class GetMassTest(unittest.TestCase):
def test_GetMassZero(self):
self.planet = Planet(0.0, 6000.0, (0.0, 0.0))
self.assertEqual(self.planet.get_mass(), 0.0)
def test_GetMassNonZero(self):
self.planet = Planet(100000000.0, 6000.0, (0.0, 0.0))
self.assertEqual(self.planet.get_mass(), 100000000.0)
def test_GetMassFalseNonZero(self):
self.planet = Planet(6000.0, 100000000.0, (0.0, 0.0))
self.assertNotEqual(self.planet.get_mass(), 131231.0)
class GetRadiusTest(unittest.TestCase):
def test_GetRadiusZero(self):
self.planet = Planet(0.0, 0.0, (0.0, 0.0))
self.assertEqual(self.planet.get_radius(), 0.0)
def test_GetRadiusNonZero(self):
self.planet = Planet(0.0, 6000.0, (0.0, 0.0))
self.assertEqual(self.planet.get_radius(), 6000.0)
def test_GetRadiusFalseNonZero(self):
self.planet = Planet(0.0, 6000.0, (0.0, 0.0))
self.assertNotEqual(self.planet.get_radius(), 0.0)
class GetPosTest(unittest.TestCase):
def test_GetPosZero(self):
self.planet = Planet(0.0, 0.0, (0.0, 0.0))
self.assertEqual(self.planet.get_pos(), (0.0, 0.0))
def test_GetPosPositive(self):
self.planet = Planet(0.0, 0.0, (60.0, 40.6))
self.assertEqual(self.planet.get_pos(), (60.0, 40.6))
def test_GetPosNegtive(self):
self.planet = Planet(0.0, 0.0, (-30.3, -20.0))
self.assertEqual(self.planet.get_pos(), (-30.3, -20.0))
def test_GetPosFalseNonZero(self):
self.planet = Planet(0.0, 0.0, (60.2, 40.0))
self.assertNotEqual(self.planet.get_pos(), (-20.0, 30.0))
def create_planets():
n_planets = int(1.1 * (random.random() + 1))
for i in range(n_planets):
index = random.randrange(0, len(sprites.planets))
planet_pos=pos()
planet=Planet(planet_pos,sprites.planets[index])
create_ships(planet)
def firsttime():
global player_team
planet=Planet(complex(0,0),sprites.AquaPlanet)
planetteam=Team()
for i in range(random.randrange(1,5)):
ship=AiShip(planet,sprites.GreenShip)
ship.weapon=weapons[0](ship)
planetteam.register(ship)
player=PlayerShip(coords((40,40)))
player.weapon=weapons[1](player)
guardian=AiShip(player,sprites.OrangeShip)
guardian.weapon=weapons[0](guardian)
player_team=Team(player,guardian)
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)
def __init__(self,
name="Sol system",
size=500,
max_planets=3,
gamma=20,
scale=1,
max_time=100,
symmetry=0):
self.name = name
self.size = size
self.max_planets = max_planets
self.planets = []
self.gamma = gamma
self.scale = scale
self.max_time = max_time
self.collisions = 0
if not symmetry:
# TODO add frame of reference
self.add_planets(
Planet(name="Sôl", mass=2500, color="yellow", fix=False),
Planet(name="Mercury",
mass=1.5,
velocity=[0, 20],
position=[100, 0],
color="grey"),
Planet(name="Venus",
mass=1.85,
velocity=[0, -15],
position=[-150, 0]),
Planet(name="Terra",
mass=2,
velocity=[-10, 0],
position=[0, 290],
color="blue"),
Planet(name="Mars",
mass=1.2,
velocity=[15, 0],
position=[0, -290],
color="orange"),
Planet(name="Iuppiter",
mass=200,
velocity=[5, -5],
position=[-300, -290],
color="brown"),
Planet(name="Saturnus",
mass=150,
velocity=[-5, 5],
position=[300, 290],
color="Yellow",
ring=25),
Comet("Halley's Comet",
mass=0,
velocity=[4, 4],
position=[300, -290],
color="light blue"),
Planet(name="Saturnus",
mass=150,
velocity=[0, 20],
position=[500, -500],
color="Yellow"))
else:
self.add_planets(
Planet(name="Sol", mass=1000, color="yellow", fix=True))
for i in range(max_planets - 1):
self.add_planets(
Planet(name=i,
mass=0,
velocity=self.point_velocity(
sqrt((10 * gamma * self.planets[0].mass) /
symmetry), i, max_planets - 1),
position=self.point(symmetry, i, max_planets - 1),
color="white"))
def main():
#delta_t (in Days) for simulations
delta_t = np.longdouble(1.0) / (24.0 * 60.0 * 60.0)
ship = Craft(delta_t, x=35786, y=1, z=1, v_x=0, v_y=4.5, v_z=0, mass=12)
#Initialize Simulation
simulationStart = Time('2015-09-10T00:00:00')
simulationEnd = Time('2015-10-10T00:00:00')
if not os.path.isfile('de430.bsp'):
raise ValueError('de430.bsp was not found!')
kernel = SPK.open('de430.bsp')
#marsKernel = SPK.open('mar097.bsp')
if simulationType == 1:
planets = [ #Planet(kernel, 0, 0, np.longdouble(1.989*10**30)),
Planet(kernel, 199, 199, np.longdouble(3.285 * 10**23)),
Planet(kernel, 399, 399, np.longdouble(5.972 * 10**24))
]
if simulationType == 2:
planets = [ #Planet(kernel, 10, 10, np.longdouble(1.989*10**30)),
Planet(kernel, 299, 299, np.longdouble(4.867 * 10**24)),
Planet(kernel, 399, 399, np.longdouble(5.972 * 10**24))
]
if simulationType == 3:
planets = [ #Planet(kernel, 10, 10, np.longdouble(1.989*10**30)),
Planet(kernel, 399, 399, np.longdouble(5.972 * 10**24)),
Planet(kernel, 301, 399, np.longdouble(7.34767309 * 10**22))
]
if simulationType == 4:
planets = [ #Planet(kernel, 10, 10, np.longdouble(1.989*10**30)),
Planet(kernel, 399, 399, np.longdouble(5.972 * 10**24)),
Planet(kernel, 499, 499, np.longdouble(6.39 * 10**23))
]
if simulationType == 5:
planets = [ #Planet(kernel, 10, 10, np.longdouble(1.989*10**30)),
Planet(kernel, 399, 399, np.longdouble(5.972 * 10**24)),
Planet(kernel, 399, 399, np.longdouble(1.898 * 10**27))
]
if simulationType == 6:
planets = [ #Planet(kernel, 10, 10, np.longdouble(1.989*10**30)),
Planet(kernel, 399, 399, np.longdouble(5.972 * 10**24)),
Planet(kernel, 399, 399, np.longdouble(1.024 * 10**26))
]
if simulationType == 7:
planets = [ #Planet(kernel, 10, 10, np.longdouble(1.989*10**30)),
Planet(kernel, 399, 399, np.longdouble(5.972 * 10**24)),
Planet(kernel, 399, 399, np.longdouble(5.683 * 10**26))
]
if simulationType == 8:
planets = [ #Planet(kernel, 10, 10, np.longdouble(1.989*10**30)),
Planet(kernel, 399, 399, np.longdouble(5.972 * 10**24)),
Planet(kernel, 399, 399, np.longdouble(8.681 * 10**25))
]
#else
#planets = [Planet(kernel, 399, 399, np.longdouble(5972198600000000000000000)), Planet(null)]
runSimulation(simulationStart.jd, simulationEnd.jd, delta_t, ship, planets)
plot(ship, [planets[1]])
def test_GetMassZero(self):
self.planet = Planet(0.0, 6000.0, (0.0, 0.0))
self.assertEqual(self.planet.get_mass(), 0.0)
def test_GetPosFalseNonZero(self):
self.planet = Planet(0.0, 0.0, (60.2, 40.0))
self.assertNotEqual(self.planet.get_pos(), (-20.0, 30.0))
def test_GetPosNegtive(self):
self.planet = Planet(0.0, 0.0, (-30.3, -20.0))
self.assertEqual(self.planet.get_pos(), (-30.3, -20.0))
def test_GetPosPositive(self):
self.planet = Planet(0.0, 0.0, (60.0, 40.6))
self.assertEqual(self.planet.get_pos(), (60.0, 40.6))
def test_GetPosZero(self):
self.planet = Planet(0.0, 0.0, (0.0, 0.0))
self.assertEqual(self.planet.get_pos(), (0.0, 0.0))
def test_GetRadiusFalseNonZero(self):
self.planet = Planet(0.0, 6000.0, (0.0, 0.0))
self.assertNotEqual(self.planet.get_radius(), 0.0)
def test_GetRadiusZero(self):
self.planet = Planet(0.0, 0.0, (0.0, 0.0))
self.assertEqual(self.planet.get_radius(), 0.0)
def test_GetMassFalseNonZero(self):
self.planet = Planet(6000.0, 100000000.0, (0.0, 0.0))
self.assertNotEqual(self.planet.get_mass(), 131231.0)