt_eps
if(opt_var == "Throat"):
opt_range_min = 3.1415*pow(0.001*opt_range_min/2, 2)
opt_range_max = 3.1415*pow(0.001*opt_range_max/2, 2)
opt_eps = (opt_range_max - opt_range_min) / float(opt_it)
for i in range(opt_it + 1):
array_opt_x.append(opt_range_min)
#print(str(opt_range_min) + "\n")
mass_air = P_ins * V_air / (T * Rs)
mass_propelant = mass_air + V_water * water_density
Roc_mass = dry_mass + mass_propelant
temp_data_opt = opt_sim(k_const, Rs, water_density, P_ins, opt_range_min, V_air, V_water, Roc_mass, T, rod_lenght, rod_inside_diameter)
array_opt_Ic.append(temp_data_opt[0])
array_opt_tc.append(temp_data_opt[1])
array_opt_Ist.append(temp_data_opt[2])
array_opt_delta_v.append(temp_data_opt[3])
opt_range_min += opt_eps
if(opt_var == "Volume"):
opt_range_min *= 0.001
opt_range_max *= 0.001
opt_eps = (opt_range_max - opt_range_min) / float(opt_it)
for i in range(opt_it + 1):
array_opt_x.append(opt_range_min)
#print(str(opt_range_min) + "\n")
V_air = opt_range_min - water_content * opt_range_min
V_water = water_content * opt_range_min
mass_air = P_ins * V_air / (T * Rs)
mass_propelant = mass_air + V_water * water_density
Roc_mass = dry_mass + mass_propelant
temp_data_opt = opt_sim(k_const, Rs, water_density, P_ins, At, V_air, V_water, Roc_mass, T, rod_lenght, rod_inside_diameter)
array_opt_Ic.append(temp_data_opt[0])
array_opt_tc.append(temp_data_opt[1])
array_opt_Ist.append(temp_data_opt[2])
array_opt_delta_v.append(temp_data_opt[3])
opt_range_min += opt_eps
if(opt_var == "Water content"):
opt_range_min *= 0.01
opt_range_max *= 0.01
opt_eps = (opt_range_max - opt_range_min) / float(opt_it)
for i in range(opt_it + 1):
array_opt_x.append(opt_range_min)
#print(str(opt_range_min) + "\n")
V_air = float(V_total - opt_range_min * V_total)
V_water = float(opt_range_min * V_total)
mass_air = P_ins * V_air / (T * Rs)
mass_propelant = mass_air + V_water * water_density
Roc_mass = dry_mass + mass_propelant
temp_data_opt = opt_sim(k_const, Rs, water_density, float(P_ins), At, V_air, V_water, Roc_mass, T, rod_lenght, rod_inside_diameter)
array_opt_Ic.append(temp_data_opt[0])
array_opt_tc.append(temp_data_opt[1])
array_opt_Ist.append(temp_data_opt[2])
array_opt_delta_v.append(temp_data_opt[3])
opt_range_min += opt_eps
if(opt_var == "Dry mass"):
#opt_range_max *= 0.01
opt_eps = (opt_range_max - opt_range_min) / float(opt_it)
for i in range(opt_it + 1):
array_opt_x.append(opt_range_min)
#print(str(opt_range_min) + "\n")
mass_air = P_ins * V_air / (T * Rs)
mass_propelant = mass_air + V_water * water_density
Roc_mass = opt_range_min + mass_propelant
#print(str(Roc_mass) + "\n")
temp_data_opt = opt_sim(k_const, Rs, water_density, float(P_ins), At, V_air, V_water, Roc_mass, T, rod_lenght, rod_inside_diameter)
array_opt_Ic.append(temp_data_opt[0])
array_opt_tc.append(temp_data_opt[1])
array_opt_Ist.append(temp_data_opt[2])
array_opt_delta_v.append(temp_data_opt[3])
opt_range_min += opt_eps
if(opt_var == "Gas temperature"):
opt_range_min += 273.15
opt_range_max += 273.15
opt_eps = (opt_range_max - opt_range_min) / float(opt_it)
for i in range(opt_it + 1):
array_opt_x.append(opt_range_min)
#print(str(opt_range_min) + "\n")
mass_air = P_ins * V_air / (opt_range_min * Rs)
mass_propelant = mass_air + V_water * water_density
Roc_mass = dry_mass + mass_propelant
temp_data_opt = opt_sim(k_const, Rs, water_density, float(P_ins), At, V_air, V_water, Roc_mass, opt_range_min, rod_lenght, rod_inside_diameter)
array_opt_Ic.append(temp_data_opt[0])
array_opt_tc.append(temp_data_opt[1])
array_opt_Ist.append(temp_data_opt[2])
array_opt_delta_v.append(temp_data_opt[3])
opt_range_min += opt_eps
plot_opt_Ic()
# Erase error message
error_label_r.config(text="")
except ValueError:
# Handle the case where entered value is not valid
error_label_r.config(text="Invalid input.")
def plot_opt_Ic():
try:
# Clear the previous plot
ax_right.clear()
# Plot the new data
ax_right.plot(array_opt_x, array_opt_Ic, linestyle='-', color='b')
# Set labels and title
ax_right.set_xlabel(opt_variable_name)
ax_right.set_ylabel('Ic[Ns]')
ax_right.set_title('Graph of impulse')
# Update the canvas
canvas_right.draw()
# Erase error message
error_label_r.config(text="")
except ValueError:
# Handle the case where the entered value is not a valid float
error_label_r.config(text="Invalid input.")
def plot_opt_tc():
try:
# Clear the previous plot
ax_right.clear()
# Plot the new data
ax_right.plot(array_opt_x, array_opt_tc, linestyle='-', color='b')
# Set labels and title
ax_right.set_xlabel(opt_variable_name)
ax_right.set_ylabel('Total time[s]')
ax_right.set_title('Graph of time')
# Update the canvas
canvas_right.draw()
# Erase error message
error_label_r.config(text="")
except ValueError:
# Handle the case where the entered value is not a valid float
error_label_r.config(text="Invalid input.")
def plot_opt_Ist():
try:
# Clear the previous plot
ax_right.clear()
# Plot the new data
ax_right.plot(array_opt_x, array_opt_Ist, linestyle='-', color='b')
# Set labels and title
ax_right.set_xlabel(opt_variable_name)
ax_right.set_ylabel('Specific impuls[s]')
ax_right.set_title('Graph of specific impulse')
# Update the canvas
canvas_right.draw()
# Erase error message
error_label_r.config(text="")
except ValueError:
# Handle the case where the entered value is not a valid float
error_label_r.config(text="Invalid input.")
def plot_opt_delta_v():
try:
# Clear the previous plot
ax_right.clear()
# Plot the new data
ax_right.plot(array_opt_x, array_opt_delta_v, linestyle='-', color='b')
# Set labels and title
ax_right.set_xlabel(opt_variable_name)
ax_right.set_ylabel('Delta v[m/s]')
ax_right.set_title('Graph of delta v')
# Update the canvas
canvas_right.draw()
# Erase error message
error_label_r.config(text="")
except ValueError:
# Handle the case where the entered value is not a valid float
error_label_r.config(text="Invalid input.")
# MAIN SIMULATION FUNCTION
def simulate():
global engine_dry_mass
global engine_full_mass
# Output variables declaration
Ic = float(0)
max_h = float(0)
total_time = float(0)
delta_v = float(0)
gas_name = choosen_gas.get()
try:
if(gas_name == "Air"):
k_const = 1.4
Rs = 287
if(gas_name == "Argon"):
k_const = 1.67
Rs = 208
if(gas_name == "Helium"):
k_const = 1.66
Rs = 2077
if(gas_name == "Hydrogen"):
k_const = 1.41
Rs = 4124
if(gas_name == "Nitrogen"):
k_const = 1.4
Rs = 297
if(gas_name == "CO2"):
k_const = 1.3
Rs = 188
if(gas_name == "Xenon"):
k_const = 1.65
Rs = 208
if(gas_name == "Custom"):
k_const = float(entry_combobox1.get())
Rs = float(entry_combobox2.get())
water_density = float(entry_6.get())
# Clear total_time value
total_time = 0
Ic = 0
delta_v = 0
# Clear all arrays
array_time.clear()
array_h.clear()
array_Ft.clear()
array_mass.clear()
array_temperature.clear()
array_pressure.clear()
array_V_water.clear()
array_V_air.clear()
# Entry values read
P_ins = float(entry_0.get())*100000
At = 3.1415*pow(0.001*float(entry_1.get())/2, 2)
V_total = float(entry_2.get())*0.001
water_content = float(entry_3.get()) * 0.01
V_air = V_total - water_content * V_total
V_water = water_content * V_total
dry_mass = float(entry_4.get())
engine_dry_mass = dry_mass
T = float(entry_5.get())+273.15
rod_lenght = float(entry_launch_lenght.get()) * 0.001
rod_inside_diameter = float(entry_launch_diameter.get()) * 0.001
# Error safety net
if(P_ins <= 0):
raise ValueError
if(k_const <= 0):
raise ValueError
if(Rs <= 0):
raise ValueError
if(water_density <= 0):
raise ValueError
if(At <= 0):
raise ValueError
if(V_total <= 0):
raise ValueError
if(water_content < 0 or water_content >= 1):
raise ValueError
if(dry_mass <= 0):
raise ValueError
if(T <= 0):
raise ValueError
if(rod_inside_diameter < 0):
raise ValueError
if(rod_lenght < 0):
raise ValueError
if(rod_inside_diameter >= 0.001 * float(entry_1.get())):
raise ValueError
s = float(0.0)
vrod = float(0.0)
# V_air fix for existing rod
V_air = V_air - At * rod_lenght
# Define adiabatic constant
C_const = P_ins * pow(V_air, k_const)
# Calculate mass of air
mass_air = P_ins * V_air / (T * Rs)
mass_propelant = mass_air + V_water * water_density
Roc_mass = dry_mass + mass_propelant
engine_full_mass = Roc_mass
if(rod_inside_diameter > 0 and rod_lenght > 0):
while(s < rod_lenght):
# Array update
array_time.append(total_time)
total_time = total_time + delta_t
array_V_water.append(V_water)
array_V_air.append(V_air)
array_mass.append(Roc_mass)
array_pressure.append(P_ins)
array_temperature.append(T)
# Calculate Ft and Ic
Ft = (P_ins * At) * efficiency_sim_rod
array_Ft.append(Ft)
Ic += Ft * delta_t
arod = Ft / Roc_mass
vrod += delta_t * arod
delta_v = vrod
s += vrod * delta_t + 0.5 * arod * delta_t * delta_t
if(rod_inside_diameter == 0 and rod_lenght > 0):
while(s < rod_lenght):
# Array update
array_time.append(total_time)
total_time = total_time + delta_t
array_mass.append(Roc_mass)
array_V_air.append(V_air)
array_V_water.append(V_water)
array_temperature.append(T)
array_pressure.append(P_ins)
# Calculate Ft and Ic
Ft = (P_ins * At) * efficiency_sim_rod
array_Ft.append(Ft)
Ic += Ft * delta_t
arod = Ft / Roc_mass
vrod = vrod + delta_t * arod
delta_v = vrod
#print(str(delta_v)+" "+ str(arod)+ " "+ str(vrod))
s += vrod * delta_t + 0.5 * arod * delta_t * delta_t
delta_V = At * vrod * delta_t
V_air += delta_V
P_ins = C_const / pow(V_air, k_const)
T = (P_ins * V_air) / (mass_air * Rs)
# Loop for water phase, handles models that push out only fraction of water inside
while(V_water > 0 and P_ins > P_atm):
# Update time array for plot
array_time.append(total_time)
total_time = total_time + delta_t
# Calculate thurst
Ft = (2 * At * (P_ins - P_atm)) * efficiency_sim_water
array_Ft.append(Ft)
Ic += Ft * delta_t
ve = math.sqrt(2 * (P_ins - P_atm) / water_density)
# Calculate change of volume
delta_V = At * ve * delta_t
# Update volume arrays
array_V_water.append(V_water)
array_V_air.append(V_air)
# Calculate temperature
T = P_ins * V_air / (mass_air * Rs)
array_temperature.append(T)
# Update mass array
array_mass.append(Roc_mass)
Roc_mass = Roc_mass - delta_V * water_density
# Update delta_v
delta_v = delta_v + delta_t * Ft / Roc_mass
#print(str(delta_v)+" "+ str(Ft / Roc_mass))
# Update volume values
V_air = V_air + delta_V
V_water = V_water - delta_V
# Calculate pressure and update array
P_ins = C_const * pow(V_air, -k_const)
array_pressure.append(P_ins)
# Loop for Mach 1 on exit
while(P_ins > P_atm and P_ins/P_atm >= pow((k_const+1)/2, k_const/(k_const-1))):
# Update time array for plot
array_time.append(total_time)
total_time = total_time + delta_t
# Add values that are not changing for plot
array_V_water.append(V_water)
array_V_air.append(V_air)
Tt = T * 2 / (k_const + 1)
dot_m = P_ins * At * pow(2/(k_const+1), 0.5 * (k_const+1)/(k_const-1)) * math.sqrt(k_const/(Rs*T))
#print(str(dot_m))
ve_air = math.sqrt(k_const * Rs * Tt)
#print(str(ve_air))
P_throat = pow(2 / (k_const + 1), k_const / (k_const - 1)) * P_ins
Ft = (dot_m * ve_air + At * (P_throat - P_atm)) * efficiency_sim_gas
#print(str(Ft) + " " +str(At*(P_throat - P_atm)))
array_Ft.append(Ft)
Ic += Ft * delta_t
delta_m = dot_m * delta_t
# Update rocket mass
Roc_mass = Roc_mass - delta_m
array_mass.append(Roc_mass)
# Update delta_v
delta_v = delta_v + delta_t * Ft / Roc_mass
mass_air = mass_air - delta_m
T = (P_ins / Rs) * pow(V_air / (mass_air + delta_m), k_const) * pow(V_air / mass_air, 1 - k_const)
array_temperature.append(T)
P_ins = mass_air * Rs * T / V_air
array_pressure.append(P_ins)
#print("\n")
# Loop for sub Mach 1 on exit
while(P_ins > P_atm):
# Update time array for plot
array_time.append(total_time)
total_time = total_time + delta_t
# Add values that are not changing for plot
array_V_water.append(V_water)
array_V_air.append(V_air)
Mach = math.sqrt(2 / (k_const-1) * (pow(P_ins / P_atm, (k_const-1) / k_const) - 1))
#print(str(Mach))
Tt = T / (1 + 0.5 * (k_const-1) * Mach * Mach)
ve_air = Mach * math.sqrt(k_const * Rs * Tt)
#print(str(ve_air))
density_chamber = mass_air / V_air
density_throat = density_chamber / pow(1 + 0.5 * (k_const - 1) * Mach * Mach, 1 / (k_const-1))
dot_m = At * density_throat * ve_air
#print(str(dot_m))
Ft = (dot_m * ve_air) * efficiency_sim_gas
#print(str(Ft))
array_Ft.append(Ft)
Ic += Ft * delta_t
delta_m = dot_m * delta_t
# Update rocket mass
Roc_mass = Roc_mass - delta_m
array_mass.append(Roc_mass)
# Update delta_v
delta_v = delta_v + delta_t * Ft / Roc_mass
mass_air = mass_air - delta_m
T = (P_ins / Rs) * pow(V_air / (mass_air + delta_m), k_const) * pow(V_air / mass_air, 1 - k_const)
array_temperature.append(T)
P_ins = mass_air * Rs * T / V_air
array_pressure.append(P_ins)
# Erase error message
error_label.config(text="")
# Print output values
'''
text_widget.insert(tk.END, "Ic = ")
text_widget.insert(tk.END, Ic)
text_widget.insert(tk.END, "\n")
text_widget.insert(tk.END, "tc = ")
text_widget.insert(tk.END, total_time)
text_widget.insert(tk.END, "\n")
text_widget.insert(tk.END, "Ist = ")
text_widget.insert(tk.END, Ic / (mass_propelant * 9.81))
text_widget.insert(tk.END, "\n")
text_widget.insert(tk.END, "delta_v = ")
text_widget.insert(tk.END, delta_v)
text_widget.insert(tk.END, "\n\n")
'''
text_widget_output = "Ic = {:.2f} Ns\n".format(Ic) + "tc = {:.2f} s\n".format(total_time) + "Ist = {:.2f} s\n".format(Ic / (mass_propelant * 9.81)) + "delta_v = {:.2f} m/s\n\n".format(delta_v)
text_widget.insert("1.0", text_widget_output)
plot_Ft()
except ValueError:
# Handle the case where entered value is not valid
error_label.config(text="Invalid input.")
def plot_Ft():
try:
# Clear the previous plot
ax_left.clear()
# Plot the new data
ax_left.plot(array_time, array_Ft, linestyle='-', color='b')
# Set labels and title
ax_left.set_xlabel('Time[t]')
ax_left.set_ylabel('Thrust[N]')
ax_left.set_title('Graph of thrust')
# Update the canvas
canvas_left.draw()
# Erase error message
error_label.config(text="")
except ValueError:
# Handle the case where the entered value is not a valid float
error_label.config(text="Invalid input.")
def plot_mass():
try:
# Clear the previous plot
ax_left.clear()
# Plot the new data
ax_left.plot(array_time, array_mass, linestyle='-', color='b')
# Set labels and title
ax_left.set_xlabel('Time[t]')
ax_left.set_ylabel('Mass[kg]')
ax_left.set_title('Graph of mass')
# Update the canvas
canvas_left.draw()
# Erase error message
error_label.config(text="")
except ValueError:
# Handle the case where the entered value is not a valid float
error_label.config(text="Invalid input.")