#
# 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.
#
r"""
Overview
--------
Demonstrates how to stabilize the tumble of a spacecraft orbiting the
Earth that is initially tumbling.
This script sets up a 6-DOF spacecraft which is orbiting the Earth.
The script is found in the folder ``src/examples`` and executed by using::
python3 scenarioAttitudeFeedback.py
The simulation layout is
shown in the following illustration. A single simulation process is created
which contains both the spacecraft simulation modules, as well as the Flight Software (FSW) algorithm
modules.
.. image:: /_images/static/test_scenarioAttitudeFeedback.svg
:align: center
The dynamics simulation is setup using a :ref:`SpacecraftPlus` module to which a gravity
effector is attached. Note that both the rotational and translational degrees of
freedom of the spacecraft hub are turned on here to get a 6-DOF simulation. For more
information on how to setup orbit, see :ref:`scenarioBasicOrbit`.
The control torque is simulated using the :ref:`extForceTorque` module. This module can
accept a torque in body frame components either through an input message, or through
a module internal torque vector which can be set in python. In this simulation, the
flight software is providing the attitude control torque message which is connected to
the torque input message of this module. If an external torque is being simulated,
then the module internal torque vector is set to a constant value.
The flight software algorithm module require a navigation message with the
spacecraft orientation and attitude rates. This is setup using the :ref:`simple_nav`
module. By just invoking a sensor module it is setup to run without any simulated
corruptions. Thus in this simulation it will return truth measurements.
Next the flight software algorithms need to be setup. The inertial pointing reference
frame definition is provided through the simple :ref:`inertial3D` module. The only input
it requires is the desired inertial heading.
The reference frame states and the navigation message (output of :ref:`simple_nav` are fed
into the :ref:`attTrackingError` module. It is setup to compute the attitude tracking error
between the body frame :math:`\cal B` and the reference frame :math:`\cal R`.
If a body fixed frame other than :math:`\cal B`
needs to be driven towards *R*, this could be configured as well in this module.
Finally the tracking errors are fed to the classic MRP feedback control module. The
algorithm of this is discussed in the text book
`Analytical Mechanics of Space Systems <http://dx.doi.org/10.2514/4.105210>`__.
The control torque output vector message of this
module is connected back to the input message of the :ref:`extForceTorque` module to close
the control loop.
When the simulation completes 3 plots are shown for the MRP attitude history, the rate
tracking errors, as well as the control torque vector.
Illustration of Simulation Results
----------------------------------
::
show_plots = True, useUnmodeledTorque = False, useIntGain = False, useKnownTorque = False
.. image:: /_images/Scenarios/scenarioAttitudeFeedback1000.svg
:align: center
.. image:: /_images/Scenarios/scenarioAttitudeFeedback2000.svg
:align: center
::
show_plots = True, useUnmodeledTorque = True, useIntGain = False, useKnownTorque = False
Note that, as expected,
the orientation error doesn't settle to zero, but rather converges to a non-zero offset
proportional to the un-modeled torque being simulated. Also, the control torques settle on
non-zero steady-state values.
.. image:: /_images/Scenarios/scenarioAttitudeFeedback1100.svg
:align: center
.. image:: /_images/Scenarios/scenarioAttitudeFeedback2100.svg
:align: center
::
show_plots = True, useUnmodeledTorque = True, useIntGain = True, useKnownTorque = False
In this case the orientation error does settle to zero. The integral term changes the control torque
to settle on a value that matches the un-modeled external torque.
.. image:: /_images/Scenarios/scenarioAttitudeFeedback1110.svg
:align: center
.. image:: /_images/Scenarios/scenarioAttitudeFeedback2110.svg
:align: center
::
show_plots = True, useUnmodeledTorque = True, useIntGain = False, useKnownTorque = True
In this case the orientation error does settle to zero as the feed-forward term compensates for
the external torque. The control torque is now caused
to settle on a value that matches the un-modeled external torque.
.. image:: /_images/Scenarios/scenarioAttitudeFeedback1101.svg
:align: center
.. image:: /_images/Scenarios/scenarioAttitudeFeedback2101.svg
:align: center
"""
#
# Basilisk Scenario Script and Integrated Test
#
# Purpose: Integrated test of the spacecraftPlus(), extForceTorque, simpleNav() and
# MRP_Feedback() modules. Illustrates a 6-DOV spacecraft detumbling in orbit
# Author: Hanspeter Schaub
# Creation Date: Nov. 19, 2016
#
import sys
import os
import numpy as np
# import general simulation support files
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.utilities import macros
from Basilisk.utilities import orbitalMotion
# import simulation related support
from Basilisk.simulation import spacecraftPlus
from Basilisk.simulation import extForceTorque
from Basilisk.utilities import simIncludeGravBody
from Basilisk.simulation import simple_nav
# import FSW Algorithm related support
from Basilisk.fswAlgorithms import MRP_Feedback
from Basilisk.fswAlgorithms import inertial3D
from Basilisk.fswAlgorithms import attTrackingError
# import message declarations
from Basilisk.fswAlgorithms import fswMessages
# attempt to import vizard
from Basilisk.utilities import vizSupport
# The path to the location of Basilisk
# Used to get the location of supporting data.
from Basilisk import __path__
bskPath = __path__[0]
fileName = os.path.basename(os.path.splitext(__file__)[0])
[docs]def run(show_plots, useUnmodeledTorque, useIntGain, useKnownTorque):
"""
The scenarios can be run with the followings setups parameters:
Args:
show_plots (bool): Determines if the script should display plots
useUnmodeledTorque (bool): Specify if an external torque should be included
useIntGain (bool): Specify if the feedback control uses an integral feedback term
useKnownTorque (bool): Specify if the external torque is feed forward in the control
"""
# Create simulation variable names
simTaskName = "simTask"
simProcessName = "simProcess"
# Create a sim module as an empty container
scSim = SimulationBaseClass.SimBaseClass()
# set the simulation time variable used later on
simulationTime = macros.min2nano(10.)
#
# create the simulation process
#
dynProcess = scSim.CreateNewProcess(simProcessName)
# create the dynamics task and specify the integration update time
simulationTimeStep = macros.sec2nano(.1)
dynProcess.addTask(scSim.CreateNewTask(simTaskName, simulationTimeStep))
#
# setup the simulation tasks/objects
#
# initialize spacecraftPlus object and set properties
scObject = spacecraftPlus.SpacecraftPlus()
scObject.ModelTag = "spacecraftBody"
# define the simulation inertia
I = [900., 0., 0.,
0., 800., 0.,
0., 0., 600.]
scObject.hub.mHub = 750.0 # kg - spacecraft mass
scObject.hub.r_BcB_B = [[0.0], [0.0], [0.0]] # m - position vector of body-fixed point B relative to CM
scObject.hub.IHubPntBc_B = unitTestSupport.np2EigenMatrix3d(I)
# add spacecraftPlus object to the simulation process
scSim.AddModelToTask(simTaskName, scObject)
# clear prior gravitational body and SPICE setup definitions
gravFactory = simIncludeGravBody.gravBodyFactory()
# setup Earth Gravity Body
earth = gravFactory.createEarth()
earth.isCentralBody = True # ensure this is the central gravitational body
mu = earth.mu
# attach gravity model to spaceCraftPlus
scObject.gravField.gravBodies = spacecraftPlus.GravBodyVector(list(gravFactory.gravBodies.values()))
# setup extForceTorque module
# the control torque is read in through the messaging system
extFTObject = extForceTorque.ExtForceTorque()
extFTObject.ModelTag = "externalDisturbance"
# use the input flag to determine which external torque should be applied
# Note that all variables are initialized to zero. Thus, not setting this
# vector would leave it's components all zero for the simulation.
if useUnmodeledTorque:
extFTObject.extTorquePntB_B = [[0.25], [-0.25], [0.1]]
scObject.addDynamicEffector(extFTObject)
scSim.AddModelToTask(simTaskName, extFTObject)
# add the simple Navigation sensor module. This sets the SC attitude, rate, position
# velocity navigation message
sNavObject = simple_nav.SimpleNav()
sNavObject.ModelTag = "SimpleNavigation"
scSim.AddModelToTask(simTaskName, sNavObject)
#
# setup the FSW algorithm tasks
#
# setup inertial3D guidance module
inertial3DConfig = inertial3D.inertial3DConfig()
inertial3DWrap = scSim.setModelDataWrap(inertial3DConfig)
inertial3DWrap.ModelTag = "inertial3D"
scSim.AddModelToTask(simTaskName, inertial3DWrap, inertial3DConfig)
inertial3DConfig.sigma_R0N = [0., 0., 0.] # set the desired inertial orientation
inertial3DConfig.outputDataName = "guidanceInertial3D"
# setup the attitude tracking error evaluation module
attErrorConfig = attTrackingError.attTrackingErrorConfig()
attErrorWrap = scSim.setModelDataWrap(attErrorConfig)
attErrorWrap.ModelTag = "attErrorInertial3D"
scSim.AddModelToTask(simTaskName, attErrorWrap, attErrorConfig)
attErrorConfig.outputDataName = "attErrorInertial3DMsg"
attErrorConfig.inputRefName = inertial3DConfig.outputDataName
attErrorConfig.inputNavName = sNavObject.outputAttName
# setup the MRP Feedback control module
mrpControlConfig = MRP_Feedback.MRP_FeedbackConfig()
mrpControlWrap = scSim.setModelDataWrap(mrpControlConfig)
mrpControlWrap.ModelTag = "MRP_Feedback"
scSim.AddModelToTask(simTaskName, mrpControlWrap, mrpControlConfig)
mrpControlConfig.inputGuidName = attErrorConfig.outputDataName
mrpControlConfig.vehConfigInMsgName = "vehicleConfigName"
mrpControlConfig.outputDataName = extFTObject.cmdTorqueInMsgName
mrpControlConfig.K = 3.5
if useIntGain:
mrpControlConfig.Ki = 0.0002 # make value negative to turn off integral feedback
else:
mrpControlConfig.Ki = -1 # make value negative to turn off integral feedback
mrpControlConfig.P = 30.0
mrpControlConfig.integralLimit = 2. / mrpControlConfig.Ki * 0.1
if useKnownTorque:
mrpControlConfig.knownTorquePntB_B = [0.25, -0.25, 0.1]
#
# Setup data logging before the simulation is initialized
#
numDataPoints = 50
samplingTime = simulationTime // (numDataPoints - 1)
scSim.TotalSim.logThisMessage(mrpControlConfig.outputDataName, samplingTime)
scSim.TotalSim.logThisMessage(attErrorConfig.outputDataName, samplingTime)
scSim.TotalSim.logThisMessage(sNavObject.outputTransName, samplingTime)
#
# create simulation messages
#
# The MRP Feedback algorithm requires the vehicle configuration structure. This defines various spacecraft
# related states such as the inertia tensor and the position vector between the primary Body-fixed frame
# B origin and the center of mass (defaulted to zero). This message is set through
vehicleConfigOut = fswMessages.VehicleConfigFswMsg()
vehicleConfigOut.ISCPntB_B = I # use the same inertia in the FSW algorithm as in the simulation
unitTestSupport.setMessage(scSim.TotalSim,
simProcessName,
mrpControlConfig.vehConfigInMsgName,
vehicleConfigOut)
# Here the container object is first created, then the inertia tensor is set. Finally the macro
# setMessage() can be used to conveniently create, size and write this message to a process.
#
# set initial Spacecraft States
#
# setup the orbit using classical orbit elements
oe = orbitalMotion.ClassicElements()
oe.a = 10000000.0 # meters
oe.e = 0.01
oe.i = 33.3 * macros.D2R
oe.Omega = 48.2 * macros.D2R
oe.omega = 347.8 * macros.D2R
oe.f = 85.3 * macros.D2R
rN, vN = orbitalMotion.elem2rv(mu, oe)
scObject.hub.r_CN_NInit = unitTestSupport.np2EigenVectorXd(rN) # m - r_CN_N
scObject.hub.v_CN_NInit = unitTestSupport.np2EigenVectorXd(vN) # m/s - v_CN_N
scObject.hub.sigma_BNInit = [[0.1], [0.2], [-0.3]] # sigma_BN_B
scObject.hub.omega_BN_BInit = [[0.001], [-0.01], [0.03]] # rad/s - omega_BN_B
# if this scenario is to interface with the BSK Viz, uncomment the following line
# vizSupport.enableUnityVisualization(scSim, simTaskName, simProcessName, gravBodies=gravFactory, saveFile=fileName)
#
# initialize Simulation
#
scSim.InitializeSimulationAndDiscover()
#
# configure a simulation stop time time and execute the simulation run
#
scSim.ConfigureStopTime(simulationTime)
scSim.ExecuteSimulation()
#
# retrieve the logged data
#
dataLr = scSim.pullMessageLogData(mrpControlConfig.outputDataName + ".torqueRequestBody", list(range(3)))
dataSigmaBR = scSim.pullMessageLogData(attErrorConfig.outputDataName + ".sigma_BR", list(range(3)))
dataOmegaBR = scSim.pullMessageLogData(attErrorConfig.outputDataName + ".omega_BR_B", list(range(3)))
dataPos = scSim.pullMessageLogData(sNavObject.outputTransName + ".r_BN_N", list(range(3)))
np.set_printoptions(precision=16)
#
# plot the results
#
plt.close("all") # clears out plots from earlier test runs
plt.figure(1)
for idx in range(1, 4):
plt.plot(dataSigmaBR[:, 0] * macros.NANO2MIN, dataSigmaBR[:, idx],
color=unitTestSupport.getLineColor(idx, 3),
label=r'$\sigma_' + str(idx) + '$')
plt.legend(loc='lower right')
plt.xlabel('Time [min]')
plt.ylabel(r'Attitude Error $\sigma_{B/R}$')
figureList = {}
pltName = fileName + "1" + str(int(useUnmodeledTorque)) + str(int(useIntGain))+ str(int(useKnownTorque))
figureList[pltName] = plt.figure(1)
plt.figure(2)
for idx in range(1, 4):
plt.plot(dataLr[:, 0] * macros.NANO2MIN, dataLr[:, idx],
color=unitTestSupport.getLineColor(idx, 3),
label='$L_{r,' + str(idx) + '}$')
plt.legend(loc='lower right')
plt.xlabel('Time [min]')
plt.ylabel(r'Control Torque $L_r$ [Nm]')
pltName = fileName + "2" + str(int(useUnmodeledTorque)) + str(int(useIntGain)) + str(int(useKnownTorque))
figureList[pltName] = plt.figure(2)
plt.figure(3)
for idx in range(1, 4):
plt.plot(dataOmegaBR[:, 0] * macros.NANO2MIN, dataOmegaBR[:, idx],
color=unitTestSupport.getLineColor(idx, 3),
label=r'$\omega_{BR,' + str(idx) + '}$')
plt.legend(loc='lower right')
plt.xlabel('Time [min]')
plt.ylabel('Rate Tracking Error [rad/s] ')
if show_plots:
plt.show()
# close the plots being saved off to avoid over-writing old and new figures
plt.close("all")
return dataPos, dataSigmaBR, dataLr, numDataPoints, figureList
#
# This statement below ensures that the unit test scrip can be run as a
# stand-along python script
#
if __name__ == "__main__":
run(
True, # show_plots
False, # useUnmodeledTorque
False, # useIntGain
False # useKnownTorque
)