Source code for test_multiSpacecraft


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# Copyright (c) 2016, Autonomous Vehicle Systems Lab, University of Colorado at Boulder
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import inspect
import os

import numpy
import pytest

filename = inspect.getframeinfo(inspect.currentframe()).filename
path = os.path.dirname(os.path.abspath(filename))

from Basilisk.utilities import SimulationBaseClass
from Basilisk.utilities import unitTestSupport  # general support file with common unit test functions
import matplotlib.pyplot as plt
from Basilisk.simulation import spacecraftSystem
from Basilisk.utilities import macros
from Basilisk.utilities import pythonVariableLogger
from Basilisk.simulation import gravityEffector
from Basilisk.simulation import hingedRigidBodyStateEffector


def addTimeColumn(time, data):
    return numpy.transpose(numpy.vstack([[time], numpy.transpose(data)]))


# uncomment this line is this test is to be skipped in the global unit test run, adjust message as needed
# @pytest.mark.skipif(conditionstring)
# uncomment this line if this test has an expected failure, adjust message as needed
# @pytest.mark.xfail() # need to update how the RW states are defined
# provide a unique test method name, starting with test_

[docs] @pytest.mark.parametrize("function", ["SCConnected" , "SCConnectedAndUnconnected" ]) def test_spacecraftSystemAllTest(show_plots, function): """Module Unit Test""" [testResults, testMessage] = eval(function + '(show_plots)') assert testResults < 1, testMessage
[docs] def SCConnected(show_plots): """Module Unit Test""" # The __tracebackhide__ setting influences pytest showing of tracebacks: # the mrp_steering_tracking() function will not be shown unless the # --fulltrace command line option is specified. __tracebackhide__ = True testFailCount = 0 # zero unit test result counter testMessages = [] # create empty list to store test log messages scSystem = spacecraftSystem.SpacecraftSystem() scSystem.ModelTag = "spacecraftSystem" unitTaskName = "unitTask" # arbitrary name (don't change) unitProcessName = "TestProcess" # arbitrary name (don't change) # Create a sim module as an empty container unitTestSim = SimulationBaseClass.SimBaseClass() # Create test thread testProcessRate = macros.sec2nano(0.001) # update process rate update time testProc = unitTestSim.CreateNewProcess(unitProcessName) testProc.addTask(unitTestSim.CreateNewTask(unitTaskName, testProcessRate)) # Add test module to runtime call list unitTestSim.AddModelToTask(unitTaskName, scSystem) # Define initial conditions of primary spacecraft scSystem.primaryCentralSpacecraft.hub.mHub = 100 scSystem.primaryCentralSpacecraft.hub.r_BcB_B = [[0.0], [0.0], [0.0]] scSystem.primaryCentralSpacecraft.hub.IHubPntBc_B = [[500, 0.0, 0.0], [0.0, 200, 0.0], [0.0, 0.0, 300]] scSystem.primaryCentralSpacecraft.hub.r_CN_NInit = [[-4020338.690396649], [7490566.741852513], [5248299.211589362]] scSystem.primaryCentralSpacecraft.hub.v_CN_NInit = [[-5199.77710904224], [-3436.681645356935], [1041.576797498721]] scSystem.primaryCentralSpacecraft.hub.sigma_BNInit = [[0.0], [0.0], [0.0]] scSystem.primaryCentralSpacecraft.hub.omega_BN_BInit = [[0.5], [-0.4], [0.7]] # Define docking information dock1SC1 = spacecraftSystem.DockingData() dock1SC1.r_DB_B = [[1.0], [0.0], [0.0]] dock1SC1.dcm_DB = [[1.0, 0.0, 0.0], [0.0, 1.0, 0.0], [0.0, 0.0, 1.0]] dock1SC1.portName = "sc1port1" scSystem.primaryCentralSpacecraft.addDockingPort(dock1SC1) unitTestSim.panel1 = hingedRigidBodyStateEffector.HingedRigidBodyStateEffector() # Define Variable for panel 1 unitTestSim.panel1.mass = 100.0 unitTestSim.panel1.IPntS_S = [[100.0, 0.0, 0.0], [0.0, 50.0, 0.0], [0.0, 0.0, 50.0]] unitTestSim.panel1.d = 1.5 unitTestSim.panel1.k = 100.0 unitTestSim.panel1.c = 0.0 unitTestSim.panel1.r_HB_B = [[0.5], [0.0], [1.0]] unitTestSim.panel1.dcm_HB = [[-1.0, 0.0, 0.0], [0.0, -1.0, 0.0], [0.0, 0.0, 1.0]] unitTestSim.panel1.thetaInit = 5*numpy.pi/180.0 unitTestSim.panel1.thetaDotInit = 0.0 scSystem.primaryCentralSpacecraft.addStateEffector(unitTestSim.panel1) unitTestSim.earthGravBody = gravityEffector.GravBodyData() unitTestSim.earthGravBody.planetName = "earth_planet_data" unitTestSim.earthGravBody.mu = 0.3986004415E+15 # meters! unitTestSim.earthGravBody.isCentralBody = True scSystem.primaryCentralSpacecraft.gravField.gravBodies = spacecraftSystem.GravBodyVector([unitTestSim.earthGravBody]) sc2 = spacecraftSystem.SpacecraftUnit() sc2.hub.mHub = 100 sc2.hub.r_BcB_B = [[0.0], [0.0], [0.0]] sc2.hub.IHubPntBc_B = [[500, 0.0, 0.0], [0.0, 200, 0.0], [0.0, 0.0, 300]] sc2.spacecraftName = "spacecraft2" # Define docking information dock1SC2 = spacecraftSystem.DockingData() dock1SC2.r_DB_B = [[-1.0], [0.0], [0.0]] dock1SC2.dcm_DB = [[1.0, 0.0, 0.0], [0.0, 1.0, 0.0], [0.0, 0.0, 1.0]] dock1SC2.portName = "sc2port1" sc2.addDockingPort(dock1SC2) # Define docking information dock2SC2 = spacecraftSystem.DockingData() dock2SC2.r_DB_B = [[1.0], [0.0], [0.0]] dock2SC2.dcm_DB = [[1.0, 0.0, 0.0], [0.0, 1.0, 0.0], [0.0, 0.0, 1.0]] dock2SC2.portName = "sc2port2" sc2.addDockingPort(dock2SC2) # Define gravity for sc2 sc2.gravField.gravBodies = spacecraftSystem.GravBodyVector([unitTestSim.earthGravBody]) sc3 = spacecraftSystem.SpacecraftUnit() sc3.hub.mHub = 100 sc3.hub.r_BcB_B = [[0.0], [0.0], [0.0]] sc3.hub.IHubPntBc_B = [[500, 0.0, 0.0], [0.0, 200, 0.0], [0.0, 0.0, 300]] sc3.spacecraftName = "spacecraft3" # Define docking information dock1SC3 = spacecraftSystem.DockingData() dock1SC3.r_DB_B = [[-1.0], [0.0], [0.0]] dock1SC3.dcm_DB = [[1.0, 0.0, 0.0], [0.0, 1.0, 0.0], [0.0, 0.0, 1.0]] dock1SC3.portName = "sc3port1" sc3.addDockingPort(dock1SC3) unitTestSim.panel2 = hingedRigidBodyStateEffector.HingedRigidBodyStateEffector() # Define Variables for panel 2 unitTestSim.panel2.mass = 100.0 unitTestSim.panel2.IPntS_S = [[100.0, 0.0, 0.0], [0.0, 50.0, 0.0], [0.0, 0.0, 50.0]] unitTestSim.panel2.d = 1.5 unitTestSim.panel2.k = 100.0 unitTestSim.panel2.c = 0.0 unitTestSim.panel2.r_HB_B = [[-0.5], [0.0], [1.0]] unitTestSim.panel2.dcm_HB = [[1.0, 0.0, 0.0], [0.0, 1.0, 0.0], [0.0, 0.0, 1.0]] unitTestSim.panel2.thetaInit = 0.0 unitTestSim.panel2.thetaDotInit = 0.0 sc3.addStateEffector(unitTestSim.panel2) # Define gravity for sc2 sc3.gravField.gravBodies = spacecraftSystem.GravBodyVector([unitTestSim.earthGravBody]) # Attach spacecraft2 to spacecraft scSystem.attachSpacecraftToPrimary(sc2, dock1SC2.portName, dock1SC1.portName) # Attach spacecraft3 to spacecraft2 scSystem.attachSpacecraftToPrimary(sc3, dock1SC3.portName, dock2SC2.portName) dataLog = scSystem.primaryCentralSpacecraft.scStateOutMsg.recorder() unitTestSim.AddModelToTask(unitTaskName, dataLog) scLog = pythonVariableLogger.PythonVariableLogger({ "totOrbEnergy": lambda _: scSystem.primaryCentralSpacecraft.totOrbEnergy, "totOrbAngMomPntN_N": lambda _: scSystem.primaryCentralSpacecraft.totOrbAngMomPntN_N, "totRotAngMomPntC_N": lambda _: scSystem.primaryCentralSpacecraft.totRotAngMomPntC_N, "totRotEnergy": lambda _: scSystem.primaryCentralSpacecraft.totRotEnergy, }) unitTestSim.AddModelToTask(unitTaskName, scLog) unitTestSim.InitializeSimulation() stopTime = 1.0 unitTestSim.ConfigureStopTime(macros.sec2nano(stopTime)) unitTestSim.ExecuteSimulation() orbEnergy = unitTestSupport.addTimeColumn(scLog.times(), scLog.totOrbEnergy) orbAngMom_N = unitTestSupport.addTimeColumn(scLog.times(), scLog.totOrbAngMomPntN_N) rotAngMom_N = unitTestSupport.addTimeColumn(scLog.times(), scLog.totRotAngMomPntC_N) rotEnergy = unitTestSupport.addTimeColumn(scLog.times(), scLog.totRotEnergy) r_BN_NOutput = dataLog.r_BN_N sigma_BNOutput = dataLog.sigma_BN truePos = [ [-4072255.7737936215, 7456050.4649078, 5258610.029627514] ] trueSigma = [ [3.73034285e-01, -2.39564413e-03, 2.08570797e-01] ] initialOrbAngMom_N = [ [orbAngMom_N[0,1], orbAngMom_N[0,2], orbAngMom_N[0,3]] ] finalOrbAngMom = [ [orbAngMom_N[-1,1], orbAngMom_N[-1,2], orbAngMom_N[-1,3]] ] initialRotAngMom_N = [ [rotAngMom_N[0,1], rotAngMom_N[0,2], rotAngMom_N[0,3]] ] finalRotAngMom = [ [rotAngMom_N[-1,1], rotAngMom_N[-1,2], rotAngMom_N[-1,3]] ] initialOrbEnergy = [ [orbEnergy[0,1]] ] finalOrbEnergy = [ [orbEnergy[-1,1]] ] initialRotEnergy = [ [rotEnergy[0,1]] ] finalRotEnergy = [ [rotEnergy[-1,1]] ] plt.close("all") plt.figure() plt.clf() plt.plot(orbAngMom_N[:,0]*1e-9, (orbAngMom_N[:,1] - orbAngMom_N[0,1])/orbAngMom_N[0,1], orbAngMom_N[:,0]*1e-9, (orbAngMom_N[:,2] - orbAngMom_N[0,2])/orbAngMom_N[0,2], orbAngMom_N[:,0]*1e-9, (orbAngMom_N[:,3] - orbAngMom_N[0,3])/orbAngMom_N[0,3]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInOrbitalAngularMomentumSystem" PlotTitle = "Change in Orbital Angular Momentum with Gravity" format = r"width=0.8\textwidth" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(orbEnergy[:,0]*1e-9, (orbEnergy[:,1] - orbEnergy[0,1])/orbEnergy[0,1]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInOrbitalEnergySystem" PlotTitle = "Change in Orbital Energy with Gravity" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(rotAngMom_N[:,0]*1e-9, (rotAngMom_N[:,1] - rotAngMom_N[0,1])/rotAngMom_N[0,1], rotAngMom_N[:,0]*1e-9, (rotAngMom_N[:,2] - rotAngMom_N[0,2])/rotAngMom_N[0,2], rotAngMom_N[:,0]*1e-9, (rotAngMom_N[:,3] - rotAngMom_N[0,3])/rotAngMom_N[0,3]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInRotationalAngularMomentumSystem" PlotTitle = "Change In Rotational Angular Momentum with Gravity" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(rotEnergy[:,0]*1e-9, (rotEnergy[:,1] - rotEnergy[0,1])/rotEnergy[0,1]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInRotationalEnergySystem" PlotTitle = "Change In Rotational Energy with Gravity" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) if show_plots: plt.show() plt.close('all') accuracy = 1e-8 # for i in range(0,len(truePos)): # # check a vector values # if not unitTestSupport.isArrayEqualRelative(r_BN_NOutput[-1,:],truePos[i],3,accuracy): # testFailCount += 1 # testMessages.append("FAILED: Spacecraft Translation and Rotation Integrated test failed pos unit test") # # for i in range(0,len(trueSigma)): # # check a vector values # if not unitTestSupport.isArrayEqualRelative(sigma_BNOutput[-1,:],trueSigma[i],3,accuracy): # testFailCount += 1 # testMessages.append("FAILED: Spacecraft Translation and Rotation Integrated test failed attitude unit test") accuracy = 1e-10 for i in range(0,len(initialOrbAngMom_N)): # check a vector values if not unitTestSupport.isArrayEqualRelative(finalOrbAngMom[i],initialOrbAngMom_N[i],3,accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Translation and Rotation Integrated test failed orbital angular momentum unit test") for i in range(0,len(initialRotAngMom_N)): # check a vector values if not unitTestSupport.isArrayEqualRelative(finalRotAngMom[i],initialRotAngMom_N[i],3,accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Translation and Rotation Integrated test failed rotational angular momentum unit test") for i in range(0,len(initialRotEnergy)): # check a vector values if not unitTestSupport.isArrayEqualRelative(finalRotEnergy[i],initialRotEnergy[i],1,accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Translation and Rotation Integrated test failed rotational energy unit test") for i in range(0,len(initialOrbEnergy)): # check a vector values if not unitTestSupport.isArrayEqualRelative(finalOrbEnergy[i],initialOrbEnergy[i],1,accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Translation and Rotation Integrated test failed orbital energy unit test") if testFailCount == 0: print("PASSED: " + " Spacecraft Translation and Rotation Integrated Sim Test") assert testFailCount < 1, testMessages # return fail count and join into a single string all messages in the list # testMessage return [testFailCount, ''.join(testMessages)]
def SCConnectedAndUnconnected(show_plots): # The __tracebackhide__ setting influences pytest showing of tracebacks: # the mrp_steering_tracking() function will not be shown unless the # --fulltrace command line option is specified. __tracebackhide__ = True testFailCount = 0 # zero unit test result counter testMessages = [] # create empty list to store test log messages scSystem = spacecraftSystem.SpacecraftSystem() scSystem.ModelTag = "spacecraftSystem" unitTaskName = "unitTask" # arbitrary name (don't change) unitProcessName = "TestProcess" # arbitrary name (don't change) # Create a sim module as an empty container unitTestSim = SimulationBaseClass.SimBaseClass() # Create test thread testProcessRate = macros.sec2nano(0.001) # update process rate update time testProc = unitTestSim.CreateNewProcess(unitProcessName) testProc.addTask(unitTestSim.CreateNewTask(unitTaskName, testProcessRate)) # Add test module to runtime call list unitTestSim.AddModelToTask(unitTaskName, scSystem) # Define initial conditions of primary spacecraft scSystem.primaryCentralSpacecraft.hub.mHub = 100 scSystem.primaryCentralSpacecraft.hub.r_BcB_B = [[0.0], [0.0], [0.0]] scSystem.primaryCentralSpacecraft.hub.IHubPntBc_B = [[500, 0.0, 0.0], [0.0, 200, 0.0], [0.0, 0.0, 300]] scSystem.primaryCentralSpacecraft.hub.r_CN_NInit = [[-4020338.690396649], [7490566.741852513], [5248299.211589362]] scSystem.primaryCentralSpacecraft.hub.v_CN_NInit = [[-5199.77710904224], [-3436.681645356935], [1041.576797498721]] scSystem.primaryCentralSpacecraft.hub.sigma_BNInit = [[0.0], [0.0], [0.0]] scSystem.primaryCentralSpacecraft.hub.omega_BN_BInit = [[0.5], [-0.4], [0.7]] # Define docking information dock1SC1 = spacecraftSystem.DockingData() dock1SC1.r_DB_B = [[1.0], [0.0], [0.0]] dock1SC1.dcm_DB = [[1.0, 0.0, 0.0], [0.0, 1.0, 0.0], [0.0, 0.0, 1.0]] dock1SC1.portName = "sc1port1" scSystem.primaryCentralSpacecraft.addDockingPort(dock1SC1) unitTestSim.panel1 = hingedRigidBodyStateEffector.HingedRigidBodyStateEffector() # Define Variable for panel 1 unitTestSim.panel1.mass = 100.0 unitTestSim.panel1.IPntS_S = [[100.0, 0.0, 0.0], [0.0, 50.0, 0.0], [0.0, 0.0, 50.0]] unitTestSim.panel1.d = 1.5 unitTestSim.panel1.k = 100.0 unitTestSim.panel1.c = 0.0 unitTestSim.panel1.r_HB_B = [[0.5], [0.0], [1.0]] unitTestSim.panel1.dcm_HB = [[-1.0, 0.0, 0.0], [0.0, -1.0, 0.0], [0.0, 0.0, 1.0]] unitTestSim.panel1.thetaInit = 5*numpy.pi/180.0 unitTestSim.panel1.thetaDotInit = 0.0 scSystem.primaryCentralSpacecraft.addStateEffector(unitTestSim.panel1) unitTestSim.earthGravBody = gravityEffector.GravBodyData() unitTestSim.earthGravBody.planetName = "earth_planet_data" unitTestSim.earthGravBody.mu = 0.3986004415E+15 # meters! unitTestSim.earthGravBody.isCentralBody = True scSystem.primaryCentralSpacecraft.gravField.gravBodies = spacecraftSystem.GravBodyVector([unitTestSim.earthGravBody]) sc2 = spacecraftSystem.SpacecraftUnit() sc2.hub.mHub = 100 sc2.hub.r_BcB_B = [[0.0], [0.0], [0.0]] sc2.hub.IHubPntBc_B = [[500, 0.0, 0.0], [0.0, 200, 0.0], [0.0, 0.0, 300]] sc2.spacecraftName = "spacecraft2" # Define docking information dock1SC2 = spacecraftSystem.DockingData() dock1SC2.r_DB_B = [[-1.0], [0.0], [0.0]] dock1SC2.dcm_DB = [[1.0, 0.0, 0.0], [0.0, 1.0, 0.0], [0.0, 0.0, 1.0]] dock1SC2.portName = "sc2port1" sc2.addDockingPort(dock1SC2) # Define docking information dock2SC2 = spacecraftSystem.DockingData() dock2SC2.r_DB_B = [[1.0], [0.0], [0.0]] dock2SC2.dcm_DB = [[1.0, 0.0, 0.0], [0.0, 1.0, 0.0], [0.0, 0.0, 1.0]] dock2SC2.portName = "sc2port2" sc2.addDockingPort(dock2SC2) # Define gravity for sc2 sc2.gravField.gravBodies = spacecraftSystem.GravBodyVector([unitTestSim.earthGravBody]) sc3 = spacecraftSystem.SpacecraftUnit() sc3.hub.mHub = 100 sc3.hub.r_BcB_B = [[0.0], [0.0], [0.0]] sc3.hub.IHubPntBc_B = [[500, 0.0, 0.0], [0.0, 200, 0.0], [0.0, 0.0, 300]] sc3.spacecraftName = "spacecraft3" # Define docking information dock1SC3 = spacecraftSystem.DockingData() dock1SC3.r_DB_B = [[-1.0], [0.0], [0.0]] dock1SC3.dcm_DB = [[1.0, 0.0, 0.0], [0.0, 1.0, 0.0], [0.0, 0.0, 1.0]] dock1SC3.portName = "sc3port1" sc3.addDockingPort(dock1SC3) unitTestSim.panel2 = hingedRigidBodyStateEffector.HingedRigidBodyStateEffector() # Define Variables for panel 2 unitTestSim.panel2.mass = 100.0 unitTestSim.panel2.IPntS_S = [[100.0, 0.0, 0.0], [0.0, 50.0, 0.0], [0.0, 0.0, 50.0]] unitTestSim.panel2.d = 1.5 unitTestSim.panel2.k = 100.0 unitTestSim.panel2.c = 0.0 unitTestSim.panel2.r_HB_B = [[-0.5], [0.0], [1.0]] unitTestSim.panel2.dcm_HB = [[1.0, 0.0, 0.0], [0.0, 1.0, 0.0], [0.0, 0.0, 1.0]] unitTestSim.panel2.thetaInit = 0.0 unitTestSim.panel2.thetaDotInit = 0.0 sc3.addStateEffector(unitTestSim.panel2) # Define gravity for sc2 sc3.gravField.gravBodies = spacecraftSystem.GravBodyVector([unitTestSim.earthGravBody]) # Attach spacecraft2 to spacecraft scSystem.attachSpacecraftToPrimary(sc2, dock1SC2.portName, dock1SC1.portName) # Attach spacecraft3 to spacecraft2 scSystem.attachSpacecraftToPrimary(sc3, dock1SC3.portName, dock2SC2.portName) # Define two independent spacecraft sc4 = spacecraftSystem.SpacecraftUnit() sc4.hub.mHub = 100 sc4.hub.r_BcB_B = [[0.0], [0.0], [0.1]] sc4.hub.IHubPntBc_B = [[500, 0.0, 0.0], [0.0, 200, 0.0], [0.0, 0.0, 300]] sc4.hub.r_CN_NInit = [[7490566.741852513],[-4020338.690396649],[5248299.211589362]] sc4.hub.v_CN_NInit = [[-5199.77710904224], [-3436.681645356935], [1041.576797498721]] sc4.hub.sigma_BNInit = [[0.0], [0.0], [0.0]] sc4.hub.omega_BN_BInit = [[0.5], [-0.4], [0.7]] sc4.spacecraftName = "spacecraft4" # Define gravity for sc4 sc4.gravField.gravBodies = spacecraftSystem.GravBodyVector([unitTestSim.earthGravBody]) unitTestSim.panel3 = hingedRigidBodyStateEffector.HingedRigidBodyStateEffector() # Define Variables for panel 1 on sc4 unitTestSim.panel3.mass = 100.0 unitTestSim.panel3.IPntS_S = [[100.0, 0.0, 0.0], [0.0, 50.0, 0.0], [0.0, 0.0, 50.0]] unitTestSim.panel3.d = 1.5 unitTestSim.panel3.k = 100.0 unitTestSim.panel3.c = 0.0 unitTestSim.panel3.r_HB_B = [[-0.5], [0.0], [1.0]] unitTestSim.panel3.dcm_HB = [[1.0, 0.0, 0.0], [0.0, 1.0, 0.0], [0.0, 0.0, 1.0]] unitTestSim.panel3.thetaInit = 0.0 unitTestSim.panel3.thetaDotInit = 0.0 sc4.addStateEffector(unitTestSim.panel3) scSystem.addSpacecraftUndocked(sc4) sc5 = spacecraftSystem.SpacecraftUnit() sc5.hub.mHub = 100 sc5.hub.r_BcB_B = [[0.1], [0.0], [0.0]] sc5.hub.IHubPntBc_B = [[500, 0.0, 0.0], [0.0, 200, 0.0], [0.0, 0.0, 300]] sc5.hub.r_CN_NInit = [[5248299.211589362],[7490566.741852513],[-4020338.690396649]] sc5.hub.v_CN_NInit = [[-5199.77710904224], [-3436.681645356935], [1041.576797498721]] sc5.hub.sigma_BNInit = [[0.0], [0.0], [0.0]] sc5.hub.omega_BN_BInit = [[0.5], [-0.4], [0.7]] sc5.spacecraftName = "spacecraft5" # Define gravity for sc4 sc5.gravField.gravBodies = spacecraftSystem.GravBodyVector([unitTestSim.earthGravBody]) scSystem.addSpacecraftUndocked(sc5) dataLog = scSystem.primaryCentralSpacecraft.scStateOutMsg.recorder() dataLog4 = sc4.scStateOutMsg.recorder() dataLog5 = sc5.scStateOutMsg.recorder() dataEngLog = scSystem.primaryCentralSpacecraft.scEnergyMomentumOutMsg.recorder() dataEngLog4 = sc4.scEnergyMomentumOutMsg.recorder() dataEngLog5 = sc5.scEnergyMomentumOutMsg.recorder() unitTestSim.AddModelToTask(unitTaskName, dataLog) unitTestSim.AddModelToTask(unitTaskName, dataLog4) unitTestSim.AddModelToTask(unitTaskName, dataLog5) unitTestSim.AddModelToTask(unitTaskName, dataEngLog) unitTestSim.AddModelToTask(unitTaskName, dataEngLog4) unitTestSim.AddModelToTask(unitTaskName, dataEngLog5) unitTestSim.InitializeSimulation() stopTime = 1.0 unitTestSim.ConfigureStopTime(macros.sec2nano(stopTime)) unitTestSim.ExecuteSimulation() r_BN_NOutput = addTimeColumn(dataLog.times(), dataLog.r_BN_N) sigma_BNOutput = addTimeColumn(dataLog.times(), dataLog.sigma_BN) r_BN_NOutput1 = addTimeColumn(dataLog4.times(), dataLog4.r_BN_N) sigma_BNOutput1 = addTimeColumn(dataLog4.times(), dataLog4.sigma_BN) r_BN_NOutput2 = addTimeColumn(dataLog5.times(), dataLog5.r_BN_N) sigma_BNOutput2 = addTimeColumn(dataLog5.times(), dataLog5.sigma_BN) rotEnergy = addTimeColumn(dataEngLog.times(), dataEngLog.spacecraftRotEnergy) orbEnergy = addTimeColumn(dataEngLog.times(), dataEngLog.spacecraftOrbEnergy) rotAngMom_N = addTimeColumn(dataEngLog.times(), dataEngLog.spacecraftRotAngMomPntC_N) orbAngMom_N = addTimeColumn(dataEngLog.times(), dataEngLog.spacecraftOrbAngMomPntN_N) rotEnergy1 = addTimeColumn(dataEngLog4.times(), dataEngLog4.spacecraftRotEnergy) orbEnergy1 = addTimeColumn(dataEngLog4.times(), dataEngLog4.spacecraftOrbEnergy) rotAngMom1_N = addTimeColumn(dataEngLog4.times(), dataEngLog4.spacecraftRotAngMomPntC_N) orbAngMom1_N = addTimeColumn(dataEngLog4.times(), dataEngLog4.spacecraftOrbAngMomPntN_N) rotEnergy2 = addTimeColumn(dataEngLog5.times(), dataEngLog5.spacecraftRotEnergy) orbEnergy2 = addTimeColumn(dataEngLog5.times(), dataEngLog5.spacecraftOrbEnergy) rotAngMom2_N = addTimeColumn(dataEngLog5.times(), dataEngLog5.spacecraftRotAngMomPntC_N) orbAngMom2_N = addTimeColumn(dataEngLog5.times(), dataEngLog5.spacecraftOrbAngMomPntN_N) truePos = [ [-4072255.7737936215, 7456050.4649078, 5258610.029627514] ] trueSigma = [ [3.73034285e-01, -2.39564413e-03, 2.08570797e-01] ] initialOrbAngMom_N = [ [orbAngMom_N[0,1], orbAngMom_N[0,2], orbAngMom_N[0,3]] ] finalOrbAngMom = [ [orbAngMom_N[-1,1], orbAngMom_N[-1,2], orbAngMom_N[-1,3]] ] initialRotAngMom_N = [ [rotAngMom_N[0,1], rotAngMom_N[0,2], rotAngMom_N[0,3]] ] finalRotAngMom = [ [rotAngMom_N[-1,1], rotAngMom_N[-1,2], rotAngMom_N[-1,3]] ] initialOrbEnergy = [ [orbEnergy[0,1]] ] finalOrbEnergy = [ [orbEnergy[-1,1]] ] initialRotEnergy = [ [rotEnergy[0,1]] ] finalRotEnergy = [ [rotEnergy[-1,1]] ] plt.figure() plt.clf() plt.plot(orbAngMom_N[:,0]*1e-9, (orbAngMom_N[:,1] - orbAngMom_N[0,1])/orbAngMom_N[0,1], orbAngMom_N[:,0]*1e-9, (orbAngMom_N[:,2] - orbAngMom_N[0,2])/orbAngMom_N[0,2], orbAngMom_N[:,0]*1e-9, (orbAngMom_N[:,3] - orbAngMom_N[0,3])/orbAngMom_N[0,3]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInOrbitalAngularMomentum" PlotTitle = "Change in Orbital Angular Momentum with Gravity" format = r"width=0.8\textwidth" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(orbEnergy[:,0]*1e-9, (orbEnergy[:,1] - orbEnergy[0,1])/orbEnergy[0,1]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInOrbitalEnergy" PlotTitle = "Change in Orbital Energy with Gravity" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(rotAngMom_N[:,0]*1e-9, (rotAngMom_N[:,1] - rotAngMom_N[0,1])/rotAngMom_N[0,1], rotAngMom_N[:,0]*1e-9, (rotAngMom_N[:,2] - rotAngMom_N[0,2])/rotAngMom_N[0,2], rotAngMom_N[:,0]*1e-9, (rotAngMom_N[:,3] - rotAngMom_N[0,3])/rotAngMom_N[0,3]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInRotationalAngularMomentum" PlotTitle = "Change In Rotational Angular Momentum with Gravity" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(rotEnergy[:,0]*1e-9, (rotEnergy[:,1] - rotEnergy[0,1])/rotEnergy[0,1]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInRotationalEnergy" PlotTitle = "Change In Rotational Energy with Gravity" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(orbAngMom1_N[:,0]*1e-9, (orbAngMom1_N[:,1] - orbAngMom1_N[0,1])/orbAngMom1_N[0,1], orbAngMom1_N[:,0]*1e-9, (orbAngMom1_N[:,2] - orbAngMom1_N[0,2])/orbAngMom1_N[0,2], orbAngMom1_N[:,0]*1e-9, (orbAngMom1_N[:,3] - orbAngMom1_N[0,3])/orbAngMom1_N[0,3]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInOrbitalAngularMomentum1" PlotTitle = "Change in Orbital Angular Momentum with Gravity" format = r"width=0.8\textwidth" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(orbEnergy1[:,0]*1e-9, (orbEnergy1[:,1] - orbEnergy1[0,1])/orbEnergy1[0,1]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInOrbitalEnergy1" PlotTitle = "Change in Orbital Energy with Gravity" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(rotAngMom1_N[:,0]*1e-9, (rotAngMom1_N[:,1] - rotAngMom1_N[0,1])/rotAngMom1_N[0,1], rotAngMom1_N[:,0]*1e-9, (rotAngMom1_N[:,2] - rotAngMom1_N[0,2])/rotAngMom1_N[0,2], rotAngMom1_N[:,0]*1e-9, (rotAngMom1_N[:,3] - rotAngMom1_N[0,3])/rotAngMom1_N[0,3]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInRotationalAngularMomentum1" PlotTitle = "Change In Rotational Angular Momentum with Gravity" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(rotEnergy1[:,0]*1e-9, (rotEnergy1[:,1] - rotEnergy1[0,1])/rotEnergy1[0,1]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInRotationalEnergy1" PlotTitle = "Change In Rotational Energy with Gravity" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(orbAngMom2_N[:,0]*1e-9, (orbAngMom2_N[:,1] - orbAngMom2_N[0,1])/orbAngMom2_N[0,1], orbAngMom2_N[:,0]*1e-9, (orbAngMom2_N[:,2] - orbAngMom2_N[0,2])/orbAngMom2_N[0,2], orbAngMom2_N[:,0]*1e-9, (orbAngMom2_N[:,3] - orbAngMom2_N[0,3])/orbAngMom2_N[0,3]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInOrbitalAngularMomentum2" PlotTitle = "Change in Orbital Angular Momentum with Gravity" format = r"width=0.8\textwidth" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(orbEnergy2[:,0]*1e-9, (orbEnergy2[:,1] - orbEnergy2[0,1])/orbEnergy2[0,1]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInOrbitalEnergy2" PlotTitle = "Change in Orbital Energy with Gravity" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(rotAngMom2_N[:,0]*1e-9, (rotAngMom2_N[:,1] - rotAngMom2_N[0,1])/rotAngMom2_N[0,1], rotAngMom2_N[:,0]*1e-9, (rotAngMom2_N[:,2] - rotAngMom2_N[0,2])/rotAngMom2_N[0,2], rotAngMom2_N[:,0]*1e-9, (rotAngMom2_N[:,3] - rotAngMom2_N[0,3])/rotAngMom2_N[0,3]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInRotationalAngularMomentum2" PlotTitle = "Change In Rotational Angular Momentum with Gravity" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(rotEnergy2[:,0]*1e-9, (rotEnergy2[:,1] - rotEnergy2[0,1])/rotEnergy2[0,1]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") PlotName = "ChangeInRotationalEnergy2" PlotTitle = "Change In Rotational Energy with Gravity" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) if show_plots: plt.show() plt.close('all') accuracy = 1e-8 # for i in range(0,len(truePos)): # # check a vector values # if not unitTestSupport.isArrayEqualRelative(r_BN_NOutput[-1,:],truePos[i],3,accuracy): # testFailCount += 1 # testMessages.append("FAILED: Spacecraft Translation and Rotation Integrated test failed pos unit test") # # for i in range(0,len(trueSigma)): # # check a vector values # if not unitTestSupport.isArrayEqualRelative(sigma_BNOutput[-1,:],trueSigma[i],3,accuracy): # testFailCount += 1 # testMessages.append("FAILED: Spacecraft Translation and Rotation Integrated test failed attitude unit test") accuracy = 1e-10 for i in range(0,len(initialOrbAngMom_N)): # check a vector values if not unitTestSupport.isArrayEqualRelative(finalOrbAngMom[i],initialOrbAngMom_N[i],3,accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Translation and Rotation Integrated test failed orbital angular momentum unit test") for i in range(0,len(initialRotAngMom_N)): # check a vector values if not unitTestSupport.isArrayEqualRelative(finalRotAngMom[i],initialRotAngMom_N[i],3,accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Translation and Rotation Integrated test failed rotational angular momentum unit test") for i in range(0,len(initialRotEnergy)): # check a vector values if not unitTestSupport.isArrayEqualRelative(finalRotEnergy[i],initialRotEnergy[i],1,accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Translation and Rotation Integrated test failed rotational energy unit test") for i in range(0,len(initialOrbEnergy)): # check a vector values if not unitTestSupport.isArrayEqualRelative(finalOrbEnergy[i],initialOrbEnergy[i],1,accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Translation and Rotation Integrated test failed orbital energy unit test") if testFailCount == 0: print("PASSED: " + " Spacecraft Translation and Rotation Integrated Sim Test") assert testFailCount < 1, testMessages # return fail count and join into a single string all messages in the list # testMessage return [testFailCount, ''.join(testMessages)] if __name__ == "__main__": # SCConnected(True) SCConnectedAndUnconnected(True)