def __init__(self, propellant, motor_height, motor_diameter, exit_area,
throat_area):
self.motor_height = motor_height
self.motor_diameter = motor_diameter
self.exit_area = exit_area
self.throat_area = throat_area
self.density = propellant.density
self.a = propellant.a
self.n = propellant.n
self.T = propellant.T
self.gamma = propellant.gamma
self.molar_mass = propellant.molar_mass
self.c_star = propellant.c_star
self.R = propellant.R
self.exit_mach = burn.calculate_exit_mach(self.gamma, self.exit_area,
self.throat_area)
self.exit_temp = burn.calculate_nozzle_exit_temp(
self.T, self.gamma, self.exit_mach)
self.exit_velocity = burn.calculate_nozzle_exit_velocity(
self.exit_mach, self.gamma, self.R, self.exit_temp)
# initializing variables to be stored after burn method
self.chamber_pressure = 0
self.burn_rate = 0
self.regression_depth = 0
self.burning_area = 0
self.m_dot = 0
self.exit_pressure = 0
self.elapsed_time = 0
self.thrust = 0
self.method = 0
def __init__(self, propellant, motor_height, motor_diameter, bore_radius,
web_radius, fillet_radius, epsilon, number_of_points,
exit_area, throat_area, burn_top, burn_bottom):
self.burn_top = burn_top
self.burn_bottom = burn_bottom
self.motor_height = motor_height
self.motor_diameter = motor_diameter
self.exit_area = exit_area
self.throat_area = throat_area
self.Ro = motor_diameter / 2
self.Ri = bore_radius
self.Rp = web_radius
self.f = fillet_radius
self.epsilon = epsilon
self.N = number_of_points
self.theta = 2 * np.arctan(
self.Rp * np.sin(np.pi * epsilon / self.N) *
np.tan(np.pi * epsilon / self.N) /
(self.Rp * np.sin(np.pi * epsilon / self.N) -
self.Ri * np.tan(np.pi * epsilon / self.N)))
self.density = propellant.density
self.a = propellant.a
self.n = propellant.n
self.T = propellant.T
self.gamma = propellant.gamma
self.molar_mass = propellant.molar_mass
self.c_star = propellant.c_star
self.R = propellant.R
self.exit_mach = burn.calculate_exit_mach(self.gamma, self.exit_area,
self.throat_area)
self.exit_temp = burn.calculate_nozzle_exit_temp(
self.T, self.gamma, self.exit_mach)
self.exit_velocity = burn.calculate_nozzle_exit_velocity(
self.exit_mach, self.gamma, self.R, self.exit_temp)
# initializing variables to be stored after burn method
self.chamber_pressure = 0
self.burn_rate = 0
self.regression_depth = 0
self.burning_area = 0
self.m_dot = 0
self.exit_pressure = 0
self.elapsed_time = 0
self.thrust = 0
self.method = 0
def __init__(self, propellant, motor_height, motor_diameter, bore_radius,
fin_width, fin_length, number_of_fins, exit_area, throat_area,
burn_top, burn_bottom):
self.burn_top = burn_top
self.burn_bottom = burn_bottom
self.motor_height = motor_height
self.motor_diameter = motor_diameter
self.exit_area = exit_area
self.throat_area = throat_area
self.Rp = motor_diameter / 2
self.fin_width = fin_width
self.fin_length = fin_length
self.Rb = bore_radius
self.N = number_of_fins
self.density = propellant.density
self.a = propellant.a
self.n = propellant.n
self.T = propellant.T
self.gamma = propellant.gamma
self.molar_mass = propellant.molar_mass
self.c_star = propellant.c_star
self.R = propellant.R
self.exit_mach = burn.calculate_exit_mach(self.gamma, self.exit_area,
self.throat_area)
self.exit_temp = burn.calculate_nozzle_exit_temp(
self.T, self.gamma, self.exit_mach)
self.exit_velocity = burn.calculate_nozzle_exit_velocity(
self.exit_mach, self.gamma, self.R, self.exit_temp)
# initializing variables to be stored after burn method
self.chamber_pressure = 0
self.burn_rate = 0
self.regression_depth = 0
self.burning_area = 0
self.m_dot = 0
self.exit_pressure = 0
self.elapsed_time = 0
self.thrust = 0
self.method = 0