Source code for test_eclipse


# ISC License
#
# Copyright (c) 2016, Autonomous Vehicle Systems Lab, University of Colorado at Boulder
#
# Permission to use, copy, modify, and/or distribute this software for any
# purpose with or without fee is hereby granted, provided that the above
# copyright notice and this permission notice appear in all copies.
#
# THE SOFTWARE IS PROVIDED "AS IS" AND THE AUTHOR DISCLAIMS ALL WARRANTIES
# WITH REGARD TO THIS SOFTWARE INCLUDING ALL IMPLIED WARRANTIES OF
# MERCHANTABILITY AND FITNESS. IN NO EVENT SHALL THE AUTHOR BE LIABLE FOR
# ANY SPECIAL, DIRECT, INDIRECT, OR CONSEQUENTIAL DAMAGES OR ANY DAMAGES
# WHATSOEVER RESULTING FROM LOSS OF USE, DATA OR PROFITS, WHETHER IN AN
# ACTION OF CONTRACT, NEGLIGENCE OR OTHER TORTIOUS ACTION, ARISING OUT OF
# OR IN CONNECTION WITH THE USE OR PERFORMANCE OF THIS SOFTWARE.

#
# Eclipse Condition Unit Test
#
# Purpose:  Test the proper function of the Eclipse environment module.
#           This is done by comparing computed expected shadow factors in
#           particular eclipse conditions to what is simulated
# Author:   Patrick Kenneally
# Creation Date:  May. 31, 2017
#

import os
import numpy as np

import pytest
from Basilisk import __path__
from Basilisk.simulation import eclipse
from Basilisk.simulation import spacecraft
from Basilisk.simulation import planetEphemeris
from Basilisk.utilities import SimulationBaseClass
from Basilisk.utilities import macros
from Basilisk.utilities import orbitalMotion
from Basilisk.utilities import simIncludeGravBody
from Basilisk.utilities import unitTestSupport
from Basilisk.architecture import messaging

bskPath = __path__[0]

path = os.path.dirname(os.path.abspath(__file__))

# uncomment this line if this test has an expected failure, adjust message as needed
# @pytest.mark.xfail(True)
[docs]@pytest.mark.parametrize("eclipseCondition, planet", [ ("partial", "earth"), ("full", "earth"), ("none", "earth"), ("annular", "earth"), ("partial", "mars"), ("full", "mars"), ("none", "mars"), ("annular", "mars")]) def test_unitEclipse(show_plots, eclipseCondition, planet): """ **Test Description and Success Criteria** The unit test validates the internal aspects of the Basilisk eclipse module by comparing simulated output with \ expected output. It validates the computation of a shadow factor for total eclipse, partial eclipse,annular eclipse, \ and no eclipse scenarios. The test is designed to analyze one type at a time for both Earth and Mars and is then \ repeated for all three. Earth is set as the zero base for all eclipse types to test it as the occulting body. For full, partial, and \ no eclipse cases, orbital elements describing the spacecraft states are then converted to Cartesian vectors. \ These orbital elements vary for each eclipse type since the Sun and planet states are fixed. The conversion is \ made using the orbitalMotion elem2rv function, where the inputs are six orbital elements (a, e, i, Omega, omega, f) \ and the outputs are Cartesian position and velocity vectors. For the annular eclipse case, the conversion is \ avoided and a Cartesian position vector is initially provided instead. The vectors are then passed into \ spacecraft and, subsequently, the eclipse module through the Basilisk messaging system. Testing the no eclipse case with Mars as the occulting body is the same as the Earth no eclipse test, except \ Mars is set as the zero base. The Mars full, partial, and annular eclipse cases, however, are like the Earth \ annular case where Cartesian vectors are, instead, the initial inputs. Since the test is performed as a single \ step process, the velocity is not necessarily needed as an input, so only a position vector is provided \ for these cases. The shadow factor obtained through the module is compared to the expected result, which is either trivial or \ calculated, depending on the eclipse type. Full eclipse and no eclipse shadow factors are compared without the \ need for computation, since they are just 0.0 and 1.0, respectively. The partial and annular eclipse shadow \ factors, however, vary between 0.0 and 1.0, based on the cone dimensions, and are calculated using \ MATLAB and Spice data. **Test Parameters:** - ``eclipseCondition``: [string] defines if the eclipse is partial, full, none or annular - ``planet``: [string] defines which planet to use. Options include "earth" and "mars" **Description of Variables Being Tested** In each test scenario the shadow eclipse variable ``shadowFactor`` is pulled from the log data and compared to expected truth values. """ [testResults, testMessage] = unitEclipse(show_plots, eclipseCondition, planet) assert testResults < 1, testMessage
[docs]def test_unitEclipseCustom(show_plots): """ **Test Description and Success Criteria** The unit test validates the internal aspects of the Basilisk eclipse module by comparing simulated output with \ expected output. It validates the computation of a shadow factor for total eclipse using a custom gravity body. This unit test sets up a custom gravity body, the asteroid Bennu, using the planetEphemeris module (i.e. Spice \ is not used for this test.) An empty spice planet message is created for the sun. The spacecraft is set 500 m \ on the side of the asteroid opposite of the sun. The shadow factor obtained through the module is compared to the expected result, which is trivial to compute. **Description of Variables Being Tested** In this test scenario the shadow eclipse variable ``shadowFactor`` is pulled from the log data and compared to the expected truth value. """ [testResults, testMessage] = unitEclipseCustom(show_plots) assert testResults < 1, testMessage
def unitEclipse(show_plots, eclipseCondition, planet): __tracebackhide__ = True testFailCount = 0 testMessages = [] testTaskName = "unitTestTask" testProcessName = "unitTestProcess" testTaskRate = macros.sec2nano(1) # Create a simulation container unitTestSim = SimulationBaseClass.SimBaseClass() testProc = unitTestSim.CreateNewProcess(testProcessName) testProc.addTask(unitTestSim.CreateNewTask(testTaskName, testTaskRate)) # Set up first spacecraft scObject_0 = spacecraft.Spacecraft() scObject_0.ModelTag = "spacecraft" unitTestSim.AddModelToTask(testTaskName, scObject_0) # setup Gravity Bodies gravFactory = simIncludeGravBody.gravBodyFactory() earth = gravFactory.createEarth() mars = gravFactory.createMarsBarycenter() if planet == "earth": earth.isCentralBody = True elif planet == "mars": mars.isCentralBody = True scObject_0.gravField.gravBodies = spacecraft.GravBodyVector(list(gravFactory.gravBodies.values())) # setup Spice interface for some solar system bodies timeInitString = '2021 MAY 04 07:47:48.965 (UTC)' gravFactory.createSpiceInterface(bskPath + '/supportData/EphemerisData/' , timeInitString # earth and mars must come first as with gravBodies , spicePlanetNames=["earth", "mars barycenter", "sun", "venus"] ) if planet == "earth": if eclipseCondition == "full": gravFactory.spiceObject.zeroBase = "earth" # set up spacecraft 0 position and velocity for full eclipse oe = orbitalMotion.ClassicElements() r_0 = (500 + orbitalMotion.REQ_EARTH) # km oe.a = r_0 oe.e = 0.00001 oe.i = 5.0 * macros.D2R oe.Omega = 48.2 * macros.D2R oe.omega = 0 * macros.D2R oe.f = 173 * macros.D2R r_N_0, v_N_0 = orbitalMotion.elem2rv(orbitalMotion.MU_EARTH, oe) scObject_0.hub.r_CN_NInit = r_N_0 * 1000 # convert to meters scObject_0.hub.v_CN_NInit = v_N_0 * 1000 # convert to meters elif eclipseCondition == "partial": gravFactory.spiceObject.zeroBase = "earth" # set up spacecraft 0 position and velocity for full eclipse oe = orbitalMotion.ClassicElements() r_0 = (500 + orbitalMotion.REQ_EARTH) # km oe.a = r_0 oe.e = 0.00001 oe.i = 5.0 * macros.D2R oe.Omega = 48.2 * macros.D2R oe.omega = 0 * macros.D2R oe.f = 107.5 * macros.D2R r_N_0, v_N_0 = orbitalMotion.elem2rv(orbitalMotion.MU_EARTH, oe) scObject_0.hub.r_CN_NInit = r_N_0 * 1000 # convert to meters scObject_0.hub.v_CN_NInit = v_N_0 * 1000 # convert to meters elif eclipseCondition == "none": oe = orbitalMotion.ClassicElements() r_0 = 9959991.68982 # km oe.a = r_0 oe.e = 0.00001 oe.i = 5.0 * macros.D2R oe.Omega = 48.2 * macros.D2R oe.omega = 0 * macros.D2R oe.f = 107.5 * macros.D2R r_N_0, v_N_0 = orbitalMotion.elem2rv(orbitalMotion.MU_EARTH, oe) scObject_0.hub.r_CN_NInit = r_N_0 * 1000 # convert to meters scObject_0.hub.v_CN_NInit = v_N_0 * 1000 # convert to meters elif eclipseCondition == "annular": gravFactory.spiceObject.zeroBase = "earth" scObject_0.hub.r_CN_NInit = [-326716535628.942, -287302983139.247, -124542549301.050] elif planet == "mars": if eclipseCondition == "full": gravFactory.spiceObject.zeroBase = "mars barycenter" scObject_0.hub.r_CN_NInit = [-2930233.55919119, 2567609.100747609, 41384.23366372246] # meters elif eclipseCondition == "partial": gravFactory.spiceObject.zeroBase = "mars barycenter" scObject_0.hub.r_CN_NInit = [-6050166.454829555, 2813822.447404055, 571725.5651779658] # meters elif eclipseCondition == "none": oe = orbitalMotion.ClassicElements() r_0 = 9959991.68982 # km oe.a = r_0 oe.e = 0.00001 oe.i = 5.0 * macros.D2R oe.Omega = 48.2 * macros.D2R oe.omega = 0 * macros.D2R oe.f = 107.5 * macros.D2R r_N_0, v_N_0 = orbitalMotion.elem2rv(orbitalMotion.MU_MARS, oe) scObject_0.hub.r_CN_NInit = r_N_0 * 1000 # convert to meters scObject_0.hub.v_CN_NInit = v_N_0 * 1000 # convert to meters elif eclipseCondition == "annular": gravFactory.spiceObject.zeroBase = "mars barycenter" scObject_0.hub.r_CN_NInit = [-427424601171.464, 541312532797.400, 259820030623.064] # meters unitTestSim.AddModelToTask(testTaskName, gravFactory.spiceObject, -1) eclipseObject = eclipse.Eclipse() eclipseObject.addSpacecraftToModel(scObject_0.scStateOutMsg) eclipseObject.addPlanetToModel(gravFactory.spiceObject.planetStateOutMsgs[3]) # venus eclipseObject.addPlanetToModel(gravFactory.spiceObject.planetStateOutMsgs[1]) # mars eclipseObject.addPlanetToModel(gravFactory.spiceObject.planetStateOutMsgs[0]) # earth eclipseObject.sunInMsg.subscribeTo(gravFactory.spiceObject.planetStateOutMsgs[2]) # sun unitTestSim.AddModelToTask(testTaskName, eclipseObject) dataLog = eclipseObject.eclipseOutMsgs[0].recorder() unitTestSim.AddModelToTask(testTaskName, dataLog) unitTestSim.InitializeSimulation() # Execute the simulation for one time step unitTestSim.TotalSim.SingleStepProcesses() eclipseData_0 = dataLog.shadowFactor # Obtain body position vectors to check with MATLAB errTol = 1E-12 if planet == "earth": if eclipseCondition == "partial": truthShadowFactor = 0.62310760206735027 if not unitTestSupport.isDoubleEqual(eclipseData_0[-1], truthShadowFactor, errTol): testFailCount += 1 testMessages.append("Shadow Factor failed for Earth partial eclipse condition") elif eclipseCondition == "full": truthShadowFactor = 0.0 if not unitTestSupport.isDoubleEqual(eclipseData_0[-1], truthShadowFactor, errTol): testFailCount += 1 testMessages.append("Shadow Factor failed for Earth full eclipse condition") elif eclipseCondition == "none": truthShadowFactor = 1.0 if not unitTestSupport.isDoubleEqual(eclipseData_0[-1], truthShadowFactor, errTol): testFailCount += 1 testMessages.append("Shadow Factor failed for Earth none eclipse condition") elif eclipseCondition == "annular": truthShadowFactor = 1.497253388113018e-04 if not unitTestSupport.isDoubleEqual(eclipseData_0[-1], truthShadowFactor, errTol): testFailCount += 1 testMessages.append("Shadow Factor failed for Earth annular eclipse condition") elif planet == "mars": if eclipseCondition == "partial": truthShadowFactor = 0.18745025055615416 if not unitTestSupport.isDoubleEqual(eclipseData_0[-1], truthShadowFactor, errTol): testFailCount += 1 testMessages.append("Shadow Factor failed for Mars partial eclipse condition") elif eclipseCondition == "full": truthShadowFactor = 0.0 if not unitTestSupport.isDoubleEqual(eclipseData_0[-1], truthShadowFactor, errTol): testFailCount += 1 testMessages.append("Shadow Factor failed for Mars full eclipse condition") elif eclipseCondition == "none": truthShadowFactor = 1.0 if not unitTestSupport.isDoubleEqual(eclipseData_0[-1], truthShadowFactor, errTol): testFailCount += 1 testMessages.append("Shadow Factor failed for Mars none eclipse condition") elif eclipseCondition == "annular": truthShadowFactor = 4.245137380531894e-05 if not unitTestSupport.isDoubleEqual(eclipseData_0[-1], truthShadowFactor, errTol): testFailCount += 1 testMessages.append("Shadow Factor failed for Mars annular eclipse condition") if testFailCount == 0: print("PASSED: " + planet + "-" + eclipseCondition) # return fail count and join into a single string all messages in the list # testMessage else: print(testMessages) print('The error tolerance for all tests is ' + str(errTol)) # # unload the SPICE libraries that were loaded by the spiceObject earlier # gravFactory.unloadSpiceKernels() return [testFailCount, ''.join(testMessages)] def unitEclipseCustom(show_plots): __tracebackhide__ = True testFailCount = 0 testMessages = [] testTaskName = "unitTestTask" testProcessName = "unitTestProcess" testTaskRate = macros.sec2nano(1) # Create a simulation container unitTestSim = SimulationBaseClass.SimBaseClass() testProc = unitTestSim.CreateNewProcess(testProcessName) testProc.addTask(unitTestSim.CreateNewTask(testTaskName, testTaskRate)) # Set up first spacecraft scObject_0 = spacecraft.Spacecraft() scObject_0.ModelTag = "spacecraft" unitTestSim.AddModelToTask(testTaskName, scObject_0) # setup Gravity Bodies gravFactory = simIncludeGravBody.gravBodyFactory() mu_bennu = 4.892 custom = gravFactory.createCustomGravObject("custom", mu_bennu) # creates a custom grav object (bennu) scObject_0.gravField.gravBodies = spacecraft.GravBodyVector(list(gravFactory.gravBodies.values())) # Create the ephemeris data for the bodies # setup celestial object ephemeris module gravBodyEphem = planetEphemeris.PlanetEphemeris() gravBodyEphem.ModelTag = 'planetEphemeris' gravBodyEphem.setPlanetNames(planetEphemeris.StringVector(["custom"])) # Specify bennu orbit oeAsteroid = planetEphemeris.ClassicElementsMsgPayload() oeAsteroid.a = 1.1259 * orbitalMotion.AU * 1000. # m oeAsteroid.e = 0.20373 oeAsteroid.i = 6.0343 * macros.D2R oeAsteroid.Omega = 2.01820 * macros.D2R oeAsteroid.omega = 66.304 * macros.D2R oeAsteroid.f = 120.0 * macros.D2R gravBodyEphem.planetElements = planetEphemeris.classicElementVector([oeAsteroid]) custom.planetBodyInMsg.subscribeTo(gravBodyEphem.planetOutMsgs[0]) # Create an empty sun spice object sunPlanetStateMsgData = messaging.SpicePlanetStateMsgPayload() sunPlanetStateMsg = messaging.SpicePlanetStateMsg() sunPlanetStateMsg.write(sunPlanetStateMsgData) r_ast_N = np.array([-177862743954.6422, -25907896415.157013, -2074871174.236055]) r_sc_N = r_ast_N + 500 * r_ast_N / np.linalg.norm(r_ast_N) scObject_0.hub.r_CN_NInit = r_sc_N unitTestSim.AddModelToTask(testTaskName, gravBodyEphem, -1) eclipseObject = eclipse.Eclipse() eclipseObject.addSpacecraftToModel(scObject_0.scStateOutMsg) eclipseObject.addPlanetToModel(gravBodyEphem.planetOutMsgs[0]) # custom eclipseObject.sunInMsg.subscribeTo(sunPlanetStateMsg) # sun eclipseObject.rEqCustom = 282. # m unitTestSim.AddModelToTask(testTaskName, eclipseObject) dataLog = eclipseObject.eclipseOutMsgs[0].recorder() unitTestSim.AddModelToTask(testTaskName, dataLog) unitTestSim.InitializeSimulation() # Execute the simulation for one time step unitTestSim.TotalSim.SingleStepProcesses() eclipseData_0 = dataLog.shadowFactor # Obtain body position vectors to check with MATLAB errTol = 1E-12 truthShadowFactor = 0.0 if not unitTestSupport.isDoubleEqual(eclipseData_0[-1], truthShadowFactor, errTol): testFailCount += 1 testMessages.append("Shadow Factor failed for custom full eclipse condition") if testFailCount == 0: print("PASSED: custom-full") # return fail count and join into a single string all messages in the list # testMessage else: print(testMessages) print('The error tolerance for all tests is ' + str(errTol)) return [testFailCount, ''.join(testMessages)] if __name__ == "__main__": unitEclipse(False, "annular", "mars") unitEclipseCustom(False)