# ISC License
#
# Copyright (c) 2024, 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.
#
# Unit Test Script
# Module Name: spinningBodiesNDOF
# Author: João Vaz Carneiro
# Creation Date: April 2, 2024
#
import inspect
import os
import pytest
import numpy as np
import matplotlib.pyplot as plt
filename = inspect.getframeinfo(inspect.currentframe()).filename
path = os.path.dirname(os.path.abspath(filename))
splitPath = path.split('simulation')
from Basilisk.utilities import SimulationBaseClass, unitTestSupport, macros
from Basilisk.simulation import spacecraft, spinningBodyNDOFStateEffector, gravityEffector
from Basilisk.architecture import messaging
# 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", ["spinningBodyNoInput"
, "spinningBodyLockAxis"
, "spinningBodyCommandedTorque"])
def test_spinningBody(show_plots, function):
r"""
**Validation Test Description**
This unit test sets up a spacecraft with a four single-axis rotating rigid bodies attached to a rigid hub. The spinning
body's center of mass is off-center from the spinning axis and the position of the axis is arbitrary. The scenario
includes gravity acting on both the spacecraft and the effector.
**Description of Variables Being Tested**
In this file we are checking the principles of conservation of energy and angular momentum. Both the orbital and
rotational energy and angular momentum must be maintained when conservative forces like gravity are present.
Therefore, the values of the variables
- ``finalOrbAngMom``
- ``finalOrbEnergy``
- ``finalRotAngMom``
- ``finalRotEnergy``
against their initial values.
"""
eval(function + '(show_plots)')
def spinningBodyNoInput(show_plots):
__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(0.0001) # update process rate update time
testProc = unitTestSim.CreateNewProcess(unitProcessName)
testProc.addTask(unitTestSim.CreateNewTask(unitTaskName, testProcessRate))
# Create two hinged rigid bodies
spinningBodyEffector = spinningBodyNDOFStateEffector.SpinningBodyNDOFStateEffector()
spinningBodyEffector.ModelTag = "spinningBodyEffector"
# Define properties of spinning bodies
spinningBody1 = spinningBodyNDOFStateEffector.SpinningBody()
spinningBody1.setMass(np.random.uniform(5.0, 50.0))
spinningBody1.setISPntSc_S([[np.random.uniform(5.0, 100.0), 0.0, 0.0],
[0.0, np.random.uniform(5.0, 100.0), 0.0],
[0.0, 0.0, np.random.uniform(5.0, 100.0)]])
spinningBody1.setDCM_S0P([[-1.0, 0.0, 0.0], [0.0, -1.0, 0.0], [0.0, 0.0, 1.0]])
spinningBody1.setR_ScS_S([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody1.setR_SP_P([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody1.setSHat_S([[0], [0], [1]])
spinningBody1.setThetaInit(np.random.uniform(-10.0, 10.0) * macros.D2R)
spinningBody1.setThetaDotInit(0.0 * macros.D2R)
spinningBody1.setK(np.random.random())
spinningBodyEffector.addSpinningBody(spinningBody1)
spinningBody2 = spinningBodyNDOFStateEffector.SpinningBody()
spinningBody2.setMass(np.random.uniform(5.0, 50.0))
spinningBody2.setISPntSc_S([[np.random.uniform(5.0, 100.0), 0.0, 0.0],
[0.0, np.random.uniform(5.0, 100.0), 0.0],
[0.0, 0.0, np.random.uniform(5.0, 100.0)]])
spinningBody2.setDCM_S0P([[0.0, -1.0, 0.0], [0.0, .0, -1.0], [1.0, 0.0, 0.0]])
spinningBody2.setR_ScS_S([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody2.setR_SP_P([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody2.setSHat_S([[0], [-1], [0]])
spinningBody2.setThetaInit(np.random.uniform(-10.0, 10.0) * macros.D2R)
spinningBody2.setThetaDotInit(0.0 * macros.D2R)
spinningBody2.setK(np.random.random())
spinningBodyEffector.addSpinningBody(spinningBody2)
spinningBody3 = spinningBodyNDOFStateEffector.SpinningBody()
spinningBody3.setMass(np.random.uniform(5.0, 50.0))
spinningBody3.setISPntSc_S([[np.random.uniform(5.0, 100.0), 0.0, 0.0],
[0.0, np.random.uniform(5.0, 100.0), 0.0],
[0.0, 0.0, np.random.uniform(5.0, 100.0)]])
spinningBody3.setDCM_S0P([[1.0, 0.0, 0.0], [0.0, -1.0, 0.0], [0.0, 0.0, -1.0]])
spinningBody3.setR_ScS_S([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody3.setR_SP_P([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody3.setSHat_S([[np.sqrt(1/2)], [np.sqrt(1/2)], [0]])
spinningBody3.setThetaInit(np.random.uniform(-10.0, 10.0) * macros.D2R)
spinningBody3.setThetaDotInit(0.0 * macros.D2R)
spinningBody3.setK(np.random.random())
spinningBodyEffector.addSpinningBody(spinningBody3)
spinningBody4 = spinningBodyNDOFStateEffector.SpinningBody()
spinningBody4.setMass(np.random.uniform(5.0, 50.0))
spinningBody4.setISPntSc_S([[np.random.uniform(5.0, 100.0), 0.0, 0.0],
[0.0, np.random.uniform(5.0, 100.0), 0.0],
[0.0, 0.0, np.random.uniform(5.0, 100.0)]])
spinningBody4.setDCM_S0P([[0.0, 1.0, 0.0], [0.0, .0, 1.0], [1.0, 0.0, 0.0]])
spinningBody4.setR_ScS_S([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody4.setR_SP_P([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody4.setSHat_S([[np.sqrt(1/2)], [-np.sqrt(1/2)], [0]])
spinningBody4.setThetaInit(np.random.uniform(-10.0, 10.0) * macros.D2R)
spinningBody4.setThetaDotInit(0.0 * macros.D2R)
spinningBody4.setK(np.random.random())
spinningBodyEffector.addSpinningBody(spinningBody4)
# Add spinning body to spacecraft
scObject.addStateEffector(spinningBodyEffector)
# Define mass properties of the rigid hub of the spacecraft
scObject.hub.mHub = 750.0
scObject.hub.r_BcB_B = [[0.0], [0.0], [1.0]]
scObject.hub.IHubPntBc_B = [[900.0, 0.0, 0.0], [0.0, 800.0, 0.0], [0.0, 0.0, 600.0]]
# Set the initial values for the states
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 = [[0.1], [-0.1], [0.1]]
# Add test module to runtime call list
unitTestSim.AddModelToTask(unitTaskName, spinningBodyEffector)
unitTestSim.AddModelToTask(unitTaskName, scObject)
# Add Earth gravity to the simulation
earthGravBody = gravityEffector.GravBodyData()
earthGravBody.planetName = "earth_planet_data"
earthGravBody.mu = 0.3986004415E+15 # meters!
earthGravBody.isCentralBody = True
scObject.gravField.gravBodies = spacecraft.GravBodyVector([earthGravBody])
# Log the spacecraft state message
datLog = scObject.scStateOutMsg.recorder()
unitTestSim.AddModelToTask(unitTaskName, datLog)
# Add energy and momentum variables to log
scObjectLog = scObject.logger(["totRotEnergy", "totOrbEnergy", "totOrbAngMomPntN_N", "totRotAngMomPntC_N"])
unitTestSim.AddModelToTask(unitTaskName, scObjectLog)
# Add states to log
theta1Data = spinningBodyEffector.spinningBodyOutMsgs[0].recorder()
theta2Data = spinningBodyEffector.spinningBodyOutMsgs[1].recorder()
theta3Data = spinningBodyEffector.spinningBodyOutMsgs[2].recorder()
theta4Data = spinningBodyEffector.spinningBodyOutMsgs[3].recorder()
unitTestSim.AddModelToTask(unitTaskName, theta1Data)
unitTestSim.AddModelToTask(unitTaskName, theta2Data)
unitTestSim.AddModelToTask(unitTaskName, theta3Data)
unitTestSim.AddModelToTask(unitTaskName, theta4Data)
# Initialize the simulation
unitTestSim.InitializeSimulation()
# Setup and run the simulation
stopTime = 10000 * testProcessRate
unitTestSim.ConfigureStopTime(stopTime)
unitTestSim.ExecuteSimulation()
# Extract the logged variables
orbEnergy = scObjectLog.totOrbEnergy
orbAngMom_N = scObjectLog.totOrbAngMomPntN_N
rotAngMom_N = scObjectLog.totRotAngMomPntC_N
rotEnergy = scObjectLog.totRotEnergy
theta1 = theta1Data.theta
theta1Dot = theta1Data.thetaDot
theta2 = theta2Data.theta
theta2Dot = theta2Data.thetaDot
theta3 = theta3Data.theta
theta3Dot = theta3Data.thetaDot
theta4 = theta4Data.theta
theta4Dot = theta4Data.thetaDot
# Setup the conservation quantities
timeSec = scObjectLog.times() * 1e-9
initialOrbAngMom_N = [orbAngMom_N[0, 0], orbAngMom_N[0, 1], orbAngMom_N[0, 2]]
finalOrbAngMom = orbAngMom_N[-1]
initialRotAngMom_N = [rotAngMom_N[0, 0], rotAngMom_N[0, 1], rotAngMom_N[0, 2]]
finalRotAngMom = rotAngMom_N[-1]
initialOrbEnergy = orbEnergy[0]
finalOrbEnergy = orbEnergy[-1]
initialRotEnergy = rotEnergy[0]
finalRotEnergy = rotEnergy[-1]
# Plotting
plt.close("all")
plt.figure()
ax = plt.axes()
plt.plot(timeSec, (orbAngMom_N[:, 0] - initialOrbAngMom_N[0]) / initialOrbAngMom_N[0],
timeSec, (orbAngMom_N[:, 1] - initialOrbAngMom_N[1]) / initialOrbAngMom_N[1],
timeSec, (orbAngMom_N[:, 2] - initialOrbAngMom_N[2]) / initialOrbAngMom_N[2])
plt.xlabel('time (s)', fontsize='18')
plt.ylabel('Relative Difference', fontsize='18')
plt.title('Orbital Angular Momentum', fontsize='22')
plt.xticks(fontsize=14)
plt.yticks(fontsize=14)
ax.yaxis.offsetText.set_fontsize(14)
plt.figure()
ax = plt.axes()
plt.plot(timeSec, (orbEnergy - initialOrbEnergy) / initialOrbEnergy)
plt.xlabel('time (s)', fontsize='18')
plt.ylabel('Relative Difference', fontsize='18')
plt.title('Orbital Energy', fontsize='22')
plt.xticks(fontsize=14)
plt.yticks(fontsize=14)
ax.yaxis.offsetText.set_fontsize(14)
plt.figure()
ax = plt.axes()
plt.plot(timeSec, (rotAngMom_N[:, 0] - initialRotAngMom_N[0]) / initialRotAngMom_N[0],
timeSec, (rotAngMom_N[:, 1] - initialRotAngMom_N[1]) / initialRotAngMom_N[1],
timeSec, (rotAngMom_N[:, 2] - initialRotAngMom_N[2]) / initialRotAngMom_N[2])
plt.xlabel('time (s)', fontsize='18')
plt.ylabel('Relative Difference', fontsize='18')
plt.title('Rotational Angular Momentum', fontsize='22')
plt.xticks(fontsize=14)
plt.yticks(fontsize=14)
ax.yaxis.offsetText.set_fontsize(14)
plt.figure()
ax = plt.axes()
plt.plot(timeSec, (rotEnergy - initialRotEnergy) / initialRotEnergy)
plt.xlabel('time (s)', fontsize='18')
plt.ylabel('Relative Difference', fontsize='18')
plt.title('Rotational Energy', fontsize='22')
plt.xticks(fontsize=14)
plt.yticks(fontsize=14)
ax.yaxis.offsetText.set_fontsize(14)
plt.figure()
plt.clf()
plt.plot(timeSec, theta1, label=r'$\theta_1$')
plt.plot(timeSec, theta2, label=r'$\theta_2$')
plt.plot(timeSec, theta3, label=r'$\theta_3$')
plt.plot(timeSec, theta4, label=r'$\theta_4$')
plt.legend(loc='best')
plt.xlabel('time (s)')
plt.ylabel('Angle')
plt.figure()
plt.clf()
plt.plot(timeSec, theta1Dot, label=r'$\dot{\theta}_1$')
plt.plot(timeSec, theta2Dot, label=r'$\dot{\theta}_2$')
plt.plot(timeSec, theta3Dot, label=r'$\dot{\theta}_3$')
plt.plot(timeSec, theta4Dot, label=r'$\dot{\theta}_4$')
plt.legend(loc='best')
plt.xlabel('time (s)')
plt.ylabel('Angle Rate')
if show_plots:
plt.show()
plt.close("all")
# Testing setup
accuracy = 1e-12
np.testing.assert_allclose(finalOrbEnergy, initialOrbEnergy, rtol=accuracy)
np.testing.assert_allclose(finalRotEnergy, initialRotEnergy, rtol=accuracy)
for i in range(3):
np.testing.assert_allclose(finalOrbAngMom, initialOrbAngMom_N, rtol=accuracy)
np.testing.assert_allclose(finalRotAngMom, initialRotAngMom_N, rtol=accuracy)
def spinningBodyLockAxis(show_plots):
__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(0.0001) # update process rate update time
testProc = unitTestSim.CreateNewProcess(unitProcessName)
testProc.addTask(unitTestSim.CreateNewTask(unitTaskName, testProcessRate))
# Create two hinged rigid bodies
spinningBodyEffector = spinningBodyNDOFStateEffector.SpinningBodyNDOFStateEffector()
spinningBodyEffector.ModelTag = "spinningBodyEffector"
# Define properties of spinning bodies
spinningBody1 = spinningBodyNDOFStateEffector.SpinningBody()
spinningBody1.setMass(np.random.uniform(5.0, 50.0))
spinningBody1.setISPntSc_S([[np.random.uniform(5.0, 100.0), 0.0, 0.0],
[0.0, np.random.uniform(5.0, 100.0), 0.0],
[0.0, 0.0, np.random.uniform(5.0, 100.0)]])
spinningBody1.setDCM_S0P([[-1.0, 0.0, 0.0], [0.0, -1.0, 0.0], [0.0, 0.0, 1.0]])
spinningBody1.setR_ScS_S([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody1.setR_SP_P([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody1.setSHat_S([[0], [0], [1]])
spinningBody1.setThetaInit(np.random.uniform(-10.0, 10.0) * macros.D2R)
spinningBody1.setThetaDotInit(np.random.uniform(-1.0, 1.0) * macros.D2R)
spinningBody1.setK(np.random.random())
spinningBodyEffector.addSpinningBody(spinningBody1)
spinningBody2 = spinningBodyNDOFStateEffector.SpinningBody()
spinningBody2.setMass(np.random.uniform(5.0, 50.0))
spinningBody2.setISPntSc_S([[np.random.uniform(5.0, 100.0), 0.0, 0.0],
[0.0, np.random.uniform(5.0, 100.0), 0.0],
[0.0, 0.0, np.random.uniform(5.0, 100.0)]])
spinningBody2.setDCM_S0P([[0.0, -1.0, 0.0], [0.0, .0, -1.0], [1.0, 0.0, 0.0]])
spinningBody2.setR_ScS_S([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody2.setR_SP_P([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody2.setSHat_S([[0], [-1], [0]])
spinningBody2.setThetaInit(np.random.uniform(-10.0, 10.0) * macros.D2R)
spinningBody2.setThetaDotInit(np.random.uniform(-1.0, 1.0) * macros.D2R)
spinningBody2.setK(np.random.random())
spinningBodyEffector.addSpinningBody(spinningBody2)
spinningBody3 = spinningBodyNDOFStateEffector.SpinningBody()
spinningBody3.setMass(np.random.uniform(5.0, 50.0))
spinningBody3.setISPntSc_S([[np.random.uniform(5.0, 100.0), 0.0, 0.0],
[0.0, np.random.uniform(5.0, 100.0), 0.0],
[0.0, 0.0, np.random.uniform(5.0, 100.0)]])
spinningBody3.setDCM_S0P([[1.0, 0.0, 0.0], [0.0, -1.0, 0.0], [0.0, 0.0, -1.0]])
spinningBody3.setR_ScS_S([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody3.setR_SP_P([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody3.setSHat_S([[np.sqrt(1/2)], [np.sqrt(1/2)], [0]])
spinningBody3.setThetaInit(np.random.uniform(-10.0, 10.0) * macros.D2R)
spinningBody3.setThetaDotInit(np.random.uniform(-1.0, 1.0) * macros.D2R)
spinningBody3.setK(np.random.random())
spinningBodyEffector.addSpinningBody(spinningBody3)
spinningBody4 = spinningBodyNDOFStateEffector.SpinningBody()
spinningBody4.setMass(np.random.uniform(5.0, 50.0))
spinningBody4.setISPntSc_S([[np.random.uniform(5.0, 100.0), 0.0, 0.0],
[0.0, np.random.uniform(5.0, 100.0), 0.0],
[0.0, 0.0, np.random.uniform(5.0, 100.0)]])
spinningBody4.setDCM_S0P([[0.0, 1.0, 0.0], [0.0, .0, 1.0], [1.0, 0.0, 0.0]])
spinningBody4.setR_ScS_S([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody4.setR_SP_P([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody4.setSHat_S([[np.sqrt(1/2)], [-np.sqrt(1/2)], [0]])
spinningBody4.setThetaInit(np.random.uniform(-10.0, 10.0) * macros.D2R)
spinningBody4.setThetaDotInit(np.random.uniform(-1.0, 1.0) * macros.D2R)
spinningBody4.setK(np.random.random())
spinningBodyEffector.addSpinningBody(spinningBody4)
# Add spinning body to spacecraft
scObject.addStateEffector(spinningBodyEffector)
# Define mass properties of the rigid hub of the spacecraft
scObject.hub.mHub = 750.0
scObject.hub.r_BcB_B = [[0.0], [0.0], [1.0]]
scObject.hub.IHubPntBc_B = [[900.0, 0.0, 0.0], [0.0, 800.0, 0.0], [0.0, 0.0, 600.0]]
# Set the initial values for the states
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 = [[0.1], [-0.1], [0.1]]
# create lock message
lockArray = messaging.ArrayEffectorLockMsgPayload()
lockArray.effectorLockFlag = [1, 0, 0, 1]
lockMsg = messaging.ArrayEffectorLockMsg().write(lockArray)
spinningBodyEffector.motorLockInMsg.subscribeTo(lockMsg)
# Add test module to runtime call list
unitTestSim.AddModelToTask(unitTaskName, spinningBodyEffector)
unitTestSim.AddModelToTask(unitTaskName, scObject)
# Add Earth gravity to the simulation
earthGravBody = gravityEffector.GravBodyData()
earthGravBody.planetName = "earth_planet_data"
earthGravBody.mu = 0.3986004415E+15 # meters!
earthGravBody.isCentralBody = True
scObject.gravField.gravBodies = spacecraft.GravBodyVector([earthGravBody])
# Log the spacecraft state message
datLog = scObject.scStateOutMsg.recorder()
unitTestSim.AddModelToTask(unitTaskName, datLog)
# Add energy and momentum variables to log
scObjectLog = scObject.logger(["totRotEnergy", "totOrbEnergy", "totOrbAngMomPntN_N", "totRotAngMomPntC_N"])
unitTestSim.AddModelToTask(unitTaskName, scObjectLog)
# Add states to log
theta1Data = spinningBodyEffector.spinningBodyOutMsgs[0].recorder()
theta2Data = spinningBodyEffector.spinningBodyOutMsgs[1].recorder()
theta3Data = spinningBodyEffector.spinningBodyOutMsgs[2].recorder()
theta4Data = spinningBodyEffector.spinningBodyOutMsgs[3].recorder()
unitTestSim.AddModelToTask(unitTaskName, theta1Data)
unitTestSim.AddModelToTask(unitTaskName, theta2Data)
unitTestSim.AddModelToTask(unitTaskName, theta3Data)
unitTestSim.AddModelToTask(unitTaskName, theta4Data)
# Initialize the simulation
unitTestSim.InitializeSimulation()
# Setup and run the simulation
stopTime = 10000 * testProcessRate
unitTestSim.ConfigureStopTime(stopTime)
unitTestSim.ExecuteSimulation()
# Extract the logged variables
orbEnergy = scObjectLog.totOrbEnergy
orbAngMom_N = scObjectLog.totOrbAngMomPntN_N
rotAngMom_N = scObjectLog.totRotAngMomPntC_N
rotEnergy = scObjectLog.totRotEnergy
theta1 = theta1Data.theta
theta1Dot = theta1Data.thetaDot
theta2 = theta2Data.theta
theta2Dot = theta2Data.thetaDot
theta3 = theta3Data.theta
theta3Dot = theta3Data.thetaDot
theta4 = theta4Data.theta
theta4Dot = theta4Data.thetaDot
# Setup the conservation quantities
timeSec = scObjectLog.times() * 1e-9
initialOrbAngMom_N = [orbAngMom_N[0, 0], orbAngMom_N[0, 1], orbAngMom_N[0, 2]]
finalOrbAngMom = orbAngMom_N[-1]
initialRotAngMom_N = [rotAngMom_N[0, 0], rotAngMom_N[0, 1], rotAngMom_N[0, 2]]
finalRotAngMom = rotAngMom_N[-1]
initialOrbEnergy = orbEnergy[0]
finalOrbEnergy = orbEnergy[-1]
initialRotEnergy = rotEnergy[0]
finalRotEnergy = rotEnergy[-1]
# Plotting
plt.close("all")
plt.figure()
ax = plt.axes()
plt.plot(timeSec, (orbAngMom_N[:, 0] - initialOrbAngMom_N[0]) / initialOrbAngMom_N[0],
timeSec, (orbAngMom_N[:, 1] - initialOrbAngMom_N[1]) / initialOrbAngMom_N[1],
timeSec, (orbAngMom_N[:, 2] - initialOrbAngMom_N[2]) / initialOrbAngMom_N[2])
plt.xlabel('time (s)', fontsize='18')
plt.ylabel('Relative Difference', fontsize='18')
plt.title('Orbital Angular Momentum', fontsize='22')
plt.xticks(fontsize=14)
plt.yticks(fontsize=14)
ax.yaxis.offsetText.set_fontsize(14)
plt.figure()
ax = plt.axes()
plt.plot(timeSec, (orbEnergy - initialOrbEnergy) / initialOrbEnergy)
plt.xlabel('time (s)', fontsize='18')
plt.ylabel('Relative Difference', fontsize='18')
plt.title('Orbital Energy', fontsize='22')
plt.xticks(fontsize=14)
plt.yticks(fontsize=14)
ax.yaxis.offsetText.set_fontsize(14)
plt.figure()
ax = plt.axes()
plt.plot(timeSec, (rotAngMom_N[:, 0] - initialRotAngMom_N[0]) / initialRotAngMom_N[0],
timeSec, (rotAngMom_N[:, 1] - initialRotAngMom_N[1]) / initialRotAngMom_N[1],
timeSec, (rotAngMom_N[:, 2] - initialRotAngMom_N[2]) / initialRotAngMom_N[2])
plt.xlabel('time (s)', fontsize='18')
plt.ylabel('Relative Difference', fontsize='18')
plt.title('Rotational Angular Momentum', fontsize='22')
plt.xticks(fontsize=14)
plt.yticks(fontsize=14)
ax.yaxis.offsetText.set_fontsize(14)
plt.figure()
ax = plt.axes()
plt.plot(timeSec, (rotEnergy - initialRotEnergy) / initialRotEnergy)
plt.xlabel('time (s)', fontsize='18')
plt.ylabel('Relative Difference', fontsize='18')
plt.title('Rotational Energy', fontsize='22')
plt.xticks(fontsize=14)
plt.yticks(fontsize=14)
ax.yaxis.offsetText.set_fontsize(14)
plt.figure()
plt.clf()
plt.plot(timeSec, theta1, label=r'$\theta_1$')
plt.plot(timeSec, theta2, label=r'$\theta_2$')
plt.plot(timeSec, theta3, label=r'$\theta_3$')
plt.plot(timeSec, theta4, label=r'$\theta_4$')
plt.legend(loc='best')
plt.xlabel('time (s)')
plt.ylabel('Angle')
plt.figure()
plt.clf()
plt.plot(timeSec, theta1Dot, label=r'$\dot{\theta}_1$')
plt.plot(timeSec, theta2Dot, label=r'$\dot{\theta}_2$')
plt.plot(timeSec, theta3Dot, label=r'$\dot{\theta}_3$')
plt.plot(timeSec, theta4Dot, label=r'$\dot{\theta}_4$')
plt.legend(loc='best')
plt.xlabel('time (s)')
plt.ylabel('Angle Rate')
if show_plots:
plt.show()
plt.close("all")
# Testing setup
accuracy = 1e-12
np.testing.assert_allclose(finalOrbEnergy, initialOrbEnergy, rtol=accuracy)
np.testing.assert_allclose(finalRotEnergy, initialRotEnergy, rtol=accuracy)
for i in range(3):
np.testing.assert_allclose(finalOrbAngMom, initialOrbAngMom_N, rtol=accuracy)
np.testing.assert_allclose(finalRotAngMom, initialRotAngMom_N, rtol=accuracy)
def spinningBodyCommandedTorque(show_plots):
__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(0.0001) # update process rate update time
testProc = unitTestSim.CreateNewProcess(unitProcessName)
testProc.addTask(unitTestSim.CreateNewTask(unitTaskName, testProcessRate))
# Create two hinged rigid bodies
spinningBodyEffector = spinningBodyNDOFStateEffector.SpinningBodyNDOFStateEffector()
spinningBodyEffector.ModelTag = "spinningBodyEffector"
# Define properties of spinning bodies
spinningBody1 = spinningBodyNDOFStateEffector.SpinningBody()
spinningBody1.setMass(np.random.uniform(5.0, 50.0))
spinningBody1.setISPntSc_S([[np.random.uniform(5.0, 100.0), 0.0, 0.0],
[0.0, np.random.uniform(5.0, 100.0), 0.0],
[0.0, 0.0, np.random.uniform(5.0, 100.0)]])
spinningBody1.setDCM_S0P([[-1.0, 0.0, 0.0], [0.0, -1.0, 0.0], [0.0, 0.0, 1.0]])
spinningBody1.setR_ScS_S([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody1.setR_SP_P([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody1.setSHat_S([[0], [0], [1]])
spinningBody1.setThetaInit(np.random.uniform(-10.0, 10.0) * macros.D2R)
spinningBody1.setThetaDotInit(np.random.uniform(-1.0, 1.0) * macros.D2R)
spinningBody1.setK(np.random.random())
spinningBodyEffector.addSpinningBody(spinningBody1)
spinningBody2 = spinningBodyNDOFStateEffector.SpinningBody()
spinningBody2.setMass(np.random.uniform(5.0, 50.0))
spinningBody2.setISPntSc_S([[np.random.uniform(5.0, 100.0), 0.0, 0.0],
[0.0, np.random.uniform(5.0, 100.0), 0.0],
[0.0, 0.0, np.random.uniform(5.0, 100.0)]])
spinningBody2.setDCM_S0P([[0.0, -1.0, 0.0], [0.0, .0, -1.0], [1.0, 0.0, 0.0]])
spinningBody2.setR_ScS_S([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody2.setR_SP_P([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody2.setSHat_S([[0], [-1], [0]])
spinningBody2.setThetaInit(np.random.uniform(-10.0, 10.0) * macros.D2R)
spinningBody2.setThetaDotInit(np.random.uniform(-1.0, 1.0) * macros.D2R)
spinningBody2.setK(np.random.random())
spinningBodyEffector.addSpinningBody(spinningBody2)
spinningBody3 = spinningBodyNDOFStateEffector.SpinningBody()
spinningBody3.setMass(np.random.uniform(5.0, 50.0))
spinningBody3.setISPntSc_S([[np.random.uniform(5.0, 100.0), 0.0, 0.0],
[0.0, np.random.uniform(5.0, 100.0), 0.0],
[0.0, 0.0, np.random.uniform(5.0, 100.0)]])
spinningBody3.setDCM_S0P([[1.0, 0.0, 0.0], [0.0, -1.0, 0.0], [0.0, 0.0, -1.0]])
spinningBody3.setR_ScS_S([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody3.setR_SP_P([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody3.setSHat_S([[np.sqrt(1/2)], [np.sqrt(1/2)], [0]])
spinningBody3.setThetaInit(np.random.uniform(-10.0, 10.0) * macros.D2R)
spinningBody3.setThetaDotInit(np.random.uniform(-1.0, 1.0) * macros.D2R)
spinningBody3.setK(np.random.random())
spinningBodyEffector.addSpinningBody(spinningBody3)
spinningBody4 = spinningBodyNDOFStateEffector.SpinningBody()
spinningBody4.setMass(np.random.uniform(5.0, 50.0))
spinningBody4.setISPntSc_S([[np.random.uniform(5.0, 100.0), 0.0, 0.0],
[0.0, np.random.uniform(5.0, 100.0), 0.0],
[0.0, 0.0, np.random.uniform(5.0, 100.0)]])
spinningBody4.setDCM_S0P([[0.0, 1.0, 0.0], [0.0, .0, 1.0], [1.0, 0.0, 0.0]])
spinningBody4.setR_ScS_S([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody4.setR_SP_P([[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)],
[np.random.uniform(-1.0, 1.0)]])
spinningBody4.setSHat_S([[np.sqrt(1/2)], [-np.sqrt(1/2)], [0]])
spinningBody4.setThetaInit(np.random.uniform(-10.0, 10.0) * macros.D2R)
spinningBody4.setThetaDotInit(np.random.uniform(-1.0, 1.0) * macros.D2R)
spinningBody4.setK(np.random.random())
spinningBodyEffector.addSpinningBody(spinningBody4)
# Add spinning body to spacecraft
scObject.addStateEffector(spinningBodyEffector)
# Define mass properties of the rigid hub of the spacecraft
scObject.hub.mHub = 750.0
scObject.hub.r_BcB_B = [[0.0], [0.0], [1.0]]
scObject.hub.IHubPntBc_B = [[900.0, 0.0, 0.0], [0.0, 800.0, 0.0], [0.0, 0.0, 600.0]]
# Set the initial values for the states
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 = [[0.1], [-0.1], [0.1]]
# Create the torque message
cmdArray = messaging.ArrayMotorTorqueMsgPayload()
cmdArray.motorTorque = [0.1, -0.2, 0.3, -0.15] # [Nm]
cmdMsg = messaging.ArrayMotorTorqueMsg().write(cmdArray)
spinningBodyEffector.motorTorqueInMsg.subscribeTo(cmdMsg)
# Add test module to runtime call list
unitTestSim.AddModelToTask(unitTaskName, spinningBodyEffector)
unitTestSim.AddModelToTask(unitTaskName, scObject)
# Add Earth gravity to the simulation
earthGravBody = gravityEffector.GravBodyData()
earthGravBody.planetName = "earth_planet_data"
earthGravBody.mu = 0.3986004415E+15 # meters!
earthGravBody.isCentralBody = True
scObject.gravField.gravBodies = spacecraft.GravBodyVector([earthGravBody])
# Log the spacecraft state message
datLog = scObject.scStateOutMsg.recorder()
unitTestSim.AddModelToTask(unitTaskName, datLog)
# Add energy and momentum variables to log
scObjectLog = scObject.logger(["totRotEnergy", "totOrbEnergy", "totOrbAngMomPntN_N", "totRotAngMomPntC_N"])
unitTestSim.AddModelToTask(unitTaskName, scObjectLog)
# Add states to log
theta1Data = spinningBodyEffector.spinningBodyOutMsgs[0].recorder()
theta2Data = spinningBodyEffector.spinningBodyOutMsgs[1].recorder()
theta3Data = spinningBodyEffector.spinningBodyOutMsgs[2].recorder()
theta4Data = spinningBodyEffector.spinningBodyOutMsgs[3].recorder()
unitTestSim.AddModelToTask(unitTaskName, theta1Data)
unitTestSim.AddModelToTask(unitTaskName, theta2Data)
unitTestSim.AddModelToTask(unitTaskName, theta3Data)
unitTestSim.AddModelToTask(unitTaskName, theta4Data)
# Initialize the simulation
unitTestSim.InitializeSimulation()
# Setup and run the simulation
stopTime = 10000 * testProcessRate
unitTestSim.ConfigureStopTime(stopTime)
unitTestSim.ExecuteSimulation()
# Extract the logged variables
orbEnergy = scObjectLog.totOrbEnergy
orbAngMom_N = scObjectLog.totOrbAngMomPntN_N
rotAngMom_N = scObjectLog.totRotAngMomPntC_N
rotEnergy = scObjectLog.totRotEnergy
theta1 = theta1Data.theta
theta1Dot = theta1Data.thetaDot
theta2 = theta2Data.theta
theta2Dot = theta2Data.thetaDot
theta3 = theta3Data.theta
theta3Dot = theta3Data.thetaDot
theta4 = theta4Data.theta
theta4Dot = theta4Data.thetaDot
# Setup the conservation quantities
timeSec = scObjectLog.times() * 1e-9
initialOrbAngMom_N = [orbAngMom_N[0, 0], orbAngMom_N[0, 1], orbAngMom_N[0, 2]]
finalOrbAngMom = orbAngMom_N[-1]
initialRotAngMom_N = [rotAngMom_N[0, 0], rotAngMom_N[0, 1], rotAngMom_N[0, 2]]
finalRotAngMom = rotAngMom_N[-1]
initialOrbEnergy = orbEnergy[0]
finalOrbEnergy = orbEnergy[-1]
initialRotEnergy = rotEnergy[0]
# Plotting
plt.close("all")
plt.figure()
ax = plt.axes()
plt.plot(timeSec, (orbAngMom_N[:, 0] - initialOrbAngMom_N[0]) / initialOrbAngMom_N[0],
timeSec, (orbAngMom_N[:, 1] - initialOrbAngMom_N[1]) / initialOrbAngMom_N[1],
timeSec, (orbAngMom_N[:, 2] - initialOrbAngMom_N[2]) / initialOrbAngMom_N[2])
plt.xlabel('time (s)', fontsize='18')
plt.ylabel('Relative Difference', fontsize='18')
plt.title('Orbital Angular Momentum', fontsize='22')
plt.xticks(fontsize=14)
plt.yticks(fontsize=14)
ax.yaxis.offsetText.set_fontsize(14)
plt.figure()
ax = plt.axes()
plt.plot(timeSec, (orbEnergy - initialOrbEnergy) / initialOrbEnergy)
plt.xlabel('time (s)', fontsize='18')
plt.ylabel('Relative Difference', fontsize='18')
plt.title('Orbital Energy', fontsize='22')
plt.xticks(fontsize=14)
plt.yticks(fontsize=14)
ax.yaxis.offsetText.set_fontsize(14)
plt.figure()
ax = plt.axes()
plt.plot(timeSec, (rotAngMom_N[:, 0] - initialRotAngMom_N[0]) / initialRotAngMom_N[0],
timeSec, (rotAngMom_N[:, 1] - initialRotAngMom_N[1]) / initialRotAngMom_N[1],
timeSec, (rotAngMom_N[:, 2] - initialRotAngMom_N[2]) / initialRotAngMom_N[2])
plt.xlabel('time (s)', fontsize='18')
plt.ylabel('Relative Difference', fontsize='18')
plt.title('Rotational Angular Momentum', fontsize='22')
plt.xticks(fontsize=14)
plt.yticks(fontsize=14)
ax.yaxis.offsetText.set_fontsize(14)
plt.figure()
ax = plt.axes()
plt.plot(timeSec, (rotEnergy - initialRotEnergy) / initialRotEnergy)
plt.xlabel('time (s)', fontsize='18')
plt.ylabel('Relative Difference', fontsize='18')
plt.title('Rotational Energy', fontsize='22')
plt.xticks(fontsize=14)
plt.yticks(fontsize=14)
ax.yaxis.offsetText.set_fontsize(14)
plt.figure()
plt.clf()
plt.plot(timeSec, theta1, label=r'$\theta_1$')
plt.plot(timeSec, theta2, label=r'$\theta_2$')
plt.plot(timeSec, theta3, label=r'$\theta_3$')
plt.plot(timeSec, theta4, label=r'$\theta_4$')
plt.legend(loc='best')
plt.xlabel('time (s)')
plt.ylabel('Angle')
plt.figure()
plt.clf()
plt.plot(timeSec, theta1Dot, label=r'$\dot{\theta}_1$')
plt.plot(timeSec, theta2Dot, label=r'$\dot{\theta}_2$')
plt.plot(timeSec, theta3Dot, label=r'$\dot{\theta}_3$')
plt.plot(timeSec, theta4Dot, label=r'$\dot{\theta}_4$')
plt.legend(loc='best')
plt.xlabel('time (s)')
plt.ylabel('Angle Rate')
if show_plots:
plt.show()
plt.close("all")
# Testing setup
accuracy = 1e-12
np.testing.assert_allclose(finalOrbEnergy, initialOrbEnergy, rtol=accuracy)
for i in range(3):
np.testing.assert_allclose(finalOrbAngMom, initialOrbAngMom_N, rtol=accuracy)
np.testing.assert_allclose(finalRotAngMom, initialRotAngMom_N, rtol=accuracy)
if __name__ == "__main__":
# spinningBodyNoInput(True)
# spinningBodyLockAxis(True)
spinningBodyCommandedTorque(True)