def test_burnTimeAdjustFactor(self):
simDef = SimDefinition("MAPLEAF/Examples/Simulations/test2.mapleaf")
# Create normal motor
rocketDictReader1 = SubDictReader("Rocket", simDef)
motorRocket1 = Rocket(rocketDictReader1)
motor1 = motorRocket1.stages[0].getComponentsOfType(TabulatedMotor)[0]
burnTimeAdjustFactor = "1.11"
# Create impulse-adjusted motor
simDef.setValue("Rocket.Sustainer.Motor.burnTimeAdjustFactor",
burnTimeAdjustFactor)
rocketDictReader2 = SubDictReader("Rocket", simDef)
motorRocket2 = Rocket(rocketDictReader2)
motor2 = motorRocket2.stages[0].getComponentsOfType(TabulatedMotor)[0]
# Check that total impulse hasn't changed
impulse1 = motor1.getTotalImpulse()
impulse2 = motor2.getTotalImpulse()
self.assertAlmostEqual(impulse1, impulse2)
# Check that burn time has changed
burnTime1 = motor1.times[-1]
burnTime2 = motor2.times[-1]
self.assertAlmostEqual(burnTime2 / burnTime1,
float(burnTimeAdjustFactor))
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 setUp(self):
configFilePath = "MAPLEAF/Examples/Simulations/Wind.mapleaf"
self.simDef = SimDefinition(configFilePath, silent=True)
self.simDef.setValue("Environment.MeanWindModel", "Constant")
self.simDef.setValue("SimControl.loggingLevel", "0")
rocketDictReader = SubDictReader("Rocket", self.simDef)
envReader = SubDictReader("Environment", self.simDef)
self.rocket = Rocket(rocketDictReader, silent=True)
self.mWM = meanWindModelFactory(envReader, self.rocket)
def setUp(self):
simDef = SimDefinition("MAPLEAF/Examples/Simulations/test3.mapleaf", silent=True)
rocketDictReader = SubDictReader("Rocket", simDef)
self.rocket = Rocket(rocketDictReader, silent=True)
simDef = SimDefinition("MAPLEAF/Examples/Simulations/test6.mapleaf", silent=True)
rocketDictReader = SubDictReader("Rocket", simDef)
self.rocket2 = Rocket(rocketDictReader, silent=True)
self.finSet1 = self.rocket2.stages[0].getComponentsOfType(FinSet)[0]
self.finSet2 = self.rocket2.stages[0].getComponentsOfType(FinSet)[1]
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.dummyAngularVelocity1 = AngularVelocity(rotationVector = Vector(0,0,0))
self.dummyAngularVelocity2 = AngularVelocity(rotationVector = Vector(0,0,1))
self.dummyAngularVelocity3 = AngularVelocity(rotationVector = Vector(0,0,-1))
self.dummyAngularVelocity4 = AngularVelocity(rotationVector = Vector(1,0,0))
self.dummyAngularVelocity5 = AngularVelocity(rotationVector = Vector(-1,0,0))
self.dummyAngularVelocity6 = AngularVelocity(rotationVector = Vector(0,1,0))
self.dummyAngularVelocity7 = AngularVelocity(rotationVector = Vector(0,-1,0))
self.dummyAngularVelocity8 = AngularVelocity(rotationVector = Vector(1,1,0))
self.currentConditions = self.rocket2.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)))
self.rocketState9 = RigidBodyState(Vector(0, 0, 200), Vector(0, 0, 200), Quaternion(Vector(1, 0, 0), math.radians(-2)), AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState10 = RigidBodyState(Vector(0, 0, 200), Vector(0, 0, 200), Quaternion(Vector(0, 0, 1), 0), AngularVelocity(rotationVector=Vector(0, 0, 1)))
self.rocketState11 = RigidBodyState(Vector(0, 0, 200), Vector(0, 0, 200), Quaternion(Vector(0, 1, 0), math.radians(2)), AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState12 = RigidBodyState(Vector(0, 0, 200), Vector(0, 0, 200), Quaternion(Vector(0, 1, 0), math.radians(-2)), AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState13 = RigidBodyState(Vector(0, 0, 200), Vector(0, 0, 500), Quaternion(Vector(1, 0, 0), math.radians(4)), AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState14 = RigidBodyState(Vector(0, 0, 200), Vector(0, 0, 500), Quaternion(Vector(1, 0, 0), math.radians(6)), AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState15 = RigidBodyState(Vector(0, 0, 200), Vector(0, 0, 500), Quaternion(Vector(1, 0, 0), math.radians(8)), AngularVelocity(rotationVector=Vector(0, 0, 0)))
self.rocketState16 = RigidBodyState(Vector(0, 0, 200), Vector(0, 0, 344), Quaternion(Vector(1, 0, 0), math.radians(0)), AngularVelocity(rotationVector=Vector(0, 0, 0)))
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)
def setUp(self):
self.rocket = "fakeNewsRocket" # May have to convert this into a real Rocket at some point, but it's faster this way
self.simDefinition = SimDefinition(
"MAPLEAF/Examples/Simulations/Wind.mapleaf", silent=True)
self.simDefinition.setValue("Environment.MeanWindModel", "Constant")
envReader = SubDictReader("Environment", self.simDefinition)
self.mWM = meanWindModelFactory(envReader, self.rocket)
def test_rocketCGCalculation(self):
# Check actual CG Loc Calculation
# Top stage CG: #
# Nosecone: 1 kg @ 0m
# Recovery: 5 kg @ -2m
# BodyTube: 1 kg @ -0.762m
# Mass: 50 kg @ -2.6m
# Motor: 11.4885 kg @ 2.130434783
# Fins: 1 kg @ -4.011m
# Total Weight = 69.4885 kg
# Stage 1 CG: -2.4564359077698
expectedCG = Vector(0, 0, -1.731185736)
# Remove overrides from rocket definition file
simDef = SimDefinition("MAPLEAF/Examples/Simulations/Wind.mapleaf",
silent=True)
simDef.removeKey("Rocket.Sustainer.constCG")
simDef.removeKey("Rocket.Sustainer.constMass")
simDef.removeKey("Rocket.Sustainer.constMOI")
rocketDictReader = SubDictReader("Rocket", simDef)
rocket = Rocket(rocketDictReader, silent=True)
rocketInertia = rocket.getInertia(0, rocket.rigidBody.state)
assertVectorsAlmostEqual(self, rocketInertia.CG, expectedCG, n=4)
def test_customGust(self):
simDef = SimDefinition("MAPLEAF/Examples/Simulations/Wind.mapleaf",
silent=True)
simDef.setValue("Environment.TurbulenceModel", "customSineGust")
simDef.setValue("Environment.CustomSineGust.startAltitude", "0")
simDef.setValue("Environment.CustomSineGust.magnitude", "9")
simDef.setValue("Environment.CustomSineGust.sineBlendDistance", "30")
simDef.setValue("Environment.CustomSineGust.thickness", "200")
simDef.setValue("Environment.CustomSineGust.direction", "(0 1 0)")
envReader = SubDictReader("Environment", simDef)
turbModel = turbulenceModelFactory(envReader)
v1 = turbModel.getTurbVelocity(0, Vector(1, 0, 0), 0)
assertVectorsAlmostEqual(self, v1, Vector(0, 0, 0))
v1 = turbModel.getTurbVelocity(15, Vector(1, 0, 0), 0)
assertVectorsAlmostEqual(self, v1, Vector(0, 4.5, 0))
v1 = turbModel.getTurbVelocity(30, Vector(1, 0, 0), 0)
assertVectorsAlmostEqual(self, v1, Vector(0, 9, 0))
v1 = turbModel.getTurbVelocity(230, Vector(1, 0, 0), 0)
assertVectorsAlmostEqual(self, v1, Vector(0, 9, 0))
v1 = turbModel.getTurbVelocity(245, Vector(1, 0, 0), 0)
assertVectorsAlmostEqual(self, v1, Vector(0, 4.5, 0))
v1 = turbModel.getTurbVelocity(260, Vector(1, 0, 0), 0)
assertVectorsAlmostEqual(self, v1, Vector(0, 0, 0))
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_SolidMotor(self):
simDef = SimDefinition("MAPLEAF/Examples/Simulations/Jake1.mapleaf")
rocketDictReader = SubDictReader("Rocket", simDef)
motorRocket = Rocket(rocketDictReader)
motor = motorRocket.stages[0].motor
# Try getting thrust, if it works with 0 oxidizer flow rate, then we're good
t = motor.getAppliedForce('fakeState', 0.12, 'fakeEnv',
'fakeCG').force.Z
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_MotorMOI(self):
motorRocket = self.motorRocket
motor = self.motorRocket.stages[0].getComponentsOfType(
TabulatedMotor)[0]
### Oxidizer MOI Tests ###
def getOxMOI(time):
return motor._getOxInertia(time).MOI
ActualOxMOI = getOxMOI(0)
expectedOxMOI = Vector(1.0, 1.0, 0.1)
assertIterablesAlmostEqual(self, ActualOxMOI, expectedOxMOI)
ActualOxMOI = getOxMOI(2.505)
expectedOxMOI = Vector(0.5, 0.5, 0.05)
assertIterablesAlmostEqual(self, ActualOxMOI, expectedOxMOI)
ActualOxMOI = getOxMOI(5.0)
expectedOxMOI = Vector(0, 0, 0)
assertIterablesAlmostEqual(self, ActualOxMOI, expectedOxMOI)
ActualOxMOI = getOxMOI(10)
expectedOxMOI = Vector(0, 0, 0)
assertIterablesAlmostEqual(self, ActualOxMOI, expectedOxMOI)
### Fuel MOI Tests ###
def getFuelMOI(time):
return motor._getFuelInertia(time).MOI
ActualFuelMOI = getFuelMOI(0)
expectedFuelMOI = Vector(0.15, 0.15, 0.02)
assertIterablesAlmostEqual(self, ActualFuelMOI, expectedFuelMOI)
ActualFuelMOI = getFuelMOI(2.505)
expectedFuelMOI = Vector(0.075, 0.075, 0.01)
assertIterablesAlmostEqual(self, ActualFuelMOI, expectedFuelMOI)
ActualFuelMOI = getFuelMOI(5)
expectedFuelMOI = Vector(0, 0, 0)
assertIterablesAlmostEqual(self, ActualFuelMOI, expectedFuelMOI)
ActualFuelMOI = getFuelMOI(10)
expectedFuelMOI = Vector(0, 0, 0)
assertIterablesAlmostEqual(self, ActualFuelMOI, expectedFuelMOI)
simDef = SimDefinition("MAPLEAF/Examples/Simulations/Jake1.mapleaf")
rocketDictReader = SubDictReader("Rocket", simDef)
jakeRocket = Rocket(rocketDictReader)
motor = jakeRocket.stages[0].motor
motorInertia = motor.getInertia(3, jakeRocket.rigidBody.state)
expectedInertiaAfterBurnout = Inertia(Vector(0, 0, 0), Vector(0, 0, 0),
0.0)
assertInertiasAlmostEqual(self, motorInertia,
expectedInertiaAfterBurnout)
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)
def optimizationRunnerFactory(simDefinitionFilePath=None, simDefinition=None, optimizationReader=None, silent=False, parallel=False) -> OptimizingSimRunner:
''' Provide a subdictionary reader pointed at an optimization dictionary. Will read the dictionary, initialize an optimizing simulation runner and return it. '''
if simDefinition != None or simDefinitionFilePath != None:
simDefinition = loadSimDefinition(simDefinitionFilePath, simDefinition, silent)
optimizationReader = SubDictReader('Optimization', simDefinition)
# Ensure no output is produced during each simulation (cost function evaluation)
simDefinition.setValue("SimControl.plot", "None")
simDefinition.setValue("SimControl.RocketPlot", "Off")
else:
if optimizationReader == None:
raise ValueError('subDictReader not initialized for a nested optimization')
method = optimizationReader.tryGetString('method', defaultValue='PSO')
if method == 'PSO':
return PSORunner(optimizationReader, silent=silent, parallel=parallel)
elif 'scipy.optimize.minimize' in method:
return ScipyMinimizeRunner(optimizationReader, silent=silent, parallel=parallel)
else:
raise ValueError('Optimization method: {} not implemented, try PSO'.format(method))
def rocketComponentFactory(subDictPath, rocket, stage):
"""
Initializes a rocket component based on the stringNameToClassMap
Inputs:
subDictPath: (string) Path to subDict in simulation definition, like "Rocket.Stage1.Nosecone"
rocket: (Rocket) that the component is a part of
stage: (Stage) That the component is a part of
Also uses the stringNameToClassMap dictionary
"""
# Create SubDictReader for the rocket component's dictionary
componentDictReader = SubDictReader(subDictPath, rocket.simDefinition)
# Figure out which class to initialize
className = componentDictReader.getString("class")
referencedClass = stringNameToClassMap[className]
# Initialize the rocket component
newComponent = referencedClass(componentDictReader, rocket, stage)
# Initialize logging component forces (if desired)
initializeForceLogging(newComponent, subDictPath, rocket)
return newComponent
def integratorFactory(integrationMethod="Euler", simDefinition=None, discardedTimeStepCallback=None):
'''
Returns a callable integrator object
Inputs:
* integrationMethod: (str) Name of integration method: Examples = "Euler", "RK4", "RK23Adaptive", and "RK45Adaptive"
* simDefinition: (`MAPLEAF.IO.SimDefinition`) for adaptive integration, provide a simdefinition file with time step adaptation parameters
* discardedTimeStepCallback: (1-argument function reference) for adaptive integration, this function (if provided) is called when a time step is computed,
but then discarded and re-computed with a smaller timestep to remain below the max estimated error threshold. Used by MAPLEAF to remove
force calculation logs from those discarded time steps
'''
if "Adapt" in integrationMethod:
if simDefinition == None:
raise ValueError("SimDefinition object required to initialize adaptive integrator")
from MAPLEAF.IO import SubDictReader
adaptDictReader = SubDictReader("SimControl.TimeStepAdaptation", simDefinition)
# Adaptive Integration
controller = adaptDictReader.getString("controller")
if controller == "PID":
PIDCoeffs = [ float(x) for x in adaptDictReader.getString("PID.coefficients").split() ]
safetyFactor = None
elif controller == "elementary":
safetyFactor = adaptDictReader.getFloat("Elementary.safetyFactor")
PIDCoeffs = None
targetError = adaptDictReader.getFloat("targetError")
minFactor = adaptDictReader.getFloat("minFactor")
maxFactor = adaptDictReader.getFloat("maxFactor")
maxTimeStep = adaptDictReader.getFloat("maxTimeStep")
minTimeStep = adaptDictReader.getFloat("minTimeStep")
return AdaptiveIntegrator(
method=integrationMethod,
controller=controller,
targetError=targetError,
maxMinSafetyFactors=[maxFactor, minFactor, safetyFactor],
PIDCoeffs=PIDCoeffs,
maxTimeStep=maxTimeStep,
minTimeStep=minTimeStep,
discardedTimeStepCallback=discardedTimeStepCallback
)
else:
# Constant time step integrator
return ClassicalIntegrator(method=integrationMethod)
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, stage=None):
'''
Initializes a rocket, complete with an Environment object and logs, both owned by the instance of this class
Returns an instance of Rocket with it's Environment/Logs initialized. Can be called by external classes to obtain a prepped rocket (used a lot this way in test cases).
'''
# Initialize Rocket
rocketDictReader = SubDictReader("Rocket", self.simDefinition)
rocket = Rocket(rocketDictReader, silent=self.silent, stageToInitialize=stage, simRunner=self, environment=self.environment) # Initialize Rocket
if self.simDefinition.getValue('SimControl.RocketPlot') in [ 'On', 'on' ]:
rocket.plotShape() # Reference to this simRunner used to add to logs
if stage == None:
self._setUpConsoleLogging()
self.stagingIndex = 0 # Initially zero, after dropping first stage: 1, after dropping second stage: 2, etc...
return rocket
def test_pinkNoiseStdDev(self):
simDef = SimDefinition("MAPLEAF/Examples/Simulations/Wind.mapleaf",
silent=True)
simDef.setValue("Environment.TurbulenceModel", "PinkNoise1D")
simDef.setValue("Environment.PinkNoiseModel.velocityStdDeviation", "1")
simDef.setValue("Environment.PinkNoiseModel.randomSeed1", "63583")
simDef.setValue("Environment.turbulenceOffWhenUnderChute", "False")
# Make sure turbulence intensity is not present since it overrides the given std deviation
simDef.removeKey("Environment.PinkNoiseModel.turbulenceIntensity")
envReader = SubDictReader("Environment", simDef)
turbModel = turbulenceModelFactory(envReader)
v1 = turbModel.getTurbVelocity(1, Vector(1, 0, 0), None)
self.assertAlmostEqual(v1[0], 0.7946604314895807 / 2.26)
v2 = turbModel.getTurbVelocity(1, Vector(1, 0, 0), None)
self.assertAlmostEqual(v2[0], 0.5874110050866364 / 2.26)
def test_rocketInertiaOverrides(self):
# Check CG Override
simDef = SimDefinition("MAPLEAF/Examples/Simulations/Wind.mapleaf")
rocketDictReader = SubDictReader("Rocket", simDef)
rocket = Rocket(rocketDictReader, silent=True)
cgLoc = rocket.getCG(0, rocket.rigidBody.state)
expectedCGLoc = Vector(0, 0, -2.65)
assertVectorsAlmostEqual(self, cgLoc, expectedCGLoc)
# Check Mass override
expectedMass = 50
actualMass = rocket.getMass(0, rocket.rigidBody.state)
self.assertAlmostEqual(actualMass, expectedMass)
# Check MOI Override + getInertia function
expectedMOI = Vector(85, 85, 0.5)
actualInertia = rocket.getInertia(0, rocket.rigidBody.state)
assertVectorsAlmostEqual(self, actualInertia.MOI, expectedMOI)
assertVectorsAlmostEqual(self, actualInertia.CG, expectedCGLoc)
self.assertAlmostEqual(actualInertia.mass, expectedMass)
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_controlTimeStepChecking(self):
simDef = SimDefinition("MAPLEAF/Examples/Simulations/Canards.mapleaf",
silent=True)
simDef.setValue("SimControl.timeDiscretization", "Euler")
simDef.setValue("SimControl.loggingLevel", "0")
simDef.setValue("SimControl.timeStep", "0.01")
simDef.setValue("Rocket.ControlSystem.updateRate", "101")
rocketDictReader = SubDictReader("Rocket", simDef)
# controlledCanardRocket = Rocket(rocketDictReader, silent=True)
# self.assertAlmostEqual(controlledCanardRocket.controlSystem.controlTimeStep, 1/101)
simDef.setValue("SimControl.timeStep", "0.011")
simDef.setValue("Rocket.ControlSystem.updateRate", "100")
controlledCanardRocket = Rocket(rocketDictReader, silent=True)
self.assertAlmostEqual(
controlledCanardRocket.controlSystem.controlTimeStep, 1 / 100)
# simDef.setValue("SimControl.timeStep", "0.009")
# controlledCanardRocket = Rocket(rocketDictReader, silent=True)
# self.assertAlmostEqual(controlledCanardRocket.controlSystem.controlTimeStep, 1/100)
# simDef.setValue("SimControl.timeStep", "0.1")
# controlledCanardRocket = Rocket(rocketDictReader, silent=True)
# self.assertAlmostEqual(controlledCanardRocket.controlSystem.controlTimeStep, 1/100)
simDef.setValue("SimControl.timeStep", "0.001")
simDef.setValue("SimControl.timeDiscretization", "RK45Adaptive")
simDef.setValue("SimControl.TimeStepAdaptation.controller", "PID")
simDef.setValue("Rocket.ControlSystem.updateRate", "100")
controlledCanardRocket = Rocket(rocketDictReader, silent=True)
self.assertEqual(controlledCanardRocket.rigidBody.integrate.method,
"RK4")
self.assertEqual(type(controlledCanardRocket.rigidBody.integrate),
ClassicalIntegrator)
self.assertEqual(controlledCanardRocket.controlSystem.controlTimeStep,
1 / 100)
def _createOptimizer(self):
'''
Reads the Optimization.ParticleSwarm dictionary and creates a pyswarms.GlobalBestPSO object
Returns the Optimizer, the user's desired number of iterations, and showConvergence (bool)
'''
pathToParticleSwarmDict = self.optimizationReader.simDefDictPathToReadFrom + '.ParticleSwarm'
pSwarmReader = SubDictReader(pathToParticleSwarmDict, self.optimizationReader.simDefinition)
nParticles = pSwarmReader.tryGetInt("nParticles", defaultValue=20)
nIterations = pSwarmReader.tryGetInt("nIterations", defaultValue=50)
c1 = pSwarmReader.tryGetFloat("cognitiveParam", defaultValue=0.5)
c2 = pSwarmReader.tryGetFloat("socialParam", defaultValue=0.6)
w = pSwarmReader.tryGetFloat("inertiaParam", defaultValue=0.9)
pySwarmOptions = { 'c1':c1, 'c2':c2, 'w':w }
nVars = len(self.varNames)
varBounds = (self.minVals, self.maxVals)
from pyswarms.single import \
GlobalBestPSO # Import here because for most sims it's not required
optimizer = GlobalBestPSO(nParticles, nVars, pySwarmOptions, bounds=varBounds, init_pos=self.initPositions)
if self.bestPosition != None and self.bestCost != None:
optimizer.swarm.best_pos = self.bestPosition
optimizer.swarm.best_cost = self.bestCost
showConvergence = self.optimizationReader.tryGetBool("showConvergencePlot", defaultValue=False)
if not self.silent:
print("Optimization Parameters:")
print("{} Particles".format(nParticles))
print("{} Iterations".format(nIterations))
print("c1 = {}, c2 = {}, w = {}\n".format(c1, c2, w))
costFunctionDefinition = self.optimizationReader.getString("costFunction")
print("Cost Function:")
print(costFunctionDefinition + "\n")
return optimizer, nIterations, showConvergence
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 setUp(self):
simDef = SimDefinition("MAPLEAF/Examples/Simulations/test2.mapleaf")
rocketDictReader = SubDictReader("Rocket", simDef)
self.motorRocket = Rocket(rocketDictReader)
def __init__(self, simDefinition=None, silent=False):
''' Sets up the Wind, Atmospheric, and Earth models requested in the Sim Definition file '''
self.launchRail = None
if simDefinition != None:
# Whenever we're running a real simulation, should always end up here
envDictReader = SubDictReader("Environment", simDefinition)
self.meanWindModel = meanWindModelFactory(envDictReader, silent=silent)
self.turbulenceModel = turbulenceModelFactory(envDictReader, silent=silent)
self.atmosphericModel = atmosphericModelFactory(envDictReader=envDictReader)
self.earthModel = earthModelFactory(envDictReader)
self.launchSiteElevation = envDictReader.tryGetFloat("LaunchSite.elevation")
self.launchSiteLatitude = envDictReader.tryGetFloat("LaunchSite.latitude")
self.launchSiteLongitude = envDictReader.tryGetFloat("LaunchSite.longitude")
# Check if being launched from a launch rail
launchRailLength = envDictReader.getFloat("LaunchSite.railLength")
if launchRailLength > 0:
# Initialize a launch rail, aligned with the rocket's initial direction
initialRocketPosition_towerFrame = envDictReader.getVector("Rocket.position")
# Check whether precise initial orientation has been specified
rotationAxis = envDictReader.tryGetVector("Rocket.rotationAxis", defaultValue=None)
if rotationAxis != None:
rotationAngle = math.radians(envDictReader.getFloat("Rocket.rotationAngle"))
initOrientation = Quaternion(rotationAxis, rotationAngle)
else:
# Calculate initial orientation quaternion in launch tower frame
rotationAxis = envDictReader.tryGetVector("Rocket.rotationAxis", defaultValue=None)
if rotationAxis != None:
rotationAngle = math.radians(self.rocketDictReader.getFloat("Rocket.rotationAngle"))
initOrientation = Quaternion(rotationAxis, rotationAngle)
else:
# Calculate initial orientation quaternion in launch tower frame
initialDirection = envDictReader.getVector("Rocket.initialDirection").normalize()
angleFromVertical = Vector(0,0,1).angle(initialDirection)
rotationAxis = Vector(0,0,1).crossProduct(initialDirection)
initOrientation = Quaternion(rotationAxis, angleFromVertical)
# TODO: Get from rocket, or calculate the same way - so that it works with rotationAxis + Angle
initialDirection = envDictReader.getVector("Rocket.initialDirection").normalize()
angleFromVertical = Vector(0,0,1).angle(initialDirection)
rotationAxis = Vector(0,0,1).crossProduct(initialDirection)
initOrientation = Quaternion(rotationAxis, angleFromVertical)
initPosition_seaLevelENUFrame = initialRocketPosition_towerFrame + Vector(0, 0, self.launchSiteElevation)
launchTowerState_local = RigidBodyState(position=initPosition_seaLevelENUFrame, orientation=initOrientation)
launchTowerState_global = self.earthModel.convertIntoGlobalFrame(launchTowerState_local, self.launchSiteLatitude, self.launchSiteLongitude)
towerDirection_global = launchTowerState_global.orientation.rotate(Vector(0, 0, 1))
self.launchRail = LaunchRail(launchTowerState_global.position, towerDirection_global, launchRailLength, earthRotationRate=self.earthModel.rotationRate)
else:
# Construct default environment from default parameters when no sim definition is passed in
# Need additional default value here in case a SimDefinition is not passed in (otherwise SimDefinition takes care of default values)
self.meanWindModel = meanWindModelFactory()
self.turbulenceModel = None
self.atmosphericModel = atmosphericModelFactory()
self.earthModel = earthModelFactory()
self.launchSiteElevation = float(defaultConfigValues["Environment.LaunchSite.elevation"])
self.launchSiteLatitude = float(defaultConfigValues["Environment.LaunchSite.latitude"])
self.launchSiteLongitude = float(defaultConfigValues["Environment.LaunchSite.longitude"])
def setUp(self):
self.rocket = "fakeNewsRocket" # May have to convert this into a real Rocket at some point, but it's faster this way
self.simDefinition = SimDefinition(
"MAPLEAF/Examples/Simulations/Wind.mapleaf", silent=True)
self.envReader = SubDictReader("Environment", self.simDefinition)
def _createNestedOptimization(self, simDef):
innerOptimizationReader = SubDictReader(self.optimizationReader.simDefDictPathToReadFrom + '.InnerOptimization', simDef)
return optimizationRunnerFactory(optimizationReader=innerOptimizationReader, silent=self.silent, parallel=self.parallel)