def test_SetAccelerationNegative(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) new_x = 123.4 new_y = 5678.9 self.rocket.set_acceleration(-1 * new_x, -1 * new_y) self.assertEqual(self.rocket.get_acceleration(), [-1 * new_x, -1 * new_y])
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)
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)
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)
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_SetMassNParts(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_mass() self.assertEqual(self.rocket.get_mass(), 1000.0) self.rocket.append_part(self.tank_one) self.rocket.set_mass() self.assertEqual(self.rocket.get_mass(), 3000.0)
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_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 test_InitRocketFalseNonZero(self): self.rocket = Rocket([22.0, 23.2], [292.30, 2235.2], [292.0, 282.0]) self.assertNotEqual(self.rocket.pos, [12.0, 13.2]) self.assertNotEqual(self.rocket.velocity, [192.30, 1235.2]) self.assertNotEqual(self.rocket.acceleration, [992.0, 882.0]) self.assertNotEqual(self.rocket.mass, 10.0) self.assertNotEqual(self.rocket.surface, 20.0) self.assertNotEqual(self.rocket.angle, 30.0)
class GetVelocityTest(unittest.TestCase): def test_GetVelocityZero(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.assertEqual(self.rocket.get_velocity(), [0.0, 0.0]) def test_GetVelocityPositive(self): self.rocket = self.rocket = Rocket([0.0, 0.0], [13.3, 222222.2], [0.0, 0.0]) self.assertEqual(self.rocket.get_velocity(), [13.3, 222222.2]) def test_GetVelocityNegative(self): self.rocket = Rocket([0.0, 0.0], [-13.3, -222222.2], [0.0, 0.0]) self.assertEqual(self.rocket.get_velocity(), [-13.3, -222222.2]) def test_GetVelocityFalseNonZero(self): self.rocket = Rocket([0.0, 0.0], [24.2, 1234.5], [0.0, 0.0]) self.assertNotEqual(self.rocket.get_velocity(), [13.3, 222222.2])
class GetAccelerationTest(unittest.TestCase): def test_GetAccelerationZero(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.assertEqual(self.rocket.get_acceleration(), [0.0, 0.0]) def test_GetAccelerationPositive(self): self.rocket = self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [13.3, 222222.2]) self.assertEqual(self.rocket.get_acceleration(), [13.3, 222222.2]) def test_GetAccelerationNegative(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [-13.3, -222222.2]) self.assertEqual(self.rocket.get_acceleration(), [-13.3, -222222.2]) def test_GetAccelerationFalseNonZero(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [24.2, 1234.5]) self.assertNotEqual(self.rocket.get_acceleration(), [13.3, 222222.2])
def test_InitRocketZero(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.assertEqual(self.rocket.rocket_parts, []) self.assertEqual(self.rocket.pos, [0.0, 0.0]) self.assertEqual(self.rocket.velocity, [0.0, 0.0]) self.assertEqual(self.rocket.acceleration, [0.0, 0.0]) self.assertEqual(self.rocket.mass, 0.0) self.assertEqual(self.rocket.surface, 0.0) self.assertEqual(self.rocket.angle, 0.0)
class GetAngleTest(unittest.TestCase): def test_GetAngleZero(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.assertEqual(self.rocket.get_angle(), 0.0) def test_GetAnglePositive(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.rocket.angle = 123.4 self.assertEqual(self.rocket.get_angle(), 123.4) def test_GetAngleNegative(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.rocket.angle = -123.4 self.assertEqual(self.rocket.get_angle(), -123.4) def test_GetAngleFalseNonZero(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.rocket.angle = 285.2 self.assertNotEqual(self.rocket.get_angle(), 123.4)
def test_InitRocketPositive(self): self.rocket = Rocket([12.0, 13.2], [192.30, 1235.2], [992.0, 882.0]) self.nose = RocketPart(1000.2, 231.2, 0.23) self.rocket.rocket_parts.append(self.nose) self.assertEqual(self.rocket.rocket_parts, [self.nose]) self.assertEqual(self.rocket.pos, [12.0, 13.2]) self.assertEqual(self.rocket.velocity, [192.30, 1235.2]) self.assertEqual(self.rocket.acceleration, [992.0, 882.0]) self.assertEqual(self.rocket.mass, 0.0) self.assertEqual(self.rocket.surface, 0.0) self.assertEqual(self.rocket.angle, 0.0)
class GetPostTest(unittest.TestCase): def test_GetPosZero(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.assertEqual(self.rocket.get_pos(), [0.0, 0.0]) def test_GetPosPositive(self): self.rocket = self.rocket = Rocket([13.3, 222222.2], [0.0, 0.0], [0.0, 0.0]) self.assertEqual(self.rocket.get_pos(), [13.3, 222222.2]) def test_GetPosNegative(self): self.rocket = self.rocket = Rocket([-13.3, -222222.2], [0.0, 0.0], [0.0, 0.0]) self.assertEqual(self.rocket.get_pos(), [-13.3, -222222.2]) def test_GetPosFalseNonZero(self): self.rocket = self.rocket = self.rocket = Rocket([24.2, 1234.5], [0.0, 0.0], [0.0, 0.0]) self.assertNotEqual(self.rocket.get_pos(), [13.3, 222222.2])
class GetMassTest(unittest.TestCase): def test_GetMassZero(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.assertEqual(self.rocket.get_mass(), 0.0) def test_GetMassPositive(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.rocket.mass = 123.4 self.assertEqual(self.rocket.get_mass(), 123.4) def test_GetMassNegative(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.rocket.mass = -123.4 with self.assertRaises(ValueError): self.rocket.get_mass() def test_GetMassFalseNonZero(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.rocket.mass = 56789.0 self.assertNotEqual(self.rocket.get_mass(), 123.4)
class GetSurfaceTest(unittest.TestCase): def test_GetSurfaceZero(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.assertEqual(self.rocket.get_surface(), 0.0) def test_GetSurfacePositive(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.rocket.surface = 123.4 self.assertEqual(self.rocket.get_surface(), 123.4) def test_GetSurfaceNegative(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.rocket.surface = -123.4 with self.assertRaises(ValueError): self.rocket.get_surface() def test_GetSurfaceFalseNonZero(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.rocket.surface = 56789.0 self.assertNotEqual(self.rocket.get_surface(), 123.4)
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 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 test_GetAccelerationPositive(self): self.rocket = self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [13.3, 222222.2]) self.assertEqual(self.rocket.get_acceleration(), [13.3, 222222.2])
def test_GetAccelerationZero(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.assertEqual(self.rocket.get_acceleration(), [0.0, 0.0])
def test_GetVelocityFalseNonZero(self): self.rocket = Rocket([0.0, 0.0], [24.2, 1234.5], [0.0, 0.0]) self.assertNotEqual(self.rocket.get_velocity(), [13.3, 222222.2])
def test_GetVelocityNegative(self): self.rocket = Rocket([0.0, 0.0], [-13.3, -222222.2], [0.0, 0.0]) self.assertEqual(self.rocket.get_velocity(), [-13.3, -222222.2])
def test_GetVelocityPositive(self): self.rocket = self.rocket = Rocket([0.0, 0.0], [13.3, 222222.2], [0.0, 0.0]) self.assertEqual(self.rocket.get_velocity(), [13.3, 222222.2])
def test_GetVelocityZero(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.assertEqual(self.rocket.get_velocity(), [0.0, 0.0])
def test_GetPosFalseNonZero(self): self.rocket = self.rocket = self.rocket = Rocket([24.2, 1234.5], [0.0, 0.0], [0.0, 0.0]) self.assertNotEqual(self.rocket.get_pos(), [13.3, 222222.2])
def test_GetPosNegative(self): self.rocket = self.rocket = Rocket([-13.3, -222222.2], [0.0, 0.0], [0.0, 0.0]) self.assertEqual(self.rocket.get_pos(), [-13.3, -222222.2])
def test_GetPosPositive(self): self.rocket = self.rocket = Rocket([13.3, 222222.2], [0.0, 0.0], [0.0, 0.0]) self.assertEqual(self.rocket.get_pos(), [13.3, 222222.2])
def test_GetPosZero(self): self.rocket = Rocket([0.0, 0.0], [0.0, 0.0], [0.0, 0.0]) self.assertEqual(self.rocket.get_pos(), [0.0, 0.0])
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)