def test_getAirProperties_TabulatedAtm(self):
self.simDefinition.setValue("Environment.LaunchSite.elevation", "0")
self.simDefinition.setValue("Environment.AtmosphericPropertiesModel",
"TabulatedAtmosphere")
self.simDefinition.setValue("Environment.TabulatedAtmosphere.filePath",
"MAPLEAF/ENV/US_STANDARD_ATMOSPHERE.txt")
stdAtm = Environment(self.simDefinition, silent=True)
# Sea level
calculatedSeaLevelProperties = stdAtm.getAirProperties(Vector(0, 0, 0))
expectedSeaLevelProperties = EnvironmentalConditions(
0.0, 288.15, 101300, 1.225, 1.789e-5, Vector(0, 0, 0),
Vector(0, 0, 0), Vector(0, 0, 0))
assertIterablesAlmostEqual(self, calculatedSeaLevelProperties,
expectedSeaLevelProperties)
# 1000 m ASL
calculated1kProperties = stdAtm.getAirProperties(Vector(0, 0, 1000))
expected1kProperties = EnvironmentalConditions(1000.0, 8.5 + 273.15,
89880, 1.112, 1.758e-5,
Vector(0, 0, 0),
Vector(0, 0, 0),
Vector(0, 0, 0))
assertIterablesAlmostEqual(self, calculated1kProperties,
expected1kProperties)
# 3750 m ASL
calculated3750Properties = stdAtm.getAirProperties(Vector(0, 0, 3750))
expected3570Properties = EnvironmentalConditions(
3750.0, -9.3575 + 273.15, 63775, 0.841875, 1.66925e-5,
Vector(0, 0, 0), Vector(0, 0, 0), Vector(0, 0, 0))
assertIterablesAlmostEqual(self, calculated3750Properties,
expected3570Properties)
def setUp(self):
simDef = SimDefinition("MAPLEAF/Examples/Simulations/test3.mapleaf", silent=True)
rocketDictReader = SubDictReader("Rocket", simDef)
self.rocket = Rocket(rocketDictReader, silent=True)
self.nosecone = self.rocket.stages[0].getComponentsOfType(NoseCone)[0]
self.bodytube = self.rocket.stages[0].getComponentsOfType(BodyTube)[0]
# Find the Fixed Mass component that's actually just a Fixed Mass, not a child class (Nosecone, Bodytube)
fixedMassComponents = self.rocket.stages[0].getComponentsOfType(FixedMass)
for comp in fixedMassComponents:
if type(comp) == FixedMass:
self.fixedMass = comp
self.environment = Environment(silent=True)
self.currentConditions = self.environment.getAirProperties(Vector(0,0,200)) # m
def createRocket(self):
'''
Do all the same stuff as the parent object, but also re-initialize the environment,
to make sure changes to environmental properties during the parameter sweep take effect
'''
self.environment = Environment(self.simDefinition, silent=self.silent)
return super().createRocket()
def test_getAirProperties_USSTDA(self):
self.simDefinition.setValue("Environment.LaunchSite.elevation", "0")
self.simDefinition.setValue("Environment.AtmosphericPropertiesModel",
"USStandardAtmosphere")
stdAtm = Environment(self.simDefinition, silent=True)
# Sea level
calculatedSeaLevelProperties = stdAtm.getAirProperties(Vector(0, 0, 0))
expectedSeaLevelProperties = EnvironmentalConditions(
0.0, 288.15, 101325, 1.225, 1.789e-5, Vector(0, 0, 0),
Vector(0, 0, 0), Vector(0, 0, 0))
assertIterablesAlmostEqual(self, calculatedSeaLevelProperties,
expectedSeaLevelProperties, 5)
# 1000 m ASL
calculated1kProperties = stdAtm.getAirProperties(Vector(0, 0, 1000))
expected1kProperties = EnvironmentalConditions(1000.0, 8.501 + 273.15,
89876, 1.117, 1.758e-5,
Vector(0, 0, 0),
Vector(0, 0, 0),
Vector(0, 0, 0))
assertIterablesAlmostEqual(self, calculated1kProperties,
expected1kProperties, 0)
# 3750 m ASL
calculated3750Properties = stdAtm.getAirProperties(Vector(0, 0, 3750))
expected3570Properties = EnvironmentalConditions(
3750.0, -9.361 + 273.15, 63693, 0.84115, 1.66925e-5,
Vector(0, 0, 0), Vector(0, 0, 0), Vector(0, 0, 0))
assertIterablesAlmostEqual(self, calculated3750Properties,
expected3570Properties, 0)
# 10,550 m ASL
calculatedProperties = stdAtm.getAirProperties(Vector(0, 0, 10550))
expectedProperties = EnvironmentalConditions(10550, 219.575, 24284,
0.38529, 1.457e-6,
Vector(0, 0, 0),
Vector(0, 0, 0),
Vector(0, 0, 0))
# assertIterablesAlmostEqual(self, calculatedProperties, expectedProperties, 0)
# 85,500 m ASL
calculatedProperties = stdAtm.getAirProperties(Vector(0, 0, 85500))
expectedProperties = EnvironmentalConditions(85500, 187.920, 0.40802,
0.0000075641, 1.25816e-5,
Vector(0, 0, 0),
Vector(0, 0, 0),
Vector(0, 0, 0))
assertIterablesAlmostEqual(self, calculatedProperties,
expectedProperties, 1)
# Check that above 86 km the density is zero
calculatedProperties = stdAtm.getAirProperties(Vector(0, 0, 85500))
def setUp(self):
simDef = SimDefinition("MAPLEAF/Examples/Simulations/test3.mapleaf")
rocketDictReader = SubDictReader("Rocket", simDef)
self.rocket = Rocket(rocketDictReader)
self.environment = Environment(silent=True)
self.currentConditions = self.environment.getAirProperties(
Vector(0, 0, 200)) # m
self.rocketState1 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, 200),
Quaternion(Vector(0, 0, 1), 0),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState2 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, 200),
Quaternion(Vector(1, 0, 0), math.radians(2)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState3 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, 500),
Quaternion(Vector(1, 0, 0), math.radians(2)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState4 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, -200),
Quaternion(Vector(1, 0, 0), math.radians(180)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState5 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, -200),
Quaternion(Vector(1, 0, 0), math.radians(178)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState6 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, -200),
Quaternion(Vector(1, 0, 0), math.radians(182)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState7 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, -200),
Quaternion(Vector(1, 0, 0), math.radians(90)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState8 = RigidBodyState(
Vector(0, 0, 200), Vector(20.04, -0.12, -52.78),
Quaternion(Vector(0, 1, 0), math.radians(90)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
def setUp(self):
removeLogger()
self.dummyVelocity1 = Vector(0, 0, 50)
self.dummyVelocity2 = Vector(1, 0, 20)
self.dummyVelocity3 = Vector(0, 0, -100)
self.dummyOrientation1 = Quaternion(Vector(1, 0, 0), math.radians(2))
self.dummyOrientation2 = Quaternion(Vector(1, 0, 0), math.radians(-2))
self.dummyOrientation3 = Quaternion(Vector(0, 1, 0), math.radians(2))
self.dummyOrientation4 = Quaternion(Vector(1, 0, 0), 0)
self.dummyOrientation5 = Quaternion(Vector(1, 1, 0), math.radians(2))
self.dummyOrientation6 = Quaternion(Vector(1, 0, 0), math.radians(90))
self.environment = Environment(silent=True)
self.currentConditions = self.environment.getAirProperties(
Vector(0, 0, 200))
self.rocketState1 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, 200),
Quaternion(Vector(0, 0, 1), 0),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState3 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, 500),
Quaternion(Vector(1, 0, 0), math.radians(2)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState4 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, -200),
Quaternion(Vector(1, 0, 0), math.radians(180)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState8 = RigidBodyState(
Vector(0, 0, 200), Vector(20.04, -0.12, -52.78),
Quaternion(Vector(0, 1, 0), math.radians(90)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.correctDynamicPressure1 = self.currentConditions.Density * self.rocketState1.velocity.length(
)**2 / 2
self.correctDynamicPressure2 = self.currentConditions.Density * self.rocketState3.velocity.length(
)**2 / 2
def test_constAtmosphere(self):
# Set constant properties in SimDefinition
self.simDefinition.setValue("Environment.AtmosphericPropertiesModel",
"Constant")
self.simDefinition.setValue(
"Environment.ConstantAtmosphere.temp",
"20") # This should be converted to K -> 293.15 expected
self.simDefinition.setValue("Environment.ConstantAtmosphere.pressure",
"101325")
self.simDefinition.setValue("Environment.ConstantAtmosphere.density",
"1.225")
self.simDefinition.setValue("Environment.ConstantAtmosphere.viscosity",
"1.789e-05")
env = Environment(self.simDefinition, silent=True)
constAirProps1 = EnvironmentalConditions(100.0, 293.15, 101325, 1.225,
1.789e-5, Vector(0, 0, 0),
Vector(0, 0, 0),
Vector(0, 0, 0))
props1 = env.getAirProperties(Vector(0, 0, 100))
constAirProps2 = EnvironmentalConditions(1000.0, 293.15, 101325, 1.225,
1.789e-5, Vector(0, 0, 0),
Vector(0, 0, 0),
Vector(0, 0, 0))
props2 = env.getAirProperties(Vector(0, 0, 1000))
constAirProps3 = EnvironmentalConditions(10000.0, 293.15, 101325,
1.225, 1.789e-5,
Vector(0, 0, 0),
Vector(0, 0, 0),
Vector(0, 0, 0))
props3 = env.getAirProperties(Vector(0, 0, 10000))
self.assertEqual(constAirProps1, props1)
self.assertEqual(constAirProps2, props2)
self.assertEqual(constAirProps3, props3)
def test_initPosition(self):
# Modify file to include a launch rail
simDef = SimDefinition(
"MAPLEAF/Examples/Simulations/AdaptTimeStep.mapleaf")
simDef.setValue("Environment.LaunchSite.railLength", "10")
# Initialize environment with launch rail
env = Environment(simDef)
# Check that launch rail has been created
self.assertTrue(env.launchRail != None)
# Check initial launch rail position and direction
initPos = Vector(0, 0,
15 + 755) # Rocket position + launch site elevation
assertVectorsAlmostEqual(self, initPos, env.launchRail.initialPosition)
class TestNosecone(unittest.TestCase):
def setUp(self):
simDef = SimDefinition("MAPLEAF/Examples/Simulations/test3.mapleaf")
rocketDictReader = SubDictReader("Rocket", simDef)
self.rocket = Rocket(rocketDictReader)
self.environment = Environment(silent=True)
self.currentConditions = self.environment.getAirProperties(
Vector(0, 0, 200)) # m
self.rocketState1 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, 200),
Quaternion(Vector(0, 0, 1), 0),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState2 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, 200),
Quaternion(Vector(1, 0, 0), math.radians(2)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState3 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, 500),
Quaternion(Vector(1, 0, 0), math.radians(2)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState4 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, -200),
Quaternion(Vector(1, 0, 0), math.radians(180)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState5 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, -200),
Quaternion(Vector(1, 0, 0), math.radians(178)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState6 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, -200),
Quaternion(Vector(1, 0, 0), math.radians(182)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState7 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, -200),
Quaternion(Vector(1, 0, 0), math.radians(90)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState8 = RigidBodyState(
Vector(0, 0, 200), Vector(20.04, -0.12, -52.78),
Quaternion(Vector(0, 1, 0), math.radians(90)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
def test_noseconeGetPlanformArea(self):
nosecone = self.rocket.stages[0].getComponentsOfType(NoseCone)[0]
self.assertAlmostEqual(nosecone._getPlanformArea(), 0.077573818,
3) #From solidworks
def __init__(self, simDefinitionFilePath=None, simDefinition=None, silent=False):
'''
Inputs:
* simDefinitionFilePath: (string) path to simulation definition file
* fW: (`MAPLEAF.IO.SimDefinition`) object that's already loaded and parsed the desired sim definition file
* silent: (bool) toggles optional outputs to the console
'''
self.simDefinition = loadSimDefinition(simDefinitionFilePath, simDefinition, silent)
''' Instance of `MAPLEAF.IO.SimDefinition`. Defines the current simulation '''
self.environment = Environment(self.simDefinition, silent=silent)
''' Instance of `MAPLEAF.ENV.Environment`. Will be shared by all Rockets created by this sim runner '''
self.stagingIndex = None # Set in self.createRocket
''' (int) Set in `Simulation.createRocket`. Tracks how many stages have been dropped '''
self.silent = silent
''' (bool) '''
self.loggingLevel = int(self.simDefinition.getValue("SimControl.loggingLevel"))
self.computeStageDropPaths = strtobool(self.simDefinition.getValue("SimControl.StageDropPaths.compute"))
def test_LayerBaseProperties(self):
self.simDefinition.setValue("Environment.LaunchSite.elevation", "0")
self.simDefinition.setValue("Environment.AtmosphericPropertiesModel",
"USStandardAtmosphere")
stdAtm = Environment(self.simDefinition, silent=True)
baseHeights = [-2000, 11000, 20000, 32000, 47000, 51000, 71000,
84852] # m
dt_dh = [-6.5e-3, 0, 1.0e-3, 2.8e-3, 0, -2.8e-3, -2.0e-3, 0] # K/m
expectedTemps = [
301.15, 216.65, 216.65, 228.65, 270.65, 270.65, 214.65, 186.95
]
expectedPressures = [
127774, 22632, 5474.8, 868.01, 110.90, 66.938, 3.9564, 0.3732
]
for i in range(len(expectedTemps)):
self.assertAlmostEqual(expectedTemps[i],
stdAtm.atmosphericModel.baseTemps[i], 0)
self.assertAlmostEqual(expectedPressures[i],
stdAtm.atmosphericModel.basePressures[i], 0)
def test_init(self):
# Modify file to include a launch rail
simDef = SimDefinition(
"MAPLEAF/Examples/Simulations/NASATwoStageOrbitalRocket.mapleaf")
simDef.setValue("Environment.LaunchSite.railLength", "15")
# Initialize environment with launch rail
env = Environment(simDef)
# Check that launch rail has been created
self.assertTrue(env.launchRail != None)
# Check initial launch rail position and direction
r = 6378137 + 13.89622
initPos = Vector(r, 0, 0)
assertVectorsAlmostEqual(self, initPos, env.launchRail.initialPosition)
initDir = Vector(math.cos(math.radians(34.78)),
math.sin(math.radians(34.78)), 0).normalize()
assertVectorsAlmostEqual(self, initDir,
env.launchRail.initialDirection)
self.assertAlmostEqual(env.launchRail.length, 15)
class TestAeroParameters(unittest.TestCase):
def setUp(self):
removeLogger()
self.dummyVelocity1 = Vector(0, 0, 50)
self.dummyVelocity2 = Vector(1, 0, 20)
self.dummyVelocity3 = Vector(0, 0, -100)
self.dummyOrientation1 = Quaternion(Vector(1, 0, 0), math.radians(2))
self.dummyOrientation2 = Quaternion(Vector(1, 0, 0), math.radians(-2))
self.dummyOrientation3 = Quaternion(Vector(0, 1, 0), math.radians(2))
self.dummyOrientation4 = Quaternion(Vector(1, 0, 0), 0)
self.dummyOrientation5 = Quaternion(Vector(1, 1, 0), math.radians(2))
self.dummyOrientation6 = Quaternion(Vector(1,0,0), math.radians(90))
self.environment = Environment(silent=True)
self.currentConditions = self.environment.getAirProperties(Vector(0,0,200))
self.rocketState1 = RigidBodyState(Vector(0, 0, 200), Vector(0, 0, 200), Quaternion(Vector(0, 0, 1), 0), AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState3 = RigidBodyState(Vector(0, 0, 200), Vector(0, 0, 500), Quaternion(Vector(1, 0, 0), math.radians(2)), AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState4 = RigidBodyState(Vector(0, 0, 200), Vector(0, 0, -200), Quaternion(Vector(1, 0, 0), math.radians(180)), AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState8 = RigidBodyState(Vector(0, 0, 200), Vector(20.04, -0.12, -52.78), Quaternion(Vector(0, 1, 0), math.radians(90)), AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.correctDynamicPressure1 = self.currentConditions.Density * self.rocketState1.velocity.length()**2 / 2
self.correctDynamicPressure2 = self.currentConditions.Density * self.rocketState3.velocity.length()**2 / 2
def test_getTotalAOA(self):
def getDummyState(vel, orientation):
zeroVec = Vector(0,0,0)
zeroAngVel = AngularVelocity(rotationVector=zeroVec)
return RigidBodyState(zeroVec, vel, orientation, zeroAngVel)
state1 = getDummyState(self.dummyVelocity1, self.dummyOrientation1)
self.assertAlmostEqual(AeroParameters.getTotalAOA(state1, self.currentConditions), math.radians(2))
state2 = getDummyState(self.dummyVelocity1, self.dummyOrientation2)
self.assertAlmostEqual(AeroParameters.getTotalAOA(state2, self.currentConditions), math.radians(2))
state3 = getDummyState(self.dummyVelocity2, self.dummyOrientation3)
self.assertAlmostEqual(AeroParameters.getTotalAOA(state3, self.currentConditions), math.radians(0.862405226))
state4 = getDummyState(self.dummyVelocity2, self.dummyOrientation4)
self.assertAlmostEqual(AeroParameters.getTotalAOA(state4, self.currentConditions), math.radians(2.862405226))
self.assertAlmostEqual(AeroParameters.getTotalAOA(self.rocketState4, self.currentConditions), 0)
state5 = getDummyState(self.dummyVelocity3, self.dummyOrientation6)
self.assertAlmostEqual(AeroParameters.getTotalAOA(state5, self.currentConditions), math.radians(90))
# Prep rocket by calling getLocalFrameAirVel first to cache AOA result, then get cached result from getTotalAOA
def testLocalFrameAirVelAOA(vel, orientation, expectedResult):
state = RigidBodyState(Vector(0,0,0), vel, orientation, AngularVelocity(rotationVector=Vector(0,0,0)))
self.assertAlmostEqual(AeroParameters.getTotalAOA(state, self.currentConditions), math.radians(expectedResult))
testLocalFrameAirVelAOA(self.dummyVelocity1, self.dummyOrientation1, 2)
testLocalFrameAirVelAOA(self.dummyVelocity1, self.dummyOrientation2, 2)
testLocalFrameAirVelAOA(self.dummyVelocity2, self.dummyOrientation3, 0.862405226)
testLocalFrameAirVelAOA(self.dummyVelocity2, self.dummyOrientation4, 2.862405226)
testLocalFrameAirVelAOA(self.rocketState4.velocity, self.rocketState4.orientation, 0)
testLocalFrameAirVelAOA(self.dummyVelocity3, self.dummyOrientation6, 90)
def test_getRocketRollAngle(self):
def getDummyState(vel, orientation):
zeroVec = Vector(0,0,0)
zeroAngVel = AngularVelocity(rotationVector=zeroVec)
return RigidBodyState(zeroVec, vel, orientation, zeroAngVel)
state1 = getDummyState(self.dummyVelocity1, self.dummyOrientation4)
rollAngle1 = AeroParameters.getRollAngle(state1, self.currentConditions)
state2 = getDummyState(self.dummyVelocity1, self.dummyOrientation1)
rollAngle2 = AeroParameters.getRollAngle(state2, self.currentConditions)
state3 = getDummyState(self.dummyVelocity1, self.dummyOrientation2)
rollAngle3 = AeroParameters.getRollAngle(state3, self.currentConditions)
state4 = getDummyState(self.dummyVelocity1, self.dummyOrientation5)
rollAngle4 = AeroParameters.getRollAngle(state4, self.currentConditions)
state5 = getDummyState(self.dummyVelocity2, self.dummyOrientation4)
rollAngle5 = AeroParameters.getRollAngle(state5, self.currentConditions)
state6 = getDummyState(self.dummyVelocity1, self.dummyOrientation3)
rollAngle6 = AeroParameters.getRollAngle(state6, self.currentConditions)
self.assertAlmostEqual(rollAngle1, 180)
self.assertAlmostEqual(rollAngle2, 90)
self.assertAlmostEqual(rollAngle3, 270)
self.assertAlmostEqual(rollAngle4, 135)
self.assertAlmostEqual(rollAngle5, 0)
self.assertAlmostEqual(rollAngle6, 180)
# Prep rocket by calling getLocalFrameAirVel first to cache AOA result, then get cached result from getTotalAOA
def testLocalFrameAirVelRollAngle(vel, orientation, expectedResult):
state = RigidBodyState(Vector(0,0,0), vel, orientation, AngularVelocity(rotationVector=Vector(0,0,0)))
self.assertAlmostEqual(AeroParameters.getRollAngle(state, self.currentConditions), expectedResult)
testLocalFrameAirVelRollAngle(self.dummyVelocity1, self.dummyOrientation4, 180)
testLocalFrameAirVelRollAngle(self.dummyVelocity1, self.dummyOrientation1, 90)
testLocalFrameAirVelRollAngle(self.dummyVelocity1, self.dummyOrientation2, 270)
testLocalFrameAirVelRollAngle(self.dummyVelocity1, self.dummyOrientation5, 135)
testLocalFrameAirVelRollAngle(self.dummyVelocity2, self.dummyOrientation4, 0)
testLocalFrameAirVelRollAngle(self.dummyVelocity1, self.dummyOrientation3, 180)
def test_getNormalAeroForceDirection(self):
zeroAngVel = AngularVelocity(0,0,0)
zeroPos = Vector(0,0,0)
state1 = RigidBodyState(zeroPos, self.dummyVelocity1, self.dummyOrientation1, zeroAngVel)
assertVectorsAlmostEqual(self, AeroParameters.getNormalAeroForceDirection(state1, self.currentConditions), Vector(0, -1, 0))
state2 = RigidBodyState(zeroPos, self.dummyVelocity1, self.dummyOrientation2, zeroAngVel)
assertVectorsAlmostEqual(self, AeroParameters.getNormalAeroForceDirection(state2, self.currentConditions), Vector(0, 1, 0))
state3 = RigidBodyState(zeroPos, self.dummyVelocity1, self.dummyOrientation3, zeroAngVel)
assertVectorsAlmostEqual(self, AeroParameters.getNormalAeroForceDirection(state3, self.currentConditions), Vector(1, 0, 0))
state4 = RigidBodyState(zeroPos, self.dummyVelocity1, self.dummyOrientation4, zeroAngVel)
assertVectorsAlmostEqual(self, AeroParameters.getNormalAeroForceDirection(state4, self.currentConditions), Vector(1, 0, 0))
state5 = RigidBodyState(zeroPos, self.dummyVelocity1, self.dummyOrientation5, zeroAngVel)
assertVectorsAlmostEqual(self, AeroParameters.getNormalAeroForceDirection(state5, self.currentConditions), Vector(0.707, -0.707, 0),3)
assertVectorsAlmostEqual(self, AeroParameters.getNormalAeroForceDirection(self.rocketState8, self.currentConditions), Vector(-0.99999, 0.0022736, 0),3)
# Prep rocket by calling getLocalFrameAirVel first to cache AOA result, then get cached result from getTotalAOA
def testLocalFrameAirVelNormalForceDir(vel, orientation, expectedResult, precision=7):
state = RigidBodyState(Vector(0,0,0), vel, orientation, AngularVelocity(0,0,0))
assertVectorsAlmostEqual(self, AeroParameters.getNormalAeroForceDirection(state, self.currentConditions), expectedResult, precision)
testLocalFrameAirVelNormalForceDir(self.dummyVelocity1, self.dummyOrientation1, Vector(0, -1, 0))
testLocalFrameAirVelNormalForceDir(self.dummyVelocity1, self.dummyOrientation2, Vector(0, 1, 0))
testLocalFrameAirVelNormalForceDir(self.dummyVelocity1, self.dummyOrientation3, Vector(1, 0, 0))
testLocalFrameAirVelNormalForceDir(self.dummyVelocity1, self.dummyOrientation4, Vector(1, 0, 0))
testLocalFrameAirVelNormalForceDir(self.dummyVelocity1, self.dummyOrientation5, Vector(0.707, -0.707, 0), 3)
testLocalFrameAirVelNormalForceDir(self.rocketState8.velocity, self.rocketState8.orientation, Vector(-0.99999, 0.0022736, 0),3)
def test_dynamicPressure(self):
self.assertAlmostEqual(AeroParameters.getDynamicPressure(self.rocketState1,self.currentConditions), self.correctDynamicPressure1)
self.assertAlmostEqual(AeroParameters.getDynamicPressure(self.rocketState3,self.currentConditions), self.correctDynamicPressure2)
def test_getMachNumber(self):
environment = self.environment.getAirProperties(Vector(0,0,0))
# Assumes gamma=1.4, R=287
self.assertAlmostEqual(AeroParameters.getMachNumber(self.rocketState1, environment), 0.587781235)
def test_getReynoldsNumber(self):
environment = self.environment.getAirProperties(Vector(0,0,0))
self.assertAlmostEqual(AeroParameters.getReynoldsNumber(self.rocketState1, environment, 1), 13701279.02972, 2)
def test_getBeta(self):
self.assertAlmostEqual(AeroParameters.getBeta(0.5), 0.86602540)
self.assertAlmostEqual(AeroParameters.getBeta(1.5), 1.118033989)
def test_getAOA(self):
test1State = RigidBodyState(velocity=Vector(1, 0, 1))
expectedAOA = math.radians(-45)
computedAOA = AeroParameters.getAOA(test1State, self.currentConditions)
self.assertAlmostEqual(expectedAOA, computedAOA)
def test_getAOSS(self):
test1State = RigidBodyState(velocity=Vector(0, 1, 1))
expectedAOA = math.radians(45)
computedAOA = AeroParameters.getAOSS(test1State, self.currentConditions)
self.assertAlmostEqual(expectedAOA, computedAOA)
class TestBodyTube(unittest.TestCase):
def setUp(self):
simDef = SimDefinition("MAPLEAF/Examples/Simulations/test3.mapleaf")
rocketDictReader = SubDictReader("Rocket", simDef)
self.rocket = Rocket(rocketDictReader)
self.environment = Environment(silent=True)
self.currentConditions = self.environment.getAirProperties(
Vector(0, 0, 200)) # m
self.rocketState1 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, 200),
Quaternion(Vector(0, 0, 1), 0),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState2 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, 200),
Quaternion(Vector(1, 0, 0), math.radians(2)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState3 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, 500),
Quaternion(Vector(1, 0, 0), math.radians(2)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
# def test_bodytubeOpenRocketAeroCoefficients(self):
# time = 1
# bodyTube = self.rocket.stages[0].getComponentsOfType(Bodytube)[0]
# aeroForce = bodyTube.getAppliedForce(self.rocketState1, time, self.currentConditions, self.rocket.getCG(0, self.rocketState1))
# normalForceDirection = AeroParameters.getNormalAeroForceDirection(self.rocketState1, self.currentConditions)
# axialForceDirection = Vector(0, 0, -1) #By definition of axial force
# normalForceHandCalc = 0
# axialForceHandCalc = 86.86005
# CpWRTNoseconeTip = Vector(0, 0, -0.762 - 1) #Planform centroid
# normalForce = normalForceDirection.__mul__(normalForceHandCalc)
# axialForce = axialForceDirection.__mul__(axialForceHandCalc)
# appliedNormalForce = ForceMomentSystem(normalForce, CpWRTNoseconeTip)
# appliedAxialForce = ForceMomentSystem(axialForce, CpWRTNoseconeTip)
# correctAeroForce = appliedNormalForce + appliedAxialForce
# assertVectorsAlmostEqual(self, bodyTube.CPLocation, Vector(0,0,-1.762))
# assertForceMomentSystemsAlmostEqual(self, aeroForce, correctAeroForce, 4)
# aeroForce = bodyTube.getAppliedForce(self.rocketState2, time, self.currentConditions, self.rocket.getCG(0, self.rocketState2))
# normalForceDirection = AeroParameters.getNormalAeroForceDirection(self.rocketState2, self.currentConditions)
# axialForceDirection = Vector(0, 0, -1) #By definition of axial force
# normalForceHandCalc = 9.820304
# axialForceHandCalc = 87.857221
# CpWRTNoseconeTip = Vector(0, 0, -1.762) #Planform centroid
# normalForce = normalForceDirection.__mul__(normalForceHandCalc)
# axialForce = axialForceDirection.__mul__(axialForceHandCalc)
# appliedNormalForce = ForceMomentSystem(normalForce, CpWRTNoseconeTip)
# appliedAxialForce = ForceMomentSystem(axialForce, CpWRTNoseconeTip)
# correctAeroForce = appliedNormalForce + appliedAxialForce
# assertVectorsAlmostEqual(self, bodyTube.CPLocation, Vector(0,0,-1.762))
# assertForceMomentSystemsAlmostEqual(self, aeroForce, correctAeroForce, 6)
# aeroForce = bodyTube.getAppliedForce(self.rocketState3, time, self.currentConditions, self.rocket.getCG(0, self.rocketState3))
# normalForceDirection = AeroParameters.getNormalAeroForceDirection(self.rocketState3, self.currentConditions)
# axialForceDirection = Vector(0, 0, -1) #By definition of axial force
# normalForceHandCalc = 61.3769010
# axialForceHandCalc = 483.10726
# CpWRTNoseconeTip = Vector(0, 0, -0.762 - 1) #Planform centroid
# normalForce = normalForceDirection.__mul__(normalForceHandCalc)
# axialForce = axialForceDirection.__mul__(axialForceHandCalc)
# appliedNormalForce = ForceMomentSystem(normalForce, CpWRTNoseconeTip)
# appliedAxialForce = ForceMomentSystem(axialForce, CpWRTNoseconeTip)
# correctAeroForce = appliedNormalForce + appliedAxialForce
# assertVectorsAlmostEqual(self, bodyTube.CPLocation, Vector(0,0,-1.762))
# assertForceMomentSystemsAlmostEqual(self, aeroForce, correctAeroForce, 5)
def test_bodyTubeDampingMoment(self):
simRunner = Simulation("MAPLEAF/Examples/Simulations/test3.mapleaf",
silent=True)
rocket = simRunner.createRocket()
bodyTube = rocket.stages[0].getComponentsOfType(BodyTube)[0]
# Create a rigid body state rotating at 2 rad/s about the x-axis
pos = Vector(0, 0, 0)
vel = Vector(0, 0, 0)
orientation = Quaternion(1, 0, 0, 0)
angVel = AngularVelocity(2, 0, 0)
xRotatingState = RigidBodyState(pos, vel, orientation, angVel)
envConditions = rocket.environment.getAirProperties(Vector(0, 0, 0))
#### CoR = Middle of the body tube ####
fakeRocketCG = Vector(0, 0, -1.762)
# Get computed (numerically-integrated) result
calculatedDampingMoment = bodyTube._computeLongitudinalDampingMoments(
xRotatingState, envConditions, fakeRocketCG, nSegments=100)
# Compute analytical result (Niskanen Eqn 3.58) * 2 for both halves of the body tube (above and below center of rotation)
expectedXDampingMoment = 2 * 0.275 * envConditions.Density * (
bodyTube.outerDiameter / 2) * 4
expectedTotalDampingMoment = Vector(-expectedXDampingMoment, 0, 0)
# Compare
assertVectorsAlmostEqual(self, calculatedDampingMoment,
expectedTotalDampingMoment, 4)
#### Case 2: CoR at End of Body Tube ####
fakeRocketCG = Vector(0, 0, -2.762)
# Get computed (numerically-integrated) result
calculatedDampingMoment = bodyTube._computeLongitudinalDampingMoments(
xRotatingState, envConditions, fakeRocketCG, nSegments=150)
# Factor of 16 from moving to a tube length of two (2^4 = 16), but dividing by two (one half instead of two)
expectedTotalDampingMoment *= 8
# Compare
assertVectorsAlmostEqual(self, calculatedDampingMoment,
expectedTotalDampingMoment, 4)
class TestRocketComponents(unittest.TestCase):
def setUp(self):
simDef = SimDefinition("MAPLEAF/Examples/Simulations/test3.mapleaf", silent=True)
rocketDictReader = SubDictReader("Rocket", simDef)
self.rocket = Rocket(rocketDictReader, silent=True)
self.nosecone = self.rocket.stages[0].getComponentsOfType(NoseCone)[0]
self.bodytube = self.rocket.stages[0].getComponentsOfType(BodyTube)[0]
# Find the Fixed Mass component that's actually just a Fixed Mass, not a child class (Nosecone, Bodytube)
fixedMassComponents = self.rocket.stages[0].getComponentsOfType(FixedMass)
for comp in fixedMassComponents:
if type(comp) == FixedMass:
self.fixedMass = comp
self.environment = Environment(silent=True)
self.currentConditions = self.environment.getAirProperties(Vector(0,0,200)) # m
#### FixedMass ####
def test_getInertia(self):
noseconeInertia = Inertia(Vector(0.001,0.001,0.001), Vector(0,0,-0.2), mass=5)
bodytubeInertia = Inertia(Vector(0.001,0.001,0.001), Vector(0,0,-1), mass=50)
generalInertia = Inertia(Vector(0.001,0.001,0.001), Vector(0,0,0.0), mass=100)
state = self.rocket.rigidBody.state
self.almostEqualVectors(self.nosecone.getInertia(0, state).CG, noseconeInertia.CG)
self.assertEqual(self.nosecone.getInertia(0, state).mass, noseconeInertia.mass)
self.almostEqualVectors(self.bodytube.getInertia(0, state).CG, bodytubeInertia.CG)
self.assertEqual(self.bodytube.getInertia(0, state).mass, bodytubeInertia.mass)
self.almostEqualVectors(self.fixedMass.getInertia(0, state).CG, generalInertia.CG)
self.assertEqual(self.fixedMass.getInertia(0, state).mass, generalInertia.mass)
### FixedForce ###
def test_fixedForceInit(self):
simDef = SimDefinition("MAPLEAF/Examples/Simulations/FixedForce.mapleaf", silent=True)
rocketDictReader = SubDictReader("Rocket", simDef)
rocket = Rocket(rocketDictReader, silent=True)
fixedForce = rocket.stages[0].getComponentsOfType(FixedForce)[0]
expectedFMS = ForceMomentSystem(Vector(0,0,0), Vector(0,0,0), Vector(0,1,0))
assertForceMomentSystemsAlmostEqual(self, fixedForce.force, expectedFMS)
def test_getFixedForceInertia(self):
simDef = SimDefinition("MAPLEAF/Examples/Simulations/FixedForce.mapleaf", silent=True)
rocketDictReader = SubDictReader("Rocket", simDef)
rocket = Rocket(rocketDictReader, silent=True)
fixedForce = rocket.stages[0].getComponentsOfType(FixedForce)[0]
inertia = fixedForce.getInertia(0, "fakeState")
expectedInertia = Inertia(Vector(0,0,0), Vector(0,0,0), 0)
self.assertEqual(inertia, expectedInertia)
def test_getFixedForce(self):
simDef = SimDefinition("MAPLEAF/Examples/Simulations/FixedForce.mapleaf", silent=True)
rocketDictReader = SubDictReader("Rocket", simDef)
rocket = Rocket(rocketDictReader, silent=True)
fixedForce = rocket.stages[0].getComponentsOfType(FixedForce)[0]
force = fixedForce.getAppliedForce("fakeState", 0, "fakeEnv", Vector(0,0,0))
expectedForce = ForceMomentSystem(Vector(0,0,0), moment=Vector(0,1,0))
self.assertEqual(force.force, expectedForce.force)
self.assertEqual(force.moment, expectedForce.moment)
### TabulatedAeroForce ###
def test_TabulatedAeroForce(self):
# Init rocket that uses tabulated aero data
simDef = SimDefinition("MAPLEAF/Examples/Simulations/NASATwoStageOrbitalRocket.mapleaf", silent=True)
rocketDictReader = SubDictReader("Rocket", simDef)
rocket = Rocket(rocketDictReader, silent=True)
comp1, comp2, comp3 = rocket.stages[0].getComponentsOfType(TabulatedAeroForce)
if comp1.Lref == 3.0:
tabMoment = comp1
tabFOrce = comp2
else:
tabMoment = comp2
tabForce = comp1
zeroAOAState = RigidBodyState(Vector(0,0,0), Vector(0,0,100), Quaternion(1,0,0,0), Vector(0,0,0))
# CD, CL, CMx, CMy, CMz
expectedAero = [ 0.21, 0, 0, 0, 0 ]
calculatedAero = tabForce._getAeroCoefficients(zeroAOAState, self.currentConditions)
assertIterablesAlmostEqual(self, expectedAero, calculatedAero)
expectedAero = [ 0, 0, 0, 0, 0 ]
calculatedAero = tabMoment._getAeroCoefficients(zeroAOAState, self.currentConditions)
assertIterablesAlmostEqual(self, expectedAero, calculatedAero)
#### Utilities ####
def almostEqualVectors(self, Vector1, Vector2, n=7):
self.assertAlmostEqual(Vector1.X, Vector2.X, n)
self.assertAlmostEqual(Vector1.Y, Vector2.Y, n)
self.assertAlmostEqual(Vector1.Z, Vector2.Z, n)
class TestAeroFunctions(unittest.TestCase):
def setUp(self):
removeLogger()
self.dummyVelocity1 = Vector(0, 0, 50)
self.dummyVelocity2 = Vector(1, 0, 20)
self.dummyVelocity3 = Vector(0, 0, -100)
self.dummyOrientation1 = Quaternion(Vector(1, 0, 0), math.radians(2))
self.dummyOrientation2 = Quaternion(Vector(1, 0, 0), math.radians(-2))
self.dummyOrientation3 = Quaternion(Vector(0, 1, 0), math.radians(2))
self.dummyOrientation4 = Quaternion(Vector(1, 0, 0), 0)
self.dummyOrientation5 = Quaternion(Vector(1, 1, 0), math.radians(2))
self.dummyOrientation6 = Quaternion(Vector(1, 0, 0), math.radians(90))
self.environment = Environment(silent=True)
self.currentConditions = self.environment.getAirProperties(
Vector(0, 0, 200))
self.rocketState1 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, 200),
Quaternion(Vector(0, 0, 1), 0),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState3 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, 500),
Quaternion(Vector(1, 0, 0), math.radians(2)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState4 = RigidBodyState(
Vector(0, 0, 200), Vector(0, 0, -200),
Quaternion(Vector(1, 0, 0), math.radians(180)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState8 = RigidBodyState(
Vector(0, 0, 200), Vector(20.04, -0.12, -52.78),
Quaternion(Vector(0, 1, 0), math.radians(90)),
AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.correctDynamicPressure1 = self.currentConditions.Density * self.rocketState1.velocity.length(
)**2 / 2
self.correctDynamicPressure2 = self.currentConditions.Density * self.rocketState3.velocity.length(
)**2 / 2
def test_BarrowmanCPLocation(self):
# Check that for a cone, XCP = 0.666 Length
length = 1
baseArea = 1
tipArea = 0
volume = baseArea * length / 3
XCP_cone = AeroFunctions.Barrowman_GetCPLocation(
length, tipArea, baseArea, volume)
self.assertAlmostEqual(XCP_cone.Z, -0.666666666)
# Check that for a tangent ogive nosecone, XCP = 0.466 Length
SimRunner = Simulation("MAPLEAF/Examples/Simulations/test3.mapleaf",
silent=True)
rocket = SimRunner.createRocket()
rocketNosecone = rocket.stages[0].getComponentsOfType(NoseCone)[0]
noseconeLength = rocketNosecone.length
expectedCp = rocketNosecone.position + Vector(
0, 0, -0.46666 * noseconeLength)
actualCp = rocketNosecone.CPLocation
assertVectorsAlmostEqual(self, expectedCp, actualCp, 2)
def test_CPZ(self):
force = Vector(0, 1, 0)
location = Vector(0, 0, 0)
moment = Vector(1, 0, 0)
testForce = ForceMomentSystem(force, location, moment)
expectedCPZ = -1
calculatedCPZ = AeroFunctions._getCPZ(testForce)
self.assertAlmostEqual(expectedCPZ, calculatedCPZ)
def test_getDragToAxialForceFactor(self):
# Should be 0 at 0, 1.3 at 17, and 0 at 90
AOAsToTest = [0, 17, 90]
AOAsToTest = [math.radians(AOA) for AOA in AOAsToTest]
results = [
AeroFunctions.getDragToAxialForceFactor(AOA) for AOA in AOAsToTest
]
expectedResults = [1, 1.3, 0]
for i in range(3):
self.assertAlmostEqual(results[i], expectedResults[i], 3)
def test_getSkinFrictionCoeff(self):
env = self.currentConditions
length = 1
def checkSkinFriction(Re,
roughness,
Mach,
expectedCf,
fullyTurbulent=True):
state = createStateWithRe(Re, env, length)
coeff = AeroFunctions.getSkinFrictionCoefficient(
state, env, length, Mach, roughness, fullyTurbulent)
self.assertAlmostEqual(coeff, expectedCf)
# Min Re
checkSkinFriction(0, 0, 0, 0.0148)
checkSkinFriction(9999, 0, 0, 0.0148)
# Fully Turbulent Flow
checkSkinFriction(10000, 0, 0, 0.014815997)
checkSkinFriction(100000, 0, 0, 0.007343512274)
# Transitional Flow
checkSkinFriction(10000, 0, 0, 0.01328, False)
checkSkinFriction(500001, 0, 0, 0.001641693326, False)
checkSkinFriction(5000000, 0, 0, 0.002911385467, False)
# Flow with roughness
roughness = 0.00002
Recrit = 3888660.338
checkSkinFriction(3888500, 0.00002, 0, 0.002958676686,
False) # Check transitional flow again
checkSkinFriction(3888500, 0.00002, 0, 0.003395863262,
True) # Check turbulent flow again
checkSkinFriction(3888700, 0.00002, 0, 0.003675834736,
False) # Check roughness-determined friction
checkSkinFriction(3888700, 0.00002, 0, 0.003675834736,
True) # Check roughness-determined friction
def test_getSubsonicCompressibilityCorrectionFactor(self):
smooth = True
Mach = 0.5
expected = 0.975
self.assertAlmostEqual(
AeroFunctions._subSonicSkinFrictionCompressiblityCorrectionFactor(
Mach, smooth), expected)
smooth = False
Mach = 0.5
expected = 0.97
self.assertAlmostEqual(
AeroFunctions._subSonicSkinFrictionCompressiblityCorrectionFactor(
Mach, smooth), expected)
def test_supersonicSkinFrictionCompressibilityCorrection(self):
smooth = True
Mach = 1.5
expected = 0.844791628
self.assertAlmostEqual(
AeroFunctions.
_supersonicSkinFrictionCompressiblityCorrectionFactor(
Mach, smooth), expected)
def test_getCylindricalSkinFriction(self):
env = self.currentConditions
length = 1
Mach = 0
rough = 0
Area = 1
finenessRatio = 2
turbulent = True
def checkSkinFriction(Re,
roughness,
Mach,
finenessRatio,
expectedCf,
fullyTurbulent=True):
state = createStateWithRe(Re, env, length)
coeff, rollDamping = AeroFunctions.getCylindricalSkinFrictionDragCoefficientAndRollDampingMoment(
state, env, length, Mach, roughness, 1, 1, finenessRatio,
fullyTurbulent)
self.assertAlmostEqual(coeff, expectedCf)
self.assertAlmostEqual(rollDamping.length(), 0)
checkSkinFriction(9999, rough, Mach, finenessRatio, 0.0185)
def test_BarrowmanGetCN(self):
AOA = 0.1 #rad
Aref = 1
xArea_top = 1
xArea_bottom = 2
expected = 0.199666833
self.assertAlmostEqual(
AeroFunctions.Barrowman_GetCN(AOA, Aref, xArea_top, xArea_bottom),
expected)
def test_BarrowmanCPLocation(self):
length = 1
xArea_top = 1
xArea_bottom = 2
vol = 1.5
expected = Vector(0, 0, -0.5)
assertVectorsAlmostEqual(
self, expected,
AeroFunctions.Barrowman_GetCPLocation(length, xArea_top,
xArea_bottom, vol))
xArea_top = 1
xArea_bottom = 1
expected = Vector(0, 0, -0.5)
assertVectorsAlmostEqual(
self, expected,
AeroFunctions.Barrowman_GetCPLocation(length, xArea_top,
xArea_bottom, vol))
def __init__(self, rocketDictReader, silent=False, stageToInitialize=None, simRunner=None, environment=None):
'''
Initialization of Rocket(s) is most easily completed through an instance of Simulation
To get a single Rocket object, initialize a Simulation and call `MAPLEAF.SimulationRunners.Simulation.createRocket()`.
This will return a Rocket initialized on the pad with all its stages, ready for flight.
If initializing manually, can either provide fileName or simDefinition. If a simDefinition is provided, it will be used and fileName will be ignored.
Inputs:
* rocketDictReader: (`MAPLEAF.IO.SubDictReader`) SubDictReader pointed at the "Rocket" dictionary of the desired simulation definition file.
* silent: (bool) controls console output
* stageToInitialize: (int or None) controls whether to initialize a complete Rocket or a single (usually dropped) stage. None = initialize complete rocket. n = initialize only stage n, where n >= 1.
* simRunner: (`MAPLEAF.SimulationRunners.Simulation`) reference to the current simulation driver/runner
* environment: (`MAPLEAF.ENV.Environment`) environment model from which the rocket will retrieve atmospheric properties and wind speeds
'''
self.rocketDictReader = rocketDictReader
self.simDefinition = rocketDictReader.simDefinition
self.simRunner = simRunner
''' Parent instance of `MAPLEAF.SimulationRunners.Simulation` (or derivative sim runner). This is usually the object that has created the current instance of Rocket. '''
self.environment = environment
''' Instance of `MAPLEAF.ENV.Environment` '''
if self.environment == None:
# If no environment is passed in, create one
self.environment = Environment(self.simDefinition, silent=silent)
self.name = rocketDictReader.getString("name")
self.silent = silent
''' Controls output to console '''
self.stage = stageToInitialize
''' If controls whether the whole rocket is initialized (if == None), or a single stage is initialized (Integer stage number) '''
self.stages = []
'''
A list of `MAPLEAF.Rocket.Stage` objects that make up the rocket, ordered from top to bottom.
Populated by `_initializeStages`.
'''
self.recoverySystem = None
'''
Reference to the current Rocket's (which can represent a dropped stage) recovery system. Only a single recovery system is allowed per stage.
Set in `MAPLEAF.Rocket.RecoverySystem.__init__`
'''
self.rigidBody = None
'''
(`MAPLEAF.Motion.RigidBody` or `MAPLEAF.Motion.RigidBody_3DoF`) Responsible for motion integration.
Set in `_initializeRigidBody()`.
'''
self.isUnderChute = False
''' (bool) Controlled by `MAPLEAF.Rocket.Recovery.RecoverySystem._deployNextStage()` '''
self.mainChuteDeployTime = None
''' (float) Filled in during flight by `MAPLEAF.Rocket.Recovery.RecoverySystem._deployNextStage()` '''
self.engineShutOffTime = None
''' (float) Filled in by `MAPLEAF.Rocket.Propulsion.TabulatedMotor.__init__()` upon initialization '''
self.turbulenceOffWhenUnderChute = rocketDictReader.getBool("Environment.turbulenceOffWhenUnderChute")
''' (bool) '''
self.maxDiameter = self._getMaxBodyTubeDiameter()
''' (float) Holds maximum constant-size body tube diameter, from bodytube components in stages '''
self.Aref = math.pi * self.maxDiameter**2 / 4
'''
Reference area for force and moment coefficients.
Maximum rocket cross-sectional area. Remains constant during flight to retain a 1:1 relationship b/w coefficients in different parts of flight.
Always based on the maximum body tube diameter in the fully-assembled rocket.
'''
# TODO: Remove
self.targetLocation = None
self.simEventDetector = SimEventDetector(self)
''' (`MAPLEAF.Rocket.SimEventDetector`) Used to trigger things like recovery systems and staging '''
self.eventTimeStep = rocketDictReader.getFloat("SimControl.TimeStepAdaptation.eventTimingAccuracy")
''' If using an adaptive time stepping method, the time step will be overridden near non-time-deterministic discrete events, possibly all the way down to this minimum value '''
self.addZeroLengthBoatTailsToAccountForBaseDrag = rocketDictReader.getBool("Aero.addZeroLengthBoatTailsToAccountForBaseDrag")
''' Controls whether zero-length boat tails are automatically added to the bottom of rockets without them, to make sure base drag is accounted for '''
self.fullyTurbulentBL = rocketDictReader.getBool("Aero.fullyTurbulentBL")
''' Controls whether skin friction is solved assuming a fully turbulent BL or using laminar/transitional flow at lower Reynolds numbers '''
self.surfaceRoughness = rocketDictReader.getFloat("Aero.surfaceRoughness")
''' Default surface roughness for all rocket components '''
self.finenessRatio = None
''' Used in some aerodynamic functions. Updated after initializing subcomponents, and throughout the flight. None if no BodyComponent(s) are present in the rocket '''
self.engineShutOff = False
'''Used to shut off engines in MAPLEAF.Rocket.Propulsion.DefinedMotor class. Currently set in MAPLE_AF.GNC.Navigation'''
#### Init Hardware in the loop ####
subDicts = rocketDictReader.getImmediateSubDicts()
if "Rocket.HIL" in subDicts:
self.hardwareInTheLoopControl = "yes"
quatUpdateRate = rocketDictReader.getInt("HIL.quatUpdateRate")
posUpdateRate = rocketDictReader.getInt("HIL.posUpdateRate")
velUpdateRate = rocketDictReader.getInt("HIL.velUpdateRate")
teensyComPort = rocketDictReader.getString("HIL.teensyComPort")
imuComPort = rocketDictReader.getString("HIL.imuComPort")
teensyBaudrate = rocketDictReader.getInt("HIL.teensyBaudrate")
imuBaudrate = rocketDictReader.getInt("HIL.imuBaudrate")
self.hilInterface = HILInterface(quatUpdateRate,posUpdateRate,velUpdateRate, teensyComPort, imuComPort, teensyBaudrate, imuBaudrate)
else:
self.hardwareInTheLoopControl = "no"
#### Initialize Logging ####
self.timeStepLog = None
''' Log containing one entry per time step, logs rocket state. None if logging level == 0 '''
self.derivativeEvaluationLog = None
''' Log containing one entry per rocket motion derivative evaluation, contains component forces. None if logging level < 2 '''
loggingLevel = int(self.simDefinition.getValue("SimControl.loggingLevel"))
self.loggingLevel = loggingLevel
if loggingLevel > 0:
# Create the time step log and add columns to track the rocket state between each time step
self.timeStepLog = TimeStepLog()
zeroVector = Vector(0,0,0)
self.timeStepLog.addColumn("Position(m)", zeroVector)
self.timeStepLog.addColumn("Velocity(m/s)", zeroVector)
self.timeStepLog.addColumn("OrientationQuaternion", Quaternion(0,0,0,0))
self.timeStepLog.addColumn("EulerAngle(rad)", zeroVector)
self.timeStepLog.addColumn("AngularVelocity(rad/s)", zeroVector)
if "Adapt" in self.simDefinition.getValue("SimControl.timeDiscretization"):
self.timeStepLog.addColumn("EstimatedIntegrationError", 0)
if loggingLevel > 1:
self.derivativeEvaluationLog = Log()
zeroVector = Vector(0,0,0)
self.derivativeEvaluationLog.addColumn("Position(m)", zeroVector)
self.derivativeEvaluationLog.addColumn("Velocity(m/s)", zeroVector)
self.derivativeEvaluationLog.addColumn("OrientationQuaternion", Quaternion(0,0,0,0))
self.derivativeEvaluationLog.addColumn("AngularVelocity(rad/s)", zeroVector)
self.derivativeEvaluationLog.addColumn("CG(m)", zeroVector)
self.derivativeEvaluationLog.addColumn("MOI(kg*m^2)", zeroVector)
self.derivativeEvaluationLog.addColumn("Mass(kg)", 0)
self.derivativeEvaluationLog.addColumn("Wind(m/s)", zeroVector)
self.derivativeEvaluationLog.addColumn("AirDensity(kg/m^3)", 0)
self.derivativeEvaluationLog.addColumn("Mach", 0)
self.derivativeEvaluationLog.addColumn("UnitRe", 0)
self.derivativeEvaluationLog.addColumn("AOA(deg)", 0)
self.derivativeEvaluationLog.addColumn("RollAngle(deg)", 0)
self.derivativeEvaluationLog.addColumn("CPZ(m)", 0)
self.derivativeEvaluationLog.addColumn("AeroF(N)", zeroVector)
self.derivativeEvaluationLog.addColumn("AeroM(Nm)", zeroVector)
self.derivativeEvaluationLog.addColumn("GravityF(N)", zeroVector)
self.derivativeEvaluationLog.addColumn("TotalF(N)", zeroVector)
#### Init Components ####
self._createStages()
self._initializeRigidBody()
self._switchToStatefulRigidBodyIfRequired()
self._sortStagesAndComponents()
self._initializeStagingTriggers()
self._precomputeComponentProperties()
#### Init Parent classes ####
CompositeObject.__init__(self, self.stages)
self._updateFinenessRatio()
# Adjust rigid body state position to correspond to the rocket's CG instead of nose cone tip position
self._moveStatePositionToCG()
#### Init Guidance/Navigation/Control System (if required) ####
self.controlSystem = None
''' None for uncontrolled rockets. `MAPLEAF.GNC.ControlSystems.RocketControlSystem` for controlled rockets '''
if ( rocketDictReader.tryGetString("ControlSystem.controlledSystem") != None or rocketDictReader.tryGetString("ControlSystem.MomentController.Type") == "IdealMomentController") and stageToInitialize == None:
# Only create a control system if this is NOT a dropped stage
ControlSystemDictReader = SubDictReader("Rocket.ControlSystem", simDefinition=self.simDefinition)
controlSystemLogging = loggingLevel > 3
self.controlSystem = RocketControlSystem(ControlSystemDictReader, self, log=controlSystemLogging, silent=silent)
class Rocket(CompositeObject):
'''
Class used to represent a single flying rigid body composed of `MAPLEAF.Rocket.Stage` objects.
New instances of this class are also created to model the flight of dropped stages.
'''
#### Initialization ####
def __init__(self, rocketDictReader, silent=False, stageToInitialize=None, simRunner=None, environment=None):
'''
Initialization of Rocket(s) is most easily completed through an instance of Simulation
To get a single Rocket object, initialize a Simulation and call `MAPLEAF.SimulationRunners.Simulation.createRocket()`.
This will return a Rocket initialized on the pad with all its stages, ready for flight.
If initializing manually, can either provide fileName or simDefinition. If a simDefinition is provided, it will be used and fileName will be ignored.
Inputs:
* rocketDictReader: (`MAPLEAF.IO.SubDictReader`) SubDictReader pointed at the "Rocket" dictionary of the desired simulation definition file.
* silent: (bool) controls console output
* stageToInitialize: (int or None) controls whether to initialize a complete Rocket or a single (usually dropped) stage. None = initialize complete rocket. n = initialize only stage n, where n >= 1.
* simRunner: (`MAPLEAF.SimulationRunners.Simulation`) reference to the current simulation driver/runner
* environment: (`MAPLEAF.ENV.Environment`) environment model from which the rocket will retrieve atmospheric properties and wind speeds
'''
self.rocketDictReader = rocketDictReader
self.simDefinition = rocketDictReader.simDefinition
self.simRunner = simRunner
''' Parent instance of `MAPLEAF.SimulationRunners.Simulation` (or derivative sim runner). This is usually the object that has created the current instance of Rocket. '''
self.environment = environment
''' Instance of `MAPLEAF.ENV.Environment` '''
if self.environment == None:
# If no environment is passed in, create one
self.environment = Environment(self.simDefinition, silent=silent)
self.name = rocketDictReader.getString("name")
self.silent = silent
''' Controls output to console '''
self.stage = stageToInitialize
''' If controls whether the whole rocket is initialized (if == None), or a single stage is initialized (Integer stage number) '''
self.stages = []
'''
A list of `MAPLEAF.Rocket.Stage` objects that make up the rocket, ordered from top to bottom.
Populated by `_initializeStages`.
'''
self.recoverySystem = None
'''
Reference to the current Rocket's (which can represent a dropped stage) recovery system. Only a single recovery system is allowed per stage.
Set in `MAPLEAF.Rocket.RecoverySystem.__init__`
'''
self.rigidBody = None
'''
(`MAPLEAF.Motion.RigidBody` or `MAPLEAF.Motion.RigidBody_3DoF`) Responsible for motion integration.
Set in `_initializeRigidBody()`.
'''
self.isUnderChute = False
''' (bool) Controlled by `MAPLEAF.Rocket.Recovery.RecoverySystem._deployNextStage()` '''
self.mainChuteDeployTime = None
''' (float) Filled in during flight by `MAPLEAF.Rocket.Recovery.RecoverySystem._deployNextStage()` '''
self.engineShutOffTime = None
''' (float) Filled in by `MAPLEAF.Rocket.Propulsion.TabulatedMotor.__init__()` upon initialization '''
self.turbulenceOffWhenUnderChute = rocketDictReader.getBool("Environment.turbulenceOffWhenUnderChute")
''' (bool) '''
self.maxDiameter = self._getMaxBodyTubeDiameter()
''' (float) Holds maximum constant-size body tube diameter, from bodytube components in stages '''
self.Aref = math.pi * self.maxDiameter**2 / 4
'''
Reference area for force and moment coefficients.
Maximum rocket cross-sectional area. Remains constant during flight to retain a 1:1 relationship b/w coefficients in different parts of flight.
Always based on the maximum body tube diameter in the fully-assembled rocket.
'''
# TODO: Remove
self.targetLocation = None
self.simEventDetector = SimEventDetector(self)
''' (`MAPLEAF.Rocket.SimEventDetector`) Used to trigger things like recovery systems and staging '''
self.eventTimeStep = rocketDictReader.getFloat("SimControl.TimeStepAdaptation.eventTimingAccuracy")
''' If using an adaptive time stepping method, the time step will be overridden near non-time-deterministic discrete events, possibly all the way down to this minimum value '''
self.addZeroLengthBoatTailsToAccountForBaseDrag = rocketDictReader.getBool("Aero.addZeroLengthBoatTailsToAccountForBaseDrag")
''' Controls whether zero-length boat tails are automatically added to the bottom of rockets without them, to make sure base drag is accounted for '''
self.fullyTurbulentBL = rocketDictReader.getBool("Aero.fullyTurbulentBL")
''' Controls whether skin friction is solved assuming a fully turbulent BL or using laminar/transitional flow at lower Reynolds numbers '''
self.surfaceRoughness = rocketDictReader.getFloat("Aero.surfaceRoughness")
''' Default surface roughness for all rocket components '''
self.finenessRatio = None
''' Used in some aerodynamic functions. Updated after initializing subcomponents, and throughout the flight. None if no BodyComponent(s) are present in the rocket '''
self.engineShutOff = False
'''Used to shut off engines in MAPLEAF.Rocket.Propulsion.DefinedMotor class. Currently set in MAPLE_AF.GNC.Navigation'''
#### Init Hardware in the loop ####
subDicts = rocketDictReader.getImmediateSubDicts()
if "Rocket.HIL" in subDicts:
self.hardwareInTheLoopControl = "yes"
quatUpdateRate = rocketDictReader.getInt("HIL.quatUpdateRate")
posUpdateRate = rocketDictReader.getInt("HIL.posUpdateRate")
velUpdateRate = rocketDictReader.getInt("HIL.velUpdateRate")
teensyComPort = rocketDictReader.getString("HIL.teensyComPort")
imuComPort = rocketDictReader.getString("HIL.imuComPort")
teensyBaudrate = rocketDictReader.getInt("HIL.teensyBaudrate")
imuBaudrate = rocketDictReader.getInt("HIL.imuBaudrate")
self.hilInterface = HILInterface(quatUpdateRate,posUpdateRate,velUpdateRate, teensyComPort, imuComPort, teensyBaudrate, imuBaudrate)
else:
self.hardwareInTheLoopControl = "no"
#### Initialize Logging ####
self.timeStepLog = None
''' Log containing one entry per time step, logs rocket state. None if logging level == 0 '''
self.derivativeEvaluationLog = None
''' Log containing one entry per rocket motion derivative evaluation, contains component forces. None if logging level < 2 '''
loggingLevel = int(self.simDefinition.getValue("SimControl.loggingLevel"))
self.loggingLevel = loggingLevel
if loggingLevel > 0:
# Create the time step log and add columns to track the rocket state between each time step
self.timeStepLog = TimeStepLog()
zeroVector = Vector(0,0,0)
self.timeStepLog.addColumn("Position(m)", zeroVector)
self.timeStepLog.addColumn("Velocity(m/s)", zeroVector)
self.timeStepLog.addColumn("OrientationQuaternion", Quaternion(0,0,0,0))
self.timeStepLog.addColumn("EulerAngle(rad)", zeroVector)
self.timeStepLog.addColumn("AngularVelocity(rad/s)", zeroVector)
if "Adapt" in self.simDefinition.getValue("SimControl.timeDiscretization"):
self.timeStepLog.addColumn("EstimatedIntegrationError", 0)
if loggingLevel > 1:
self.derivativeEvaluationLog = Log()
zeroVector = Vector(0,0,0)
self.derivativeEvaluationLog.addColumn("Position(m)", zeroVector)
self.derivativeEvaluationLog.addColumn("Velocity(m/s)", zeroVector)
self.derivativeEvaluationLog.addColumn("OrientationQuaternion", Quaternion(0,0,0,0))
self.derivativeEvaluationLog.addColumn("AngularVelocity(rad/s)", zeroVector)
self.derivativeEvaluationLog.addColumn("CG(m)", zeroVector)
self.derivativeEvaluationLog.addColumn("MOI(kg*m^2)", zeroVector)
self.derivativeEvaluationLog.addColumn("Mass(kg)", 0)
self.derivativeEvaluationLog.addColumn("Wind(m/s)", zeroVector)
self.derivativeEvaluationLog.addColumn("AirDensity(kg/m^3)", 0)
self.derivativeEvaluationLog.addColumn("Mach", 0)
self.derivativeEvaluationLog.addColumn("UnitRe", 0)
self.derivativeEvaluationLog.addColumn("AOA(deg)", 0)
self.derivativeEvaluationLog.addColumn("RollAngle(deg)", 0)
self.derivativeEvaluationLog.addColumn("CPZ(m)", 0)
self.derivativeEvaluationLog.addColumn("AeroF(N)", zeroVector)
self.derivativeEvaluationLog.addColumn("AeroM(Nm)", zeroVector)
self.derivativeEvaluationLog.addColumn("GravityF(N)", zeroVector)
self.derivativeEvaluationLog.addColumn("TotalF(N)", zeroVector)
#### Init Components ####
self._createStages()
self._initializeRigidBody()
self._switchToStatefulRigidBodyIfRequired()
self._sortStagesAndComponents()
self._initializeStagingTriggers()
self._precomputeComponentProperties()
#### Init Parent classes ####
CompositeObject.__init__(self, self.stages)
self._updateFinenessRatio()
# Adjust rigid body state position to correspond to the rocket's CG instead of nose cone tip position
self._moveStatePositionToCG()
#### Init Guidance/Navigation/Control System (if required) ####
self.controlSystem = None
''' None for uncontrolled rockets. `MAPLEAF.GNC.ControlSystems.RocketControlSystem` for controlled rockets '''
if ( rocketDictReader.tryGetString("ControlSystem.controlledSystem") != None or rocketDictReader.tryGetString("ControlSystem.MomentController.Type") == "IdealMomentController") and stageToInitialize == None:
# Only create a control system if this is NOT a dropped stage
ControlSystemDictReader = SubDictReader("Rocket.ControlSystem", simDefinition=self.simDefinition)
controlSystemLogging = loggingLevel > 3
self.controlSystem = RocketControlSystem(ControlSystemDictReader, self, log=controlSystemLogging, silent=silent)
def _getMaxBodyTubeDiameter(self):
''' Gets max body tube diameter directly from config file '''
stageDicts = self._getStageSubDicts()
maxDiameter = 0
for stageDict in stageDicts:
componentDicts = self.rocketDictReader.getImmediateSubDicts(stageDict)
for componentDict in componentDicts:
className = self.rocketDictReader.getString(componentDict + ".class")
if className == "Bodytube":
diameter = self.rocketDictReader.getFloat(componentDict + ".outerDiameter")
maxDiameter = max(maxDiameter, diameter)
return maxDiameter
def _getStageSubDicts(self):
# Get all immediate subdictionaries of 'Rocket'
stageDicts = self.rocketDictReader.getImmediateSubDicts()
# Assume all subdictionaries represent rocket stages except for these exceptions
nonStageSubDicts = [ "Rocket.ControlSystem", "Rocket.HIL", "Rocket.Aero" ]
# Remove them from the list if they're in it
for dictName in nonStageSubDicts:
if dictName in stageDicts:
stageDicts.remove(dictName)
return stageDicts
def _initializeRigidBody(self):
#### Get initial kinematic state (in launch tower frame) ####
initPos = self.rocketDictReader.getVector("position")
initVel = self.rocketDictReader.getVector("velocity")
# Check whether precise initial orientation has been specified
rotationAxis = self.rocketDictReader.tryGetVector("rotationAxis", defaultValue=None)
if rotationAxis != None:
rotationAngle = math.radians(self.rocketDictReader.getFloat("rotationAngle"))
initOrientation = Quaternion(rotationAxis, rotationAngle)
else:
# Calculate initial orientation quaternion in launch tower frame
initialDirection = self.rocketDictReader.getVector("initialDirection").normalize()
angleFromVertical = Vector(0,0,1).angle(initialDirection)
rotationAxis = Vector(0,0,1).crossProduct(initialDirection)
initOrientation = Quaternion(rotationAxis, angleFromVertical)
initAngVel = AngularVelocity(rotationVector=self.rocketDictReader.getVector("angularVelocity"))
initState_launchTowerFrame = RigidBodyState(initPos, initVel, initOrientation, initAngVel)
# Convert to the global inertial frame
initState_globalInertialFrame = self.environment.convertInitialStateToGlobalFrame(initState_launchTowerFrame)
# Get desired time discretization method
timeDisc = self.rocketDictReader.getString("SimControl.timeDiscretization")
#TODO: Check for additional parameters to integrate - if they exist create a StatefulRigidBody + RocketState instead!
# Ask each rocket component whether it would like to add parameters to integrate after all the components have been initialized
discardDtCallback = None if (self.simRunner == None) else self.simRunner.discardForceLogsForPreviousTimeStep
#### Initialize the rigid body ####
self.rigidBody = RigidBody(
initState_globalInertialFrame,
self._getAppliedForce,
self.getInertia,
integrationMethod=timeDisc,
discardedTimeStepCallback=discardDtCallback,
simDefinition=self.simDefinition
)
def _createStages(self):
''' Initialize each of the stages and all of their subcomponents. '''
stageDicts = self._getStageSubDicts()
# If we're initializing a dropped stage, figure out which one
if self.stage != None:
stageNumbers = []
stageNumberSet = set()
for stageDict in stageDicts:
stageNumber = self.rocketDictReader.getFloat(stageDict + ".stageNumber")
stageNumbers.append(stageNumber)
stageNumberSet.add(stageNumber)
if len(stageNumbers) != len(stageNumberSet):
raise ValueError("For multi-stage rockets, each stage must have a unique stage number. Set the Rocket.StageName.stageNumber value for each stage. 0 for first stage, 1 for second, etc...")
stageNumbers.sort()
stageToInitialize = stageNumbers[self.stage]
# Initialize Stage(s)
initializingAllStages = (self.stage == None)
for stageDictionary in stageDicts:
stageDictReader = SubDictReader(stageDictionary, self.simDefinition)
stageNumber = stageDictReader.getFloat("stageNumber")
if initializingAllStages or stageNumber == stageToInitialize:
newStage = Stage(stageDictReader, self)
self.stages.append(newStage)
if newStage.name not in self.__dict__: # Avoid clobbering existing info
setattr(self, newStage.name, newStage) # Make stage available as rocket.stageName
def _sortStagesAndComponents(self):
# Create Planar Interfaces b/w components inside stages
for stage in self.stages:
stage.components = PlanarInterface.sortByZLocation(stage.components, self.rigidBody.state)
stage.componentInterfaces = PlanarInterface.createPlanarComponentInterfaces(stage.components)
# Create planar interfaces b/w stages
self.stages = PlanarInterface.sortByZLocation(self.stages, self.rigidBody.state)
self.stageInterfaces = PlanarInterface.createPlanarComponentInterfaces(self.stages)
if self.maxDiameter > 0:
# Only run this if we're running a real rocket with body tubes
self._ensureBaseDragIsAccountedFor()
def _initializeStagingTriggers(self):
''' Set up trigger conditions for staging '''
# Self.stage is not passed in if the current instance represents a rocket ready to launch - then we have to set up staging events
if self.stage == None:
for stageIndex in range(len(self.stages)):
stage = self.stages[stageIndex]
if stage.separationConditionType != 'None':
self.simEventDetector.subscribeToEvent(
stage.separationConditionType,
self._stageSeparation,
stage.separationConditionValue,
triggerDelay=stage.separationDelay
)
if stageIndex != len(self.stages)-1:
# Set all upper stage motors to ignite a very long time in the future
stage.motor.updateIgnitionTime(1000000000, fakeValue=True)
else:
# Otherwise this rocket object is representing a single dropped stage, and no stage separations are necessary
# Motor is burned out
self.stages[0].motor.updateIgnitionTime(-1000000000, fakeValue=True)
def _switchToStatefulRigidBodyIfRequired(self):
'''
Query all of the rocket components to see if any of them are stateful by attempting to call their getExtraParametersToIntegrate function
If the rocket contains stateful components, the rocket state is converted to a StateList and all of these state variables requested by components are added to it
Otherwise, nothing changes and the rocket state remains a RigidBodyState
'''
varNames = []
initVals = []
derivativeFuncs = []
# Query all of the components
for stage in self.stages:
for component in stage.components:
try:
paramNames, initValues, derivativeFunctions = component.getExtraParametersToIntegrate()
varNames += paramNames
initVals += initValues
derivativeFuncs += derivativeFunctions
except AttributeError:
pass # No extra parameters to integrate
# If any of the components are stateful, keep track of their states in the main rocket state
if len(varNames) > 0:
if len(varNames) != len(initVals) or len(initVals) != len(derivativeFuncs):
raise ValueError("ERROR: Mismatch in number of extra parameters names ({}), init values({}), and derivative functions({}) to integrate".format(len(varNames), len(initVals), len(derivativeFuncs)))
# Switch to a stateful rigid body
initState = self.rigidBody.state
forceFunc = self.rigidBody.forceFunc
inertiaFunc = self.rigidBody.inertiaFunc
integrationMethod = self.rocketDictReader.getString("SimControl.timeDiscretization")
discardDtCallback = None if (self.simRunner == None) else self.simRunner.discardForceLogsForPreviousTimeStep
self.rigidBody = StatefulRigidBody(
initState,
forceFunc,
inertiaFunc,
integrationMethod=integrationMethod,
discardedTimeStepCallback=discardDtCallback,
simDefinition=self.simDefinition
)
# Add the additional state variables
for i in range(len(varNames)):
self.rigidBody.addStateVariable(varNames[i], initVals[i], derivativeFuncs[i])
def _precomputeComponentProperties(self):
for stage in self.stages:
for component in stage.components:
try:
component.precomputeProperties()
except AttributeError:
pass
def _moveStatePositionToCG(self):
''' Moves self.rigidBody.state.position to have it represent the rocket's initial CG position, not the initial nose cone position '''
initInertia = self.getInertia(0, self.rigidBody.state)
CGPosition_wrtNoseCone_localFrame = initInertia.CG
CGPosition__wrtNoseCone_globalFrame = self.rigidBody.state.orientation.rotate(CGPosition_wrtNoseCone_localFrame)
CGPosition_globalFrame = self.rigidBody.state.position + CGPosition__wrtNoseCone_globalFrame
self.rigidBody.state.position = CGPosition_globalFrame
def getLength(self):
totalLength = 0
for stage in self.stages:
try:
totalLength += stage.getLength()
except TypeError:
pass # Stage Length was None - no body components in stage
return totalLength
def plotShape(self):
plt.figure()
plt.gca().set_aspect('equal')
rocketInertia = self.getInertia(0, self.rigidBody.state)
TotalCG = rocketInertia.CG.Z
TotalMass = rocketInertia.mass
TotalCGplt = plt.plot(TotalCG, 0, color='b', marker='d', label='Total CG', linestyle='None')
CGsubZ = []
CGsubY = []
plt.title('Total Rocket CG: %10.4f m \n Total Rocket Mass: %10.4f Kg' % (TotalCG,TotalMass) )
for stage in self.stages:
zCGs, yCGs = stage.plotShape()
# Add subcomponents CGs to arrays
CGsubZ += zCGs
CGsubY += yCGs
SubCGplt = plt.plot(CGsubZ, CGsubY, color='g', marker='.', label='Subcomponent CG', linestyle='None')
legendHeight = self.maxDiameter
plt.legend(loc='upper center', bbox_to_anchor = (0.5,-1.05))
plt.show()
#### Stage Separation ####
def _stageSeparation(self):
print("Stage {} Separation".format(self.simRunner.stagingIndex + 1))
# Initialize dropped stage as a new rocket
self.simRunner.createNewDetachedStage()
# Drop stage from current rocket
self._dropStage()
# Ignite next motor (set ignition time to the time of stage separation)
currentTime = self.rigidBody.time
self.stages[0].motor.updateIgnitionTime(currentTime)
self._ensureBaseDragIsAccountedFor()
self._updateFinenessRatio()
def _dropStage(self, stageIndex=-1):
droppedStage = self.stages.pop(stageIndex)
delattr(self, droppedStage.name)
self.recomputeFixedMassInertia()
if self.controlSystem != None:
# Check whether the controlled system was part of the dropped stage
if self.controlSystem.controlledSystem in droppedStage.components:
# If so delete the rocket's control system and remove any control system-induced time stepping modifications
print("Rocket's controlled system was on the dropped stage. Deactivating control system.")
self.controlSystem.restoreOriginalTimeStepping()
self.controlSystem = None
def _ensureBaseDragIsAccountedFor(self):
''' If no BoatTail exists at the bottom of the rocket, adds a zero-length boat tail. This is necessary b/c Boat Tail aero-functions are the ones that account for base drag '''
boatTailComponentAtBottomOfRocket = False
bottomStage = self.stages[-1]
for comp in reversed(bottomStage.components):
if isinstance(comp, BodyComponent):
if isinstance(comp, BoatTail):
boatTailComponentAtBottomOfRocket = True
break
if not boatTailComponentAtBottomOfRocket and self.addZeroLengthBoatTailsToAccountForBaseDrag:
if not self.silent:
print("Adding zero-length BoatTail to the bottom of current bottom stage ({}) to account for base drag".format(bottomStage.name))
# Create a zero-length, zero-mass boat tail to account for base drag
zeroInertia = Inertia(Vector(0,0,0), Vector(0,0,0), 0)
diameter = self.maxDiameter # TODO: Get the actual bottom-body-tube diameter from a future Stage.getRadius function
length = 0
position = bottomStage.getBottomInterfaceLocation()
boatTail = BoatTail(
diameter,
diameter,
length,
position,
zeroInertia,
self,
bottomStage,
"Auto-AddedZeroLengthBoatTail",
self.surfaceRoughness
)
initializeForceLogging(boatTail, "FakeRocketName.Auto-AddedZeroLengthBoatTail", self)
bottomStage.components.append(boatTail)
def _updateFinenessRatio(self):
''' Updates self.finenessRatio based on current BodyComponents in rocket stages '''
length = self.getLength()
maxDiameter = max([ stage.getMaxDiameter() for stage in self.stages ])
if maxDiameter == 0:
self.finenessRatio = None
else:
self.finenessRatio = length/maxDiameter
#### Component-buildup method for Force ####
def _getEnvironmentalConditions(self, time, state):
env = self.environment.getAirProperties(state.position, time)
# Neglect turbulent component of wind if required
if self.isUnderChute and self.turbulenceOffWhenUnderChute:
env = EnvironmentalConditions(
env.ASLAltitude,
env.Temp,
env.Pressure,
env.Density,
env.DynamicViscosity,
env.MeanWind,
env.MeanWind,
Vector(0, 0, 0),
)
return env
def _getAppliedForce(self, time, state):
''' Get the total force currently being experienced by the rocket, used by self.rigidBody to calculate the rocket's acceleration '''
### Precomputations and Logging ###
environment = self._getEnvironmentalConditions(time, state) # Get and log current air/wind properties
rocketInertia = self.getInertia(time, state) # Get and log current rocket inertia
if self.derivativeEvaluationLog is not None:
self.derivativeEvaluationLog.newLogRow(time)
self.derivativeEvaluationLog.logValue("Position(m)", state.position)
self.derivativeEvaluationLog.logValue("Velocity(m/s)", state.velocity)
### Component Forces ###
if not self.isUnderChute:
# Precompute and log
Mach = AeroParameters.getMachNumber(state, environment)
unitRe = AeroParameters.getReynoldsNumber(state, environment, 1.0)
AOA = AeroParameters.getTotalAOA(state, environment)
rollAngle = AeroParameters.getRollAngle(state, environment)
if self.derivativeEvaluationLog is not None:
self.derivativeEvaluationLog.logValue("Mach", Mach)
self.derivativeEvaluationLog.logValue("UnitRe", unitRe)
self.derivativeEvaluationLog.logValue("AOA(deg)", math.degrees(AOA))
self.derivativeEvaluationLog.logValue("RollAngle(deg)", rollAngle)
self.derivativeEvaluationLog.logValue("OrientationQuaternion", state.orientation)
self.derivativeEvaluationLog.logValue("AngularVelocity(rad/s)", state.angularVelocity)
# This function will be the inherited function CompositeObject.getAppliedForce
componentForces = self.getAppliedForce(state, time, environment, rocketInertia.CG)
else:
# When under chute, neglect forces from other components
componentForces = self.recoverySystem.getAppliedForce(state, time, environment, Vector(0,0,-1))
# Log the recovery system's applied force (Normally handled in CompositeObject.getAppliedForce)
if hasattr(self.recoverySystem, "forcesLog"):
self.recoverySystem.forcesLog.append(componentForces.force)
self.recoverySystem.momentsLog.append(componentForces.moment)
# Move Force-Moment system to rocket CG
componentForces = componentForces.getAt(rocketInertia.CG)
### Gravity ###
gravityForce = self.environment.getGravityForce(rocketInertia, state)
totalForce = componentForces + gravityForce
### Launch Rail ###
totalForce = self.environment.applyLaunchTowerForce(state, time, totalForce)
if self.derivativeEvaluationLog is not None:
self.derivativeEvaluationLog.logValue("Wind(m/s)", environment.Wind)
self.derivativeEvaluationLog.logValue("AirDensity(kg/m^3)", environment.Density)
self.derivativeEvaluationLog.logValue("CG(m)", rocketInertia.CG)
self.derivativeEvaluationLog.logValue("MOI(kg*m^2)", rocketInertia.MOI)
self.derivativeEvaluationLog.logValue("Mass(kg)", rocketInertia.mass)
CPZ = AeroFunctions._getCPZ(componentForces)
self.derivativeEvaluationLog.logValue("CPZ(m)", CPZ)
self.derivativeEvaluationLog.logValue("AeroF(N)", componentForces.force)
self.derivativeEvaluationLog.logValue("AeroM(Nm)", componentForces.moment)
self.derivativeEvaluationLog.logValue("GravityF(N)", gravityForce.force)
self.derivativeEvaluationLog.logValue("TotalF(N)", totalForce.force)
return totalForce
#### Driving / Controlling Simulation ####
def _logState(self):
'''
Logs the initial state of the rocket to the time step log
'''
state = self.rigidBody.state
time = self.rigidBody.time
if self.timeStepLog is not None:
self.timeStepLog.newLogRow(time)
self.timeStepLog.logValue("Position(m)", state.position)
self.timeStepLog.logValue("Velocity(m/s)", state.velocity)
try: # 6DoF Mode
self.timeStepLog.logValue("OrientationQuaternion", state.orientation)
self.timeStepLog.logValue("AngularVelocity(rad/s)", state.angularVelocity)
# Also log NED Tait-Bryan 3-2-1 z-y-x Euler Angles if in 6DoF mode
globalOrientation = state.orientation
orientationOfNEDFrameInGlobalFrame = self.environment.earthModel.getInertialToNEDFrameRotation(*state.position)
orientationRelativeToNEDFrame = orientationOfNEDFrameInGlobalFrame.conjugate() * globalOrientation
eulerAngles = orientationRelativeToNEDFrame.toEulerAngles()
self.timeStepLog.logValue("EulerAngle(rad)", eulerAngles)
except AttributeError:
pass # 3DoF mode
# Print the current time and altitude to the console
altitude = self.environment.earthModel.getAltitude(*state.position)
consoleOutput = "{:<8.4f} {:>6.5f}".format(time, altitude)
print(consoleOutput)
def _runControlSystem(self):
'''
Attempts to run the rocket control system (only runs if it's time to run again, based on its updated rate) (updating target positions for actuators)
'''
if self.controlSystem != None and not self.isUnderChute:
state = self.rigidBody.state
time = self.rigidBody.time
environment = self._getEnvironmentalConditions(time, state)
### Run Control Loop ###
self.controlSystem.runControlLoopIfRequired(time, state, environment)
def timeStep(self, dt: float):
'''
Tells the simulation to take a time step of size dt.
Usually called by functions like `MAPLEAF.SimulationRunners.Simulation.run()`
Returns:
* timeStepAdaptationFactor: (float) indicates the factor by which the adaptive time stepping method would like to change the timestep for the next timestep (1.0 for non-adaptive methods)
* dt: (float) actual size of time step taken. Adaptive methods will override the dt asked for if the predicted error for a time step is over their error threshold.
'''
# Stop the rocket from sliding off the bottom of the launch rail
self.rigidBody.state = self.environment.applyLaunchRailMotionConstraints(self.rigidBody.state, self.rigidBody.time)
# Trigger any events that occurred during the last time step
estimatedTimeToNextEvent, accuratePrediction = self.simEventDetector.triggerEvents()
# If required, override time step to accurately resolve upcoming discrete events
if "Adapt" in self.rigidBody.integrate.method and estimatedTimeToNextEvent < dt:
if accuratePrediction:
# For time-deterministic events, just set the time step to ever so slightly past the event
newDt = estimatedTimeToNextEvent + 1e-5
print("Rocket + SimEventDetector overriding time step from {} to {} to accurately trigger resolve time-deterministic event.".format(dt, newDt))
dt = newDt
else:
# For time-nondeterministic events, slowly approach the event
newDt = max(estimatedTimeToNextEvent/1.5, self.eventTimeStep)
estimatedOccurenceTime = self.rigidBody.time + estimatedTimeToNextEvent
print("Rocket + SimEventDetector overriding time step from {} to {} to accurately resolve upcoming event. Estimated occurence at: {}".format(dt, newDt, estimatedOccurenceTime))
dt = newDt
self._runControlSystem()
self._logState()
# Take timestep
integrationResult = self.rigidBody.timeStep(dt)
# If required, log estimated integration error
if "Adapt" in self.rigidBody.integrate.method and self.timeStepLog is not None:
self.timeStepLog.logValue("EstimatedIntegrationError", integrationResult.errorMagEstimate)
return integrationResult
def _switchTo3DoF(self):
''' Switch to 3DoF simulation after recovery system is deployed '''
print("Switching to 3DoF simulation")
new3DoFState = RigidBodyState_3DoF(self.rigidBody.state.position, self.rigidBody.state.velocity)
# Re-read time discretization in case an adaptive method has been selected while using a fixed-update rate control system - in that case, want to switch back to adaptive time stepping for the recovery (uncontrolled) portion of the flight
originalTimeDiscretization = self.rocketDictReader.getString("SimControl.timeDiscretization")
if self.simRunner != None:
self.rigidBody = RigidBody_3DoF(
new3DoFState,
self._getAppliedForce,
self.getMass,
startTime=self.rigidBody.time,
integrationMethod=originalTimeDiscretization,
discardedTimeStepCallback=self.simRunner.discardForceLogsForPreviousTimeStep,
simDefinition=self.simDefinition
)
else:
self.rigidBody = RigidBody_3DoF(
new3DoFState,
self._getAppliedForce,
self.getMass,
startTime=self.rigidBody.time,
integrationMethod=originalTimeDiscretization,
simDefinition=self.simDefinition
)
#### After Simulation ####
def writeLogsToFile(self, directory="."):
logfilePaths = []
if self.timeStepLog is not None:
rocketName = self.components[0].name # Rocket is named after its top stage
path = os.path.join(directory, "{}_timeStepLog.csv".format(rocketName))
# Time step log
if self.timeStepLog.writeToCSV(path):
logfilePaths.append(path)
# Derivative evaluation log
if self.derivativeEvaluationLog is not None:
path = os.path.join(directory, "{}_derivativeEvaluationLog.csv".format(rocketName))
if self.derivativeEvaluationLog.writeToCSV(path):
logfilePaths.append(path)
# Calculate aerodynamic coefficients if desired
if self.loggingLevel > 2:
expandedLogPath = Logging.postProcessForceEvalLog(path, refArea=self.Aref, refLength=self.maxDiameter)
logfilePaths.append(expandedLogPath)
# Control system log
if self.controlSystem != None:
if self.controlSystem.log != None:
controlSystemLogPath = self.controlSystem.writeLogsToFile(directory)
logfilePaths.append(controlSystemLogPath)
return logfilePaths
