Source code for test_spacecraft


# ISC License
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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
from random import random

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 spacecraft
from Basilisk.utilities import macros
from Basilisk.simulation import gravityEffector
from Basilisk.simulation import extForceTorque
from Basilisk.utilities import RigidBodyKinematics
from Basilisk.utilities import simIncludeGravBody
from Basilisk.simulation import GravityGradientEffector
from Basilisk.architecture import messaging

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", ["SCTranslation" , "SCTransAndRotation" , "SCRotation" , "SCTransBOE" , "SCPointBVsPointC" , "scOptionalRef" , "scAccumDV" , "scAccumDVExtForce" ]) def test_spacecraftAllTest(show_plots, function): """Module Unit Test""" if function == "scOptionalRef": [testResults, testMessage] = eval(function + '(show_plots, 1e-3)') elif function == "scAccumDV" or function == "scAccumDVExtForce": [testResults, testMessage] = eval(function + '()') else: [testResults, testMessage] = eval(function + '(show_plots)') assert testResults < 1, testMessage
[docs]def SCTranslation(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 scObject = spacecraft.Spacecraft() scObject.ModelTag = "spacecraftBody" 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(0.01) # 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, scObject) unitTestSim.earthGravBody = gravityEffector.GravBodyData() unitTestSim.earthGravBody.planetName = "earth_planet_data" unitTestSim.earthGravBody.mu = 0.3986004415E+15 # meters! unitTestSim.earthGravBody.isCentralBody = True scObject.gravField.gravBodies = spacecraft.GravBodyVector([unitTestSim.earthGravBody]) dataLog = scObject.scStateOutMsg.recorder() unitTestSim.AddModelToTask(unitTaskName, dataLog) # Define initial conditions of the spacecraft scObject.hub.mHub = 100 scObject.hub.r_CN_NInit = [[-4020338.690396649], [7490566.741852513], [5248299.211589362]] scObject.hub.v_CN_NInit = [[-5199.77710904224], [-3436.681645356935], [1041.576797498721]] scObjectLog = scObject.logger(["totOrbAngMomPntN_N", "totOrbEnergy"]) unitTestSim.AddModelToTask(unitTaskName, scObjectLog) unitTestSim.InitializeSimulation() accuracy = 1e-3 if not unitTestSupport.isArrayEqual(scObject.scStateOutMsg.read().r_BN_N, [item for sublist in scObject.hub.r_CN_NInit for item in sublist], 3, accuracy): testFailCount += 1 testMessages.append("FAILED: SCHub Translation test failed init pos msg unit test") if not unitTestSupport.isArrayEqual(scObject.scStateOutMsg.read().v_BN_N, [item for sublist in scObject.hub.v_CN_NInit for item in sublist], 3, accuracy): testFailCount += 1 testMessages.append("FAILED: SCHub Translation test failed init pos msg unit test") stopTime = 10.0 unitTestSim.ConfigureStopTime(macros.sec2nano(stopTime)) unitTestSim.ExecuteSimulation() orbAngMom_N = unitTestSupport.addTimeColumn(scObjectLog.times(), scObjectLog.totOrbAngMomPntN_N) orbEnergy = unitTestSupport.addTimeColumn(scObjectLog.times(), scObjectLog.totOrbEnergy) 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") unitTestSupport.writeFigureLaTeX("scPlusChangeInOrbitalAngularMomentumTranslationOnly", "Change in Orbital Angular Momentum Translation Only", plt, r"width=0.8\textwidth", 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") unitTestSupport.writeFigureLaTeX("scPlusChangeInOrbitalEnergyTranslationOnly", "Change in Orbital Energy Translation Only", plt, r"width=0.8\textwidth", path) if show_plots: plt.show() plt.close('all') moduleOutput = dataLog.r_BN_N truePos = [ [-4072255.7737936215, 7456050.4649078, 5258610.029627514] ] 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]] ] initialOrbEnergy = [ [orbEnergy[0,1]] ] finalOrbEnergy = [ [orbEnergy[-1,1]] ] accuracy = 1e-10 for i in range(0,len(truePos)): # check a vector values if not unitTestSupport.isArrayEqualRelative(moduleOutput[-1,:],truePos[i],3,accuracy): testFailCount += 1 testMessages.append("FAILED: SCHub Translation test failed pos unit test") 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: SCHub Translation test failed orbital angular momentum 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: SCHub Translation test failed orbital energy unit test") if testFailCount == 0: print("PASSED: " + " SCHub Translation 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)]
[docs]def SCTransAndRotation(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 scObject = spacecraft.Spacecraft() scObject.ModelTag = "spacecraftBody" 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, scObject) unitTestSim.earthGravBody = gravityEffector.GravBodyData() unitTestSim.earthGravBody.planetName = "earth_planet_data" unitTestSim.earthGravBody.mu = 0.3986004415E+15 # meters! unitTestSim.earthGravBody.isCentralBody = True scObject.gravField.gravBodies = spacecraft.GravBodyVector([unitTestSim.earthGravBody]) dataLog = scObject.scStateOutMsg.recorder() unitTestSim.AddModelToTask(unitTaskName, dataLog) # Define initial conditions of the spacecraft scObject.hub.mHub = 100 scObject.hub.r_BcB_B = [[0.0], [0.0], [0.0]] scObject.hub.IHubPntBc_B = [[500, 0.0, 0.0], [0.0, 200, 0.0], [0.0, 0.0, 300]] scObject.hub.r_CN_NInit = [[-4020338.690396649], [7490566.741852513], [5248299.211589362]] scObject.hub.v_CN_NInit = [[-5199.77710904224], [-3436.681645356935], [1041.576797498721]] scObject.hub.sigma_BNInit = [[0.0], [0.0], [0.0]] scObject.hub.omega_BN_BInit = [[0.5], [-0.4], [0.7]] scObjectLog = scObject.logger(["totOrbAngMomPntN_N", "totRotAngMomPntC_N", "totOrbEnergy", "totRotEnergy"]) unitTestSim.AddModelToTask(unitTaskName, scObjectLog) unitTestSim.InitializeSimulation() stopTime = 10.0 unitTestSim.ConfigureStopTime(macros.sec2nano(stopTime)) unitTestSim.ExecuteSimulation() orbAngMom_N = unitTestSupport.addTimeColumn(scObjectLog.times(), scObjectLog.totOrbAngMomPntN_N) rotAngMom_N = unitTestSupport.addTimeColumn(scObjectLog.times(), scObjectLog.totRotAngMomPntC_N) rotEnergy = unitTestSupport.addTimeColumn(scObjectLog.times(), scObjectLog.totRotEnergy) orbEnergy = unitTestSupport.addTimeColumn(scObjectLog.times(), scObjectLog.totOrbEnergy) 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") unitTestSupport.writeFigureLaTeX("scPlusChangeInOrbitalAngularMomentumTranslationAndRotation", "Change in Orbital Angular Momentum Translation And Rotation", plt, r"width=0.8\textwidth", 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") unitTestSupport.writeFigureLaTeX("scPlusChangeInOrbitalEnergyTranslationAndRotation", "Change in Orbital Energy Translation And Rotation", plt, r"width=0.8\textwidth", 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") unitTestSupport.writeFigureLaTeX("scPlusChangeInRotationalAngularMomentumTranslationAndRotation", "Change in Rotational Angular Momentum Translation And Rotation", plt, r"width=0.8\textwidth", 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") unitTestSupport.writeFigureLaTeX("scPlusChangeInRotationalEnergyTranslationAndRotation", "Change in Rotational Energy Translation And Rotation", plt, r"width=0.8\textwidth", 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)]
[docs]def SCRotation(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 scObject = spacecraft.Spacecraft() scObject.ModelTag = "spacecraftBody" 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 timeStep = 0.001 testProcessRate = macros.sec2nano(timeStep) # 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, scObject) dataLog = scObject.scStateOutMsg.recorder() unitTestSim.AddModelToTask(unitTaskName, dataLog) # Define initial conditions of the spacecraft scObject.hub.IHubPntBc_B = [[500, 0.0, 0.0], [0.0, 200, 0.0], [0.0, 0.0, 300]] scObject.hub.omega_BN_BInit = [[0.5], [-0.4], [0.7]] # BOE for rotational dynamics h = numpy.dot(numpy.asarray(scObject.hub.IHubPntBc_B),numpy.asarray(scObject.hub.omega_BN_BInit).flatten()) H = numpy.linalg.norm(h) n3_B = -h/H # Find DCM n2_B = numpy.zeros(3) n2_B[1] = 0.1 n2_B[0] = -n2_B[1]*n3_B[1]/n3_B[0] n2_B = n2_B/numpy.linalg.norm(n2_B) n1_B = numpy.cross(n2_B,n3_B) n1_B = n1_B/(numpy.linalg.norm(n1_B)) dcm_BN = numpy.zeros([3,3]) dcm_BN[:,0] = n1_B dcm_BN[:,1] = n2_B dcm_BN[:,2] = n3_B h3_N = numpy.array([0,0,-H]) h3_B = numpy.dot(dcm_BN,h3_N) h3_Ncheck = numpy.dot(dcm_BN.transpose(),h3_B) sigmaCalc = RigidBodyKinematics.C2MRP(dcm_BN) scObject.hub.sigma_BNInit = [[sigmaCalc[0]], [sigmaCalc[1]], [sigmaCalc[2]]] scObjectLog = scObject.logger(["totRotAngMomPntC_N", "totRotEnergy"]) unitTestSim.AddModelToTask(unitTaskName, scObjectLog) unitTestSim.InitializeSimulation() stopTime = 10.0 unitTestSim.ConfigureStopTime(macros.sec2nano(stopTime)) unitTestSim.ExecuteSimulation() rotAngMom_N = unitTestSupport.addTimeColumn(scObjectLog.times(), scObjectLog.totRotAngMomPntC_N) rotEnergy = unitTestSupport.addTimeColumn(scObjectLog.times(), scObjectLog.totRotEnergy) rotAngMomMag = numpy.zeros(len(rotAngMom_N)) for i in range(0,len(rotAngMom_N)): rotAngMomMag[i] = numpy.linalg.norm(numpy.asarray(rotAngMom_N[i,1:4])) trueSigma = [ [5.72693314e-01, 5.10734375e-01, -3.07377611e-01] ] initialRotAngMom_N = [ [numpy.linalg.norm(numpy.asarray(rotAngMom_N[0,1:4]))] ] finalRotAngMom = [ [numpy.linalg.norm(numpy.asarray(rotAngMom_N[-1,1:4]))] ] initialRotEnergy = [ [rotEnergy[0,1]] ] finalRotEnergy = [ [rotEnergy[-1,1]] ] moduleOutput = addTimeColumn(dataLog.times(), dataLog.sigma_BN) omega_BNOutput = addTimeColumn(dataLog.times(), dataLog.omega_BN_B) check = 0 for i in range(0,len(moduleOutput)): if check == 0 and moduleOutput[i+1,2] < moduleOutput[i,2]: check = 1 if check == 1 and moduleOutput[i+1,2] > moduleOutput[i,2]: check = 2 index = i+1 break sigmaBeforeSwitch = moduleOutput[index-1,1:4] sigmaBeforeBefore = moduleOutput[index-2,1:4] sigmaAfterSwitch = moduleOutput[index,:] deltaT = (moduleOutput[index-1,0] - moduleOutput[index-2,0])*1e-9 yPrime = (sigmaBeforeSwitch - sigmaBeforeBefore)/deltaT sigmaGhost = sigmaBeforeSwitch + yPrime*deltaT sigmaAfterAnalytical = - sigmaGhost/numpy.dot(numpy.linalg.norm(numpy.asarray(sigmaGhost)),numpy.linalg.norm(numpy.asarray(sigmaGhost))) timeArray = numpy.zeros(5) sigmaArray = numpy.zeros([3,5]) omegaAnalyticalArray = numpy.zeros([3,5]) omegaArray = numpy.zeros([4,5]) for i in range(0, 5): idx = int(stopTime/timeStep*(i+1)/5) timeArray[i] = moduleOutput[idx, 0] sigmaArray[:, i] = moduleOutput[idx, 1:4] sigma = sigmaArray[:, i] sigmaNorm = numpy.linalg.norm(sigma) sigma1 = sigma[0] sigma2 = sigma[1] sigma3 = sigma[2] omegaArray[:,i] = omega_BNOutput[idx, :] omegaAnalyticalArray[0,i] = -H/(1 + sigmaNorm**2)**2*(8*sigma1*sigma3 - 4*sigma2*(1 - sigmaNorm**2))/scObject.hub.IHubPntBc_B[0][0] omegaAnalyticalArray[1,i] = -H/(1 + sigmaNorm**2)**2*(8*sigma2*sigma3 + 4*sigma1*(1 - sigmaNorm**2))/scObject.hub.IHubPntBc_B[1][1] omegaAnalyticalArray[2,i] = -H/(1 + sigmaNorm**2)**2*(4*(-sigma1**2 - sigma2**2 + sigma3**2) + (1 - sigmaNorm**2)**2)/scObject.hub.IHubPntBc_B[2][2] plt.close("all") # clear out earlier figures plt.figure() plt.clf() plt.plot(moduleOutput[:,0]*1e-9, moduleOutput[:,1], moduleOutput[:,0]*1e-9, moduleOutput[:,2], moduleOutput[:,0]*1e-9, moduleOutput[:,3]) plt.plot(moduleOutput[index,0]*1e-9, moduleOutput[index,1],'bo') plt.plot(moduleOutput[index,0]*1e-9, sigmaGhost[0],'yo') plt.plot(moduleOutput[index-1,0]*1e-9, moduleOutput[index-1,1],'bo') plt.xlabel("Time (s)") plt.ylabel("MRPs") unitTestSupport.writeFigureLaTeX("scPlusMRPs", "Attitude of Spacecraft in MRPs", plt, r"width=0.8\textwidth", path) plt.figure() plt.clf() plt.plot(moduleOutput[index - 3: index + 3,0]*1e-9, moduleOutput[index - 3: index + 3,1],"b") plt.plot(moduleOutput[index-1,0]*1e-9, moduleOutput[index-1,1],'bo', label = "Basilisk " + r"$\sigma_{1,t-1}$") plt.plot(moduleOutput[index,0]*1e-9, moduleOutput[index,1],'ro', label = "Basilisk " + r"$\sigma_{1,t}$") plt.plot(moduleOutput[index,0]*1e-9, sigmaGhost[0],'ko', label = "Basilisk " + r"$\sigma_{1,0}$") plt.plot([moduleOutput[index-1,0]*1e-9, moduleOutput[index,0]*1e-9], [moduleOutput[index-1,1], sigmaGhost[0]],'--k') axes = plt.gca() axes.set_ylim([-0.5,0.5]) plt.legend(loc ='upper right',numpoints = 1) plt.xlabel("Time (s)") plt.ylabel("MRPs") unitTestSupport.writeFigureLaTeX("scPlusMRPSwitching", "MRP Switching", plt, r"width=0.8\textwidth", path) plt.figure() plt.clf() plt.plot(rotAngMom_N[:,0]*1e-9, (rotAngMomMag - rotAngMomMag[0])/rotAngMomMag[0]) plt.xlabel("Time (s)") plt.ylabel("Relative Difference") unitTestSupport.writeFigureLaTeX("scPlusChangeInRotationalAngularMomentumRotationOnly", "Change in Rotational Angular Momentum Rotation Only", plt, r"width=0.8\textwidth", 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") unitTestSupport.writeFigureLaTeX("scPlusChangeInRotationalEnergyRotationOnly", "Change in Rotational Energy Rotation Only", plt, r"width=0.8\textwidth", path) plt.figure() plt.clf() plt.plot(omega_BNOutput[:,0]*1e-9,omega_BNOutput[:,1],label = r"$\omega_1$" + " Basilisk") plt.plot(omega_BNOutput[:,0]*1e-9,omega_BNOutput[:,2],label = r"$\omega_2$" + " Basilisk") plt.plot(omega_BNOutput[:,0]*1e-9,omega_BNOutput[:,3], label = r"$\omega_3$" + " Basilisk") plt.plot(timeArray*1e-9,omegaAnalyticalArray[0,:],'bo', label = r"$\omega_1$" + " BOE") plt.plot(timeArray*1e-9,omegaAnalyticalArray[1,:],'go', label = r"$\omega_2$" + " BOE") plt.plot(timeArray*1e-9,omegaAnalyticalArray[2,:],'ro', label = r"$\omega_3$" + " BOE") plt.xlabel("Time (s)") plt.ylabel("Angular Velocity (rad/s)") plt.legend(loc ='lower right',numpoints = 1, prop = {'size': 6.5}) unitTestSupport.writeFigureLaTeX("scPlusBasiliskVsBOECalcForRotation", "Basilisk Vs BOE Calc For Rotation", plt, r"width=0.8\textwidth", path) if show_plots: plt.show() plt.close("all") moduleOutput = dataLog.sigma_BN accuracy = 1e-8 for i in range(0,len(trueSigma)): # check a vector values if not unitTestSupport.isArrayEqualRelative(moduleOutput[-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(initialRotAngMom_N)): # check a vector values if not unitTestSupport.isArrayEqualRelative(finalRotAngMom[i],initialRotAngMom_N[i],1,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 Rotation Integrated test failed rotational energy unit test") omegaArray = (numpy.delete(omegaArray, 0, 0)).transpose() omegaAnalyticalArray = omegaAnalyticalArray.transpose() for i in range(0,len(omegaAnalyticalArray)): # check a vector values if not unitTestSupport.isArrayEqualRelative(omegaArray[i],omegaAnalyticalArray[i],3,accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Rotation Integrated test Rotational BOE unit test") accuracy = 1e-5 if not unitTestSupport.isArrayEqualRelative(numpy.delete(sigmaAfterSwitch, 0,), sigmaAfterAnalytical,1,accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Rotation Integrated test failed MRP Switching unit test") if testFailCount == 0: print("PASSED: " + "Spacecraft Rotation Integrated test") assert testFailCount < 1, testMessages # return fail count and join into a single string all messages in the list # testMessage return [testFailCount, ''.join(testMessages)]
[docs]def SCTransBOE(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 scObject = spacecraft.Spacecraft() scObject.ModelTag = "spacecraftBody" 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 timeStep = 0.1 testProcessRate = macros.sec2nano(timeStep) # 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, scObject) # Define conditions for the forces and times F1 = 3. F2 = -7. t1 = 3. t2 = 6. t3 = 10. # Add external force and torque extFTObject = extForceTorque.ExtForceTorque() extFTObject.ModelTag = "externalDisturbance" extFTObject.extTorquePntB_B = [[0], [0], [0]] extFTObject.extForce_B = [[F1], [0], [0]] scObject.addDynamicEffector(extFTObject) unitTestSim.AddModelToTask(unitTaskName, extFTObject) dataLog = scObject.scStateOutMsg.recorder() unitTestSim.AddModelToTask(unitTaskName, dataLog) # Define initial conditions of the spacecraft scObject.hub.mHub = 100 scObject.hub.r_BcB_B = [[0.0], [0.0], [0.0]] scObject.hub.IHubPntBc_B = [[500, 0.0, 0.0], [0.0, 200, 0.0], [0.0, 0.0, 300]] # Set the initial values for the states scObject.hub.r_CN_NInit = [[0.0], [0.0], [0.0]] scObject.hub.v_CN_NInit = [[0.0], [0.0], [0.0]] scObject.hub.sigma_BNInit = [[0.0], [0.0], [0.0]] scObject.hub.omega_BN_BInit = [[0.0], [0.0], [0.0]] unitTestSim.InitializeSimulation() stopTime = t1 unitTestSim.ConfigureStopTime(macros.sec2nano(stopTime)) unitTestSim.ExecuteSimulation() extFTObject.extTorquePntB_B = [[0], [0], [0]] extFTObject.extForce_B = [[0], [0], [0]] stopTime = t2 unitTestSim.ConfigureStopTime(macros.sec2nano(stopTime)) unitTestSim.ExecuteSimulation() extFTObject.extTorquePntB_B = [[0], [0], [0]] extFTObject.extForce_B = [[F2], [0], [0]] stopTime = t3 unitTestSim.ConfigureStopTime(macros.sec2nano(stopTime)) unitTestSim.ExecuteSimulation() r_BN_NOutput = addTimeColumn(dataLog.times(), dataLog.r_BN_N) v_BN_NOutput = addTimeColumn(dataLog.times(), dataLog.v_BN_N) # BOE calcs a1 = F1/scObject.hub.mHub a2 = F2/scObject.hub.mHub v1 = a1*t1 v2 = v1 v3 = v2 + a2*(t3-t2) x1 = 0.5*v1*t1 x2 = x1 + v2*(t2-t1) t0 = t2 - v2/a2 x3 = x2 + 0.5*v2*(t0-t2) + 0.5*v3*(t3-t0) # truth and Basilisk truthV = [v1, v2, v3] truthX = [x1, x2, x3] basiliskV = [v_BN_NOutput[int(t1/timeStep), 1], v_BN_NOutput[int(t2/timeStep), 1], v_BN_NOutput[int(t3/timeStep), 1]] basiliskX = [r_BN_NOutput[int(t1/timeStep), 1], r_BN_NOutput[int(t2/timeStep), 1], r_BN_NOutput[int(t3/timeStep), 1]] plt.close('all') plt.figure() plt.clf() plt.plot(r_BN_NOutput[:,0]*1e-9, r_BN_NOutput[:,1],'-b',label = "Basilisk") plt.plot([t1, t2, t3], [x1, x2, x3],'ro',markersize = 6.5,label = "BOE") plt.xlabel('time (s)') plt.ylabel('X (m)') plt.legend(loc ='upper left',numpoints = 1) PlotName = "scPlusTranslationPositionBOE" PlotTitle = "Translation Position BOE" format = r"width=0.8\textwidth" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(v_BN_NOutput[:,0]*1e-9, v_BN_NOutput[:,1],'-b',label = "Basilisk") plt.plot([t1, t2, t3], [v1, v2, v3],'ro',markersize = 6.5,label = "BOE") plt.xlabel('time (s)') plt.ylabel('X velocity (m/s)') plt.legend(loc ='lower left',numpoints = 1) PlotName = "scPlusTranslationVelocityBOE" PlotTitle = "Translation Velocity BOE" format = r"width=0.8\textwidth" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) if show_plots: plt.show() plt.close('all') accuracy = 1e-10 for i in range(0,3): # check a vector values if abs((truthX[i] - basiliskX[i])/truthX[i]) > accuracy: testFailCount += 1 testMessages.append("FAILED: Spacecraft Translation BOE Integrated test failed pos unit test") for i in range(0,3): # check a vector values if abs((truthV[i] - basiliskV[i])/truthV[i]) > accuracy: testFailCount += 1 testMessages.append("FAILED: Spacecraft Translation BOE Integrated test failed velocity unit test") if testFailCount == 0: print("PASSED: " + " Spacecraft Translation BOE 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)]
[docs]def SCPointBVsPointC(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 scObject = spacecraft.Spacecraft() scObject.ModelTag = "spacecraftBody" 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(0.01) # 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, scObject) # Define location of force rFBc_B = numpy.array([0.3, -0.7, 0.4]) force_B = numpy.array([0.5, 0.6, -0.2]) torquePntC_B = numpy.cross(rFBc_B,force_B) # Add external force and torque extFTObject = extForceTorque.ExtForceTorque() extFTObject.ModelTag = "externalDisturbance" extFTObject.extTorquePntB_B = [[torquePntC_B[0]], [torquePntC_B[1]], [torquePntC_B[2]]] extFTObject.extForce_B = [[force_B[0]], [force_B[1]], [force_B[2]]] scObject.addDynamicEffector(extFTObject) unitTestSim.AddModelToTask(unitTaskName, extFTObject) dataLog = scObject.scStateOutMsg.recorder() unitTestSim.AddModelToTask(unitTaskName, dataLog) # Define initial conditions of the spacecraft scObject.hub.mHub = 100 scObject.hub.r_BcB_B = [[0.0], [0.0], [0.0]] scObject.hub.IHubPntBc_B = [[500, 0.0, 0.0], [0.0, 200, 0.0], [0.0, 0.0, 300]] scObject.hub.r_CN_NInit = [[0.0], [0.0], [0.0]] scObject.hub.v_CN_NInit = [[0.0], [0.0], [0.0]] scObject.hub.sigma_BNInit = [[0.0], [0.0], [0.0]] scObject.hub.omega_BN_BInit = [[0.5], [-0.4], [0.7]] unitTestSim.InitializeSimulation() stopTime = 10.0 unitTestSim.ConfigureStopTime(macros.sec2nano(stopTime)) unitTestSim.ExecuteSimulation() r_CN_NOutput1 = addTimeColumn(dataLog.times(), dataLog.r_CN_N) sigma_BNOutput1 = addTimeColumn(dataLog.times(), dataLog.sigma_BN) #################### scObject = spacecraft.Spacecraft() scObject.ModelTag = "spacecraftBody" 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(0.01) # 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, scObject) # Define location of force rBcB_B = numpy.array([0.4, 0.5, 0.2]) rFB_B = rBcB_B + rFBc_B torquePntB_B = numpy.cross(rFB_B,force_B) # Add external force and torque extFTObject = extForceTorque.ExtForceTorque() extFTObject.ModelTag = "externalDisturbance" extFTObject.extTorquePntB_B = [[torquePntB_B[0]], [torquePntB_B[1]], [torquePntB_B[2]]] extFTObject.extForce_B = [[force_B[0]], [force_B[1]], [force_B[2]]] scObject.addDynamicEffector(extFTObject) unitTestSim.AddModelToTask(unitTaskName, extFTObject) dataLog2 = scObject.scStateOutMsg.recorder() unitTestSim.AddModelToTask(unitTaskName, dataLog2) # Define initial conditions of the spacecraft scObject.hub.mHub = 100 scObject.hub.r_BcB_B = [[rBcB_B[0]], [rBcB_B[1]], [rBcB_B[2]]] scObject.hub.IHubPntBc_B = [[500, 0.0, 0.0], [0.0, 200, 0.0], [0.0, 0.0, 300]] scObject.hub.r_CN_NInit = [[0.0], [0.0], [0.0]] scObject.hub.v_CN_NInit = [[0.0], [0.0], [0.0]] scObject.hub.sigma_BNInit = [[0.0], [0.0], [0.0]] scObject.hub.omega_BN_BInit = [[0.5], [-0.4], [0.7]] unitTestSim.InitializeSimulation() stopTime = 10.0 unitTestSim.ConfigureStopTime(macros.sec2nano(stopTime)) unitTestSim.ExecuteSimulation() r_CN_NOutput2 = addTimeColumn(dataLog2.times(), dataLog2.r_CN_N) sigma_BNOutput2 = addTimeColumn(dataLog2.times(), dataLog2.sigma_BN) plt.figure() plt.clf() plt.plot(r_CN_NOutput1[:,0]*1e-9, r_CN_NOutput1[:,1], 'k', label = 'Torque About Point C', linewidth=3.0) plt.plot(r_CN_NOutput1[:,0]*1e-9,r_CN_NOutput1[:,2], 'k', r_CN_NOutput1[:,0]*1e-9, r_CN_NOutput1[:,3], 'k', linewidth=3.0) plt.plot(r_CN_NOutput2[:,0]*1e-9, r_CN_NOutput2[:,1], '--c', label = 'Torque About Point B') plt.plot(r_CN_NOutput2[:,0]*1e-9,r_CN_NOutput2[:,2], '--c', r_CN_NOutput2[:,0]*1e-9, r_CN_NOutput1[:,3], '--c') plt.xlabel('Time (s)') plt.ylabel('Inertial Position (m)') plt.legend(loc ='upper left', handlelength=3.5) PlotName = "scPlusPointBVsPointCTranslation" PlotTitle = "PointB Vs PointC Translation" format = r"width=0.8\textwidth" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) plt.figure() plt.clf() plt.plot(sigma_BNOutput1[:,0]*1e-9, sigma_BNOutput1[:,1], 'k', label = 'Torque About Point C', linewidth=3.0) plt.plot(sigma_BNOutput1[:,0]*1e-9, sigma_BNOutput1[:,2], 'k', sigma_BNOutput1[:,0]*1e-9, sigma_BNOutput1[:,3], 'k', linewidth=3.0) plt.plot(sigma_BNOutput2[:,0]*1e-9, sigma_BNOutput2[:,1], '--c', label = 'Torque About Point B') plt.plot(sigma_BNOutput2[:,0]*1e-9, sigma_BNOutput2[:,2], '--c', sigma_BNOutput2[:,0]*1e-9, sigma_BNOutput2[:,3], '--c') plt.xlabel('Time (s)') plt.ylabel('MRPs') plt.legend(loc ='upper right', handlelength=3.5) PlotName = "scPlusPointBVsPointCAttitude" PlotTitle = "PointB Vs PointC Attitude" format = r"width=0.8\textwidth" unitTestSupport.writeFigureLaTeX(PlotName, PlotTitle, plt, format, path) if show_plots: plt.show() plt.close('all') accuracy = 1e-8 if not unitTestSupport.isArrayEqualRelative(r_CN_NOutput1[-1,1:4],r_CN_NOutput2[-1,1:4],3,accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Point B Vs Point C test failed pos unit test") if not unitTestSupport.isArrayEqualRelative(sigma_BNOutput1[-1,1:4],sigma_BNOutput2[-1,1:4],3,accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Point B Vs Point C test failed attitude unit test") if testFailCount == 0: print("PASSED: " + " Spacecraft Point B Vs Point C 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)]
[docs]@pytest.mark.parametrize("accuracy", [1e-3]) def scOptionalRef(show_plots, accuracy): """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 scObject = spacecraft.Spacecraft() scObject.ModelTag = "spacecraftBody" 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 timeStep = 0.1 testProcessRate = macros.sec2nano(timeStep) # 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, scObject) dataLog = scObject.scStateOutMsg.recorder() unitTestSim.AddModelToTask(unitTaskName, dataLog) # add Earth gravFactory = simIncludeGravBody.gravBodyFactory() earth = gravFactory.createEarth() earth.isCentralBody = True # ensure this is the central gravitational body scObject.gravField.gravBodies = spacecraft.GravBodyVector(list(gravFactory.gravBodies.values())) # add gravity gradient effector ggEff = GravityGradientEffector.GravityGradientEffector() ggEff.ModelTag = scObject.ModelTag ggEff.addPlanetName(earth.planetName) scObject.addDynamicEffector(ggEff) unitTestSim.AddModelToTask(unitTaskName, ggEff) # Define initial conditions of the spacecraft scObject.hub.mHub = 100 scObject.hub.r_BcB_B = [[0.0], [0.0], [0.0]] scObject.hub.IHubPntBc_B = [[500, 0.0, 0.0], [0.0, 200, 0.0], [0.0, 0.0, 300]] scObject.hub.r_CN_NInit = [[7000000.0], [0.0], [0.0]] scObject.hub.v_CN_NInit = [[7000.0], [0.0], [0.0]] scObject.hub.sigma_BNInit = [[0.5], [0.4], [0.3]] scObject.hub.sigma_BNInit = [[0.], [0.], [1.0]] scObject.hub.omega_BN_BInit = [[0.5], [-0.4], [0.7]] # write attitude reference message attRef = messaging.AttRefMsgPayload() attRef.sigma_RN = [0.0, 0.0, 1.0] attRef.omega_RN_N = [0.0001, 0.0002, 0.0003] attRefMsg = messaging.AttRefMsg().write(attRef) scObject.attRefInMsg.subscribeTo(attRefMsg) # write translational reference message transRef = messaging.TransRefMsgPayload() transRef.r_RN_N = [1000000, 2000000, 3000000] transRef.v_RN_N = [2000, 3000, 4000] transRefMsg = messaging.TransRefMsg().write(transRef) scObject.transRefInMsg.subscribeTo(transRefMsg) unitTestSim.InitializeSimulation() stopTime = 0.2 unitTestSim.ConfigureStopTime(macros.sec2nano(stopTime)) unitTestSim.ExecuteSimulation() omegaOut = dataLog.omega_BN_B sigmaOut = dataLog.sigma_BN r_RN_Out = dataLog.r_BN_N v_RN_Out = dataLog.v_BN_N trueSigma = [attRef.sigma_RN]*3 trueOmega = [[-0.0001, -0.0002, 0.0003]]*3 truer_RN_N = [transRef.r_RN_N]*3 truev_RN_N = [transRef.v_RN_N]*3 testFailCount, testMessages = unitTestSupport.compareArray(trueSigma, sigmaOut, accuracy, "sigma_BN", testFailCount, testMessages) testFailCount, testMessages = unitTestSupport.compareArray(trueOmega, omegaOut, accuracy, "omega_BN_B", testFailCount, testMessages) testFailCount, testMessages = unitTestSupport.compareArray(truer_RN_N, r_RN_Out, accuracy, "r_RN_N", testFailCount, testMessages) testFailCount, testMessages = unitTestSupport.compareArray(truev_RN_N, v_RN_Out, accuracy, "v_RN_N", testFailCount, testMessages) if testFailCount == 0: print("PASSED: scPlus setting optional reference state input message") else: print("FAILED: scPlus setting optional reference state input message") assert testFailCount < 1, testMessages return [testFailCount, ''.join(testMessages)]
[docs]def scAccumDV(): """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 scObject = spacecraft.Spacecraft() scObject.ModelTag = "spacecraftBody" 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 timeStep = 0.1 testProcessRate = macros.sec2nano(timeStep) # 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, scObject) dataLog = scObject.scStateOutMsg.recorder() unitTestSim.AddModelToTask(unitTaskName, dataLog) # add Earth gravFactory = simIncludeGravBody.gravBodyFactory() earth = gravFactory.createEarth() earth.isCentralBody = True # ensure this is the central gravitational body scObject.gravField.gravBodies = spacecraft.GravBodyVector(list(gravFactory.gravBodies.values())) # Define initial conditions of the spacecraft scObject.hub.mHub = 100 scObject.hub.r_BcB_B = [[0.0], [100.0], [0.0]] scObject.hub.IHubPntBc_B = [[500, 0.0, 0.0], [0.0, 200, 0.0], [0.0, 0.0, 300]] scObject.hub.r_CN_NInit = [[-7000000.0], [0.0], [0.0]] scObject.hub.v_CN_NInit = [[0.0], [7000.0], [0.0]] scObject.hub.sigma_BNInit = [[0.0], [0.0], [0.0]] scObject.hub.omega_BN_BInit = [[0.0], [0.0], [numpy.pi/180]] unitTestSim.InitializeSimulation() stopTime = 0.5 unitTestSim.ConfigureStopTime(macros.sec2nano(stopTime)) unitTestSim.ExecuteSimulation() dataAccumDV_CN_B = dataLog.TotalAccumDVBdy dataAccumDV_BN_B = dataLog.TotalAccumDV_BN_B dataAccumDV_CN_N = dataLog.TotalAccumDV_CN_N accuracy = 1e-10 truth_dataAccumDV_CN_B = [0.0, 0.0, 0.0] truth_dataAccumDV_CN_N = [0.0, 0.0, 0.0] v_r = numpy.cross(numpy.array(scObject.hub.omega_BN_BInit).T, -numpy.array(scObject.hub.r_BcB_B).T)[0] truth_dataAccumDV_BN_B = numpy.zeros(3) for i in range(len(dataLog.times())-1): if not unitTestSupport.isArrayEqual(dataAccumDV_CN_B[i+1],truth_dataAccumDV_CN_B,3,accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Point C Accumulated DV test failed pos unit test") truth_dataAccumDV_BN_B += numpy.matmul(RigidBodyKinematics.MRP2C(dataLog.sigma_BN[i+1]), numpy.matmul(RigidBodyKinematics.MRP2C(dataLog.sigma_BN[i+1]).T,v_r) - numpy.matmul(RigidBodyKinematics.MRP2C(dataLog.sigma_BN[i]).T,v_r)) if not unitTestSupport.isArrayEqual(dataAccumDV_BN_B[i+1],truth_dataAccumDV_BN_B,3,accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Point B Accumulated DV test failed pos unit test") if not unitTestSupport.isArrayEqual(dataAccumDV_CN_N[i+1],truth_dataAccumDV_CN_N,3,accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Point C Accumulated DV in inertial frame test failed pos unit test") if testFailCount == 0: print("PASSED: Spacecraft Accumulated DV tests with offset CoM") return [testFailCount, ''.join(testMessages)]
[docs]def scAccumDVExtForce(): """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 scObject = spacecraft.Spacecraft() scObject.ModelTag = "spacecraftBody" 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 timeStep = 0.1 testProcessRate = macros.sec2nano(timeStep) # 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, scObject) # Add external force and torque extFTObject = extForceTorque.ExtForceTorque() extFTObject.ModelTag = "externalDisturbance" extFTObject.extTorquePntB_B = [[0], [0], [0]] extForce = numpy.array([random() for _ in range(3)]) extFTObject.extForce_B = [[item] for item in extForce] scObject.addDynamicEffector(extFTObject) unitTestSim.AddModelToTask(unitTaskName, extFTObject) # Define initial conditions of the spacecraft scObject.hub.mHub = 100 dataLog = scObject.scStateOutMsg.recorder() unitTestSim.AddModelToTask(unitTaskName, dataLog) unitTestSim.InitializeSimulation() stopTime = 0.5 unitTestSim.ConfigureStopTime(macros.sec2nano(stopTime)) unitTestSim.ExecuteSimulation() dataAccumDV_CN_N = dataLog.TotalAccumDV_CN_N timeArraySec = dataLog.times() * macros.NANO2SEC accuracy = 1e-10 for i in range(len(dataLog.times())): truth_dataAccumDV_CN_N = extForce * timeArraySec[i] / scObject.hub.mHub if not unitTestSupport.isArrayEqual(dataAccumDV_CN_N[i], truth_dataAccumDV_CN_N, 3, accuracy): testFailCount += 1 testMessages.append("FAILED: Spacecraft Point C Accumulated DV with external force test failed unit test") if testFailCount == 0: print("PASSED: Spacecraft Accumulated DV tests with offset CoM") return [testFailCount, ''.join(testMessages)]
if __name__ == "__main__": # scAttRef(True, 1e-3) # SCTranslation(True) # SCTransAndRotation(True) # SCRotation(True) # SCTransBOE(True) # SCPointBVsPointC(True) # scOptionalRef(True, 0.001) # scAccumDV() scAccumDVExtForce()