class SetSurfaceTest(unittest.TestCase):
def test_SetSurfaceNoParts(self):
self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0])
self.rocket.set_surface()
self.assertEqual(self.rocket.get_surface(), 0.0)
def test_SetSurfaceOnePart(self):
self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0])
self.part_one = RocketPart(1000.0, 2000.0, 0.34)
self.rocket.append_part(self.part_one)
self.rocket.set_surface()
self.assertEqual(self.rocket.get_surface(), 2000.0)
def test_SetSurfaceNParts(self):
self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0])
self.part_one = RocketPart(1000.0, 2000.0, 0.34)
self.tank_one = Tank(1000.0, 2000.0, 0.34, 1000.0, 0.5, 100.0)
self.rocket.append_part(self.part_one)
self.rocket.set_surface()
self.assertEqual(self.rocket.get_surface(), 2000.0)
self.rocket.append_part(self.tank_one)
self.rocket.set_surface()
self.assertEqual(self.rocket.get_surface(), 4000.0)
def test_SetSurfaceNPartsFalseNonZero(self):
self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0])
self.part_one = RocketPart(1234.5, 3000.0, 0.34)
self.tank_one = Tank(6789.0, 3000.0, 0.34, 1000.0, 0.5, 100.0)
self.rocket.append_part(self.part_one)
self.rocket.set_surface()
self.assertNotEqual(self.rocket.get_surface(), 2000.0)
self.rocket.append_part(self.tank_one)
self.rocket.set_surface()
self.assertNotEqual(self.rocket.get_surface(), 4000.0)
class AppendPartTest(unittest.TestCase):
def test_AppendPartInt(self):
self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0])
with self.assertRaises(ValueError):
self.rocket.append_part(123)
def test_AppendPartString(self):
self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0])
with self.assertRaises(ValueError):
self.rocket.append_part("test")
def test_AppendPartRocketPartFirst(self):
self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0])
self.part_one = RocketPart(1000.0, 2000.0, 0.34)
self.rocket.append_part(self.part_one)
self.assertEqual(self.rocket.rocket_parts[0], self.part_one)
def test_AppendPartTankFirst(self):
self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0])
self.tank_one = Tank(1000.0, 2000.0, 0.34, 1000.0, 0.5, 100.0)
with self.assertRaises(ValueError):
self.rocket.append_part(self.tank_one)
def test_AppendPartRocketPartThenTank(self):
self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0])
self.part_one = RocketPart(1000.0, 2000.0, 0.34)
self.tank_one = Tank(1000.0, 2000.0, 0.34, 1000.0, 0.5, 100.0)
self.rocket.append_part(self.part_one)
self.rocket.append_part(self.tank_one)
self.assertEqual(self.rocket.rocket_parts[0], self.part_one)
self.assertEqual(self.rocket.rocket_parts[1], self.tank_one)
class GetCurrentStage(unittest.TestCase):
def test_GetCurrentStageNone(self):
self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0])
with self.assertRaises(ValueError):
self.rocket.get_current_stage()
def test_GetCurrentStageOne(self):
self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0])
self.part_one = RocketPart(1234.5, 2000.0, 0.34)
self.rocket.append_part(self.part_one)
self.assertEqual(self.rocket.get_current_stage(), self.part_one)
def test_GetCurrentStageN(self):
self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0])
self.part_one = RocketPart(1234.5, 2000.0, 0.34)
self.tank_one = Tank(6789.0, 2000.0, 0.34, 1000.0, 0.5, 100.0)
self.tank_two = Tank(6789.0, 2000.0, 0.34, 1000.0, 0.5, 100.0)
self.rocket.append_part(self.part_one)
self.rocket.append_part(self.tank_one)
self.rocket.append_part(self.tank_two)
self.assertEqual(self.rocket.get_current_stage(), self.tank_two)
self.rocket.decouple()
self.assertEqual(self.rocket.get_current_stage(), self.tank_one)
def main():
"""
Declare your planet, atmosphere with its layers, the rocket with its parts, the data object and the time delta here
and run the simulation
:return:
"""
# Setup here
sim_max_step = 100000 # Maximum time steps the simulation should run
sim_time_step = 0.1 # [s] Timestep the simulation uses
earth = Planet(pos_planet=[0.0, 0.0],
mass_planet=5.974e+24,
radius_planet=12756.32 / 2.0 * 1000)
earth_radius = earth.get_radius()
troposphere = Layer(pressure_low=101325.0,
width_layer=18000.0,
temp_gradient=-0.0065,
temp_low=288.15)
stratosphere = Layer(pressure_low=16901.37,
width_layer=32000.0,
temp_gradient=0.0031875,
temp_low=171.15)
mesosphere = Layer(pressure_low=1.02,
width_layer=30000.0,
temp_gradient=-0.003333,
temp_low=273.15)
thermosphere = Layer(pressure_low=0.04,
width_layer=420000.0,
temp_gradient=-0.000405,
temp_low=173.15)
exosphere = Layer(pressure_low=0.0,
width_layer=9999999999.0,
temp_gradient=0.0,
temp_low=3.0)
earth_atmosphere = Atmosphere()
earth_atmosphere.add_layer(troposphere)
earth_atmosphere.add_layer(stratosphere)
earth_atmosphere.add_layer(mesosphere)
earth_atmosphere.add_layer(thermosphere)
earth_atmosphere.add_layer(exosphere)
# Set maximum propellant mass
A150_mass_propellant = 484.8076
# Calculate A150 one tank:
sim_flight_name = "A150_OneTank"
sim_data = Data(
data_file="./Results_2/{}/Results_Data.csv".format(sim_flight_name))
sim_data.name = "Einstufig"
A150_payload = 0.0 # kg moegliche Nutzlast
A150_nose_cone = RocketPart(mass_part=7.0 + 2.31336 + A150_payload,
surface_part=0.1140,
drag_coefficient_part=0.27)
A150_liquid_tank = Tank(mass_part=116.1216,
surface_part=0.0,
drag_coefficient_part=0.0,
mass_propellant=A150_mass_propellant,
mass_change_tank=9.394,
velocity_exhaust_tank=1417.32,
surface_nozzle=0.0275,
pressure_nozzle=101325.0)
A150 = Rocket(pos=[earth_radius, 0.0],
velocity=[0.0, 0.0],
acceleration=[0.0, 0.0])
A150_booster = Tank(mass_part=28.1232,
surface_part=0.0,
drag_coefficient_part=0.0,
mass_propellant=117.6074,
mass_change_tank=47.1733,
velocity_exhaust_tank=1747.6074,
surface_nozzle=0.0434,
pressure_nozzle=101325.0)
A150.append_part(A150_nose_cone)
A150.append_part(A150_liquid_tank)
A150.append_part(A150_booster)
A150.set_mass()
A150.set_surface()
sim_flight = Flight(sim_time_step, earth, A150, earth_atmosphere, sim_data)
# Running the simulation
run_sim(sim_flight, sim_flight_name, sim_max_step, sim_time_step)
# Calculate A150 two tanks 1
sim_flight_name = "A150_RefTankA"
sim_data = Data(
data_file="./Results_2/{}/Results_Data.csv".format(sim_flight_name))
sim_data.name = "Stufe 1 leer"
A150_payload = 0.0 # kg moegliche Nutzlast
A150_nose_cone = RocketPart(mass_part=7.0 + 2.31336 + A150_payload,
surface_part=0.1140,
drag_coefficient_part=0.27)
A150_liquid_tank_one = Tank(mass_part=116.1216,
surface_part=0.0,
drag_coefficient_part=0.0,
mass_propellant=A150_mass_propellant,
mass_change_tank=9.394,
velocity_exhaust_tank=1417.32,
surface_nozzle=0.0275,
pressure_nozzle=101325.0)
A150_liquid_tank_two = Tank(mass_part=116.1216,
surface_part=0.0,
drag_coefficient_part=0.0,
mass_propellant=0,
mass_change_tank=9.394,
velocity_exhaust_tank=1417.32,
surface_nozzle=0.0275,
pressure_nozzle=101325.0)
A150 = Rocket(pos=[earth_radius, 0.0],
velocity=[0.0, 0.0],
acceleration=[0.0, 0.0])
A150_booster = Tank(mass_part=28.1232,
surface_part=0.0,
drag_coefficient_part=0.0,
mass_propellant=117.6074,
mass_change_tank=47.1733,
velocity_exhaust_tank=1747.6074,
surface_nozzle=0.0434,
pressure_nozzle=101325.0)
A150.append_part(A150_nose_cone)
A150.append_part(A150_liquid_tank_one)
A150.append_part(A150_liquid_tank_two)
A150.append_part(A150_booster)
A150.set_mass()
A150.set_surface()
sim_flight_a = Flight(sim_time_step, earth, A150, earth_atmosphere,
sim_data)
# Running the simulation
run_sim(sim_flight_a, sim_flight_name, sim_max_step, sim_time_step)
# Calculate A150 two tanks 1
sim_flight_name = "A150_RefTankB"
sim_data = Data(
data_file="./Results_2/{}/Results_Data.csv".format(sim_flight_name))
sim_data.name = "Stufe 2 leer"
A150_payload = 0.0 # kg moegliche Nutzlast
A150_nose_cone = RocketPart(mass_part=7.0 + 2.31336 + A150_payload,
surface_part=0.1140,
drag_coefficient_part=0.27)
A150_liquid_tank_one = Tank(mass_part=116.1216,
surface_part=0.0,
drag_coefficient_part=0.0,
mass_propellant=0,
mass_change_tank=9.394,
velocity_exhaust_tank=1417.32,
surface_nozzle=0.0275,
pressure_nozzle=101325.0)
A150_liquid_tank_two = Tank(mass_part=116.1216,
surface_part=0.0,
drag_coefficient_part=0.0,
mass_propellant=A150_mass_propellant,
mass_change_tank=9.394,
velocity_exhaust_tank=1417.32,
surface_nozzle=0.0275,
pressure_nozzle=101325.0)
A150 = Rocket(pos=[earth_radius, 0.0],
velocity=[0.0, 0.0],
acceleration=[0.0, 0.0])
A150_booster = Tank(mass_part=28.1232,
surface_part=0.0,
drag_coefficient_part=0.0,
mass_propellant=117.6074,
mass_change_tank=47.1733,
velocity_exhaust_tank=1747.6074,
surface_nozzle=0.0434,
pressure_nozzle=101325.0)
A150.append_part(A150_nose_cone)
A150.append_part(A150_liquid_tank_one)
A150.append_part(A150_liquid_tank_two)
A150.append_part(A150_booster)
A150.set_mass()
A150.set_surface()
sim_flight_b = Flight(sim_time_step, earth, A150, earth_atmosphere,
sim_data)
# Running the simulation
run_sim(sim_flight_b, sim_flight_name, sim_max_step, sim_time_step)
# Searching for optimal tank setup
divisor = 2
count = 0
sim_opt_max_step = 40
propellant_step = A150_mass_propellant / sim_opt_max_step
while count < sim_opt_max_step:
sim_flight_name = "A150_TankSetup_{0:03d}".format(count)
sim_data = Data(data_file="./Results_2/{}/Results_Data.csv".format(
sim_flight_name))
A150_mass_propellant_tank_one = propellant_step * count
A150_mass_propellant_tank_two = A150_mass_propellant - propellant_step * count
sim_data.name = "Stufe 1: {0:.2f} kg Stufe 2: {1:.2f} kg".format(
A150_mass_propellant_tank_two, A150_mass_propellant_tank_one)
A150 = Rocket(pos=[earth_radius, 0.0],
velocity=[0.0, 0.0],
acceleration=[0.0, 0.0])
A150_liquid_tank_one_split = Tank(
mass_part=116.1216,
surface_part=0.0,
drag_coefficient_part=0.0,
mass_propellant=A150_mass_propellant_tank_one,
mass_change_tank=9.394,
velocity_exhaust_tank=1417.32,
surface_nozzle=0.0275,
pressure_nozzle=101325.0)
A150_liquid_tank_two_split = Tank(
mass_part=116.1216,
surface_part=0.0,
drag_coefficient_part=0.0,
mass_propellant=A150_mass_propellant_tank_two,
mass_change_tank=9.394,
velocity_exhaust_tank=1417.32,
surface_nozzle=0.0275,
pressure_nozzle=101325.0)
A150_booster = Tank(mass_part=28.1232,
surface_part=0.0,
drag_coefficient_part=0.0,
mass_propellant=117.6074,
mass_change_tank=47.1733,
velocity_exhaust_tank=1747.6074,
surface_nozzle=0.0434,
pressure_nozzle=101325.0)
A150.append_part(A150_nose_cone)
A150.append_part(A150_liquid_tank_one_split)
A150.append_part(A150_liquid_tank_two_split)
A150.append_part(A150_booster)
A150.set_mass()
A150.set_surface()
sim_flight_p = Flight(sim_time_step, earth, A150, earth_atmosphere,
sim_data)
# Running the simulation
run_sim(sim_flight_p, sim_flight_name, sim_max_step, sim_time_step)
count += 1
# Calculate A150 one tank, no booster:
sim_flight_name = "A150_NoBooster"
sim_data = Data(
data_file="./Results_2/{}/Results_Data.csv".format(sim_flight_name))
sim_data.name = "Einstufig ohne Booster"
A150_payload = 0.0 # kg moegliche Nutzlast
A150_nose_cone = RocketPart(mass_part=7.0 + 2.31336 + A150_payload,
surface_part=0.1140,
drag_coefficient_part=0.27)
A150_liquid_tank = Tank(mass_part=116.1216,
surface_part=0.0,
drag_coefficient_part=0.0,
mass_propellant=A150_mass_propellant,
mass_change_tank=9.394,
velocity_exhaust_tank=1417.32,
surface_nozzle=0.0275,
pressure_nozzle=101325.0)
A150 = Rocket(pos=[earth_radius, 0.0],
velocity=[0.0, 0.0],
acceleration=[0.0, 0.0])
A150.append_part(A150_nose_cone)
A150.append_part(A150_liquid_tank)
A150.set_mass()
A150.set_surface()
sim_flight_nb = Flight(sim_time_step, earth, A150, earth_atmosphere,
sim_data)
# Running the simulation
run_sim(sim_flight_nb, sim_flight_name, sim_max_step, sim_time_step)
print "Optimization has ended after {} iterations, Results available".format(
count - 1)
class DecoupleTest(unittest.TestCase):
def test_decoupleLastTank(self):
self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0])
self.part_one = RocketPart(1234.5, 2000.0, 0.34)
self.tank_one = Tank(6789.0, 2000.0, 0.34, 1000.0, 0.5, 100.0)
self.rocket.append_part(self.part_one)
self.rocket.append_part(self.tank_one)
self.assertEqual(self.rocket.rocket_parts[0], self.part_one)
self.assertEqual(self.rocket.rocket_parts[1], self.tank_one)
self.rocket.decouple()
self.assertEqual(len(self.rocket.rocket_parts), 1)
def test_decoupleNTimes(self):
self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0])
self.part_one = RocketPart(1234.5, 2000.0, 0.34)
self.tank_one = Tank(6789.0, 2000.0, 0.34, 1000.0, 0.5, 100.0)
self.tank_two = Tank(6789.0, 2000.0, 0.34, 1000.0, 0.5, 100.0)
self.tank_three = Tank(6789.0, 2000.0, 0.34, 1000.0, 0.5, 100.0)
self.tank_four = Tank(6789.0, 2000.0, 0.34, 1000.0, 0.5, 100.0)
self.tank_five = Tank(6789.0, 2000.0, 0.34, 1000.0, 0.5, 100.0)
self.rocket.append_part(self.part_one)
self.rocket.append_part(self.tank_one)
self.rocket.append_part(self.tank_two)
self.rocket.append_part(self.tank_three)
self.rocket.append_part(self.tank_four)
self.rocket.append_part(self.tank_five)
self.assertEqual(len(self.rocket.rocket_parts), 6)
self.assertEqual(self.rocket.rocket_parts[-1], self.tank_five)
self.rocket.decouple()
self.assertEqual(len(self.rocket.rocket_parts), 5)
self.assertEqual(self.rocket.rocket_parts[-1], self.tank_four)
self.rocket.decouple()
self.assertEqual(len(self.rocket.rocket_parts), 4)
self.assertEqual(self.rocket.rocket_parts[-1], self.tank_three)
def test_decoupleNose(self):
self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0])
self.part_one = RocketPart(1234.5, 2000.0, 0.34)
self.rocket.append_part(self.part_one)
self.rocket.decouple()
self.assertEqual(self.rocket.rocket_parts[-1], self.part_one)