Source code for scenarioAttitudeFeedback2T_stateEffTH

#
#  ISC License
#
#  Copyright (c) 2022, 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
--------

This scenario is an exact replica of :ref:`scenarioAttitudeFeedback2T_TH`. The only difference lies in the fact that
this scenario uses the :ref:`thrusterStateEffector` module instead of :ref:`thrusterDynamicEffector`. The performance
and results should be nearly identical to the original scenario, with the small difference that the thrusters do not
have an on-off behavior, but instead behave like a first-order filter. For more information on the scenario setup, see
:ref:`scenarioAttitudeFeedback2T_TH`.

To show that the :ref:`thrusterStateEffector` thruster module works with variable time step integrators, this scenario
uses an RKF78 integrator instead of the usual RK4.

Illustration of Simulation Results
----------------------------------

::

    show_plots = True, useDVThrusters = False

.. image:: /_images/Scenarios/scenarioAttitudeFeedback2T_stateEffTH10.svg
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.. image:: /_images/Scenarios/scenarioAttitudeFeedback2T_stateEffTH60.svg
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::

    show_plots = True, useDVThrusters = True

.. image:: /_images/Scenarios/scenarioAttitudeFeedback2T_stateEffTH11.svg
   :align: center

.. image:: /_images/Scenarios/scenarioAttitudeFeedback2T_stateEffTH21.svg
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.. image:: /_images/Scenarios/scenarioAttitudeFeedback2T_stateEffTH61.svg
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"""

#
# Basilisk Scenario Script and Integrated Test
#
# Purpose:  Integrated test of the spacecraft(), extForceTorque, simpleNav(), thrusterDynamicEffector() and
#           mrpFeedback() modules.  Illustrates a 6-DOV spacecraft detumbling in orbit, while using thrusters
#           to do the attitude control actuation.
# Author: João Vaz Carneiro
# Creation Date:  July 27, 2022
#

import os

import matplotlib.pyplot as plt
import numpy as np
# The path to the location of Basilisk
# Used to get the location of supporting data.
from Basilisk import __path__
# import message declarations
from Basilisk.architecture import messaging
from Basilisk.fswAlgorithms import attTrackingError
from Basilisk.fswAlgorithms import inertial3D
# import FSW Algorithm related support
from Basilisk.fswAlgorithms import mrpFeedback
from Basilisk.fswAlgorithms import thrFiringSchmitt
from Basilisk.fswAlgorithms import thrForceMapping
from Basilisk.simulation import extForceTorque
from Basilisk.simulation import simpleNav
# import simulation related support
from Basilisk.simulation import spacecraft
from Basilisk.simulation import svIntegrators
from Basilisk.simulation import thrusterStateEffector
# import general simulation support files
from Basilisk.utilities import SimulationBaseClass
from Basilisk.utilities import fswSetupThrusters
from Basilisk.utilities import macros
from Basilisk.utilities import orbitalMotion
from Basilisk.utilities import simIncludeGravBody
from Basilisk.utilities import simIncludeThruster
from Basilisk.utilities import unitTestSupport  # general support file with common unit test functions
# attempt to import vizard
from Basilisk.utilities import vizSupport

bskPath = __path__[0]
fileName = os.path.basename(os.path.splitext(__file__)[0])


# Plotting functions
[docs] def plot_attitude_error(timeDataFSW, dataSigmaBR): """Plot the attitude errors.""" plt.figure(1) for idx in range(3): plt.plot(timeDataFSW, dataSigmaBR[:, idx], color=unitTestSupport.getLineColor(idx, 3), label=r'$\sigma_' + str(idx) + r'$') plt.legend(loc='lower right') plt.xlabel('Time [min]') plt.ylabel(r'Attitude Error $\sigma_{B/R}$')
[docs] def plot_rate_error(timeDataFSW, dataOmegaBR): """Plot the body angular velocity tracking errors.""" plt.figure(2) for idx in range(3): plt.plot(timeDataFSW, dataOmegaBR[:, idx], color=unitTestSupport.getLineColor(idx, 3), label=r'$\omega_{BR,' + str(idx) + r'}$') plt.legend(loc='lower right') plt.xlabel('Time [min]') plt.ylabel('Rate Tracking Error [rad/s] ')
[docs] def plot_requested_torque(timeDataFSW, dataLr): """Plot the commanded attitude control torque.""" plt.figure(3) for idx in range(3): plt.plot(timeDataFSW, 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]')
[docs] def plot_thrForce(timeDataFSW, dataMap, numTh): """Plot the Thruster force values.""" plt.figure(4) for idx in range(numTh): plt.plot(timeDataFSW, dataMap[:, idx], color=unitTestSupport.getLineColor(idx, numTh), label=r'$thrForce_{' + str(idx) + r'}$') plt.legend(loc='lower right') plt.xlabel('Time [min]') plt.ylabel('Force requested [N]')
[docs] def plot_OnTimeRequest(timeDataFSW, dataSchm, numTh): """Plot the thruster on time requests.""" plt.figure(5) for idx in range(numTh): plt.plot(timeDataFSW, dataSchm[:, idx], color=unitTestSupport.getLineColor(idx, numTh), label=r'$OnTimeRequest_{' + str(idx) + r'}$') plt.legend(loc='lower right') plt.xlabel('Time [min]') plt.ylabel('OnTimeRequest [sec]')
[docs] def plot_trueThrForce(timeDataFSW, dataMap, numTh): """Plot the Thruster force values.""" plt.figure(6) for idx in range(numTh): plt.plot(timeDataFSW, dataMap[:, idx], color=unitTestSupport.getLineColor(idx, numTh), label=r'$thrForce_{' + str(idx) + r'}$') plt.legend(loc='lower right') plt.xlabel('Time [min]') plt.ylabel('Force implemented[N]')
[docs] def run(show_plots, useDVThrusters): """ The scenarios can be run with the followings setups parameters: Args: show_plots (bool): Determines if the script should display plots useDVThrusters (bool): Use 6 DV thrusters instead of the default 8 ACS thrusters. """ # Create simulation variable names dynTaskName = "dynTask" dynProcessName = "dynProcess" fswTaskName = "fswTask" fswProcessName = "fswProcess" # 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(dynProcessName) fswProcess = scSim.CreateNewProcess(fswProcessName) # create the dynamics task and specify the integration update time simTimeStep = macros.sec2nano(0.1) dynProcess.addTask(scSim.CreateNewTask(dynTaskName, simTimeStep)) fswTimeStep = macros.sec2nano(0.5) fswProcess.addTask(scSim.CreateNewTask(fswTaskName, fswTimeStep)) # # setup the simulation tasks/objects # # initialize spacecraft object and set properties scObject = spacecraft.Spacecraft() scObject.ModelTag = "bsk-Sat" # 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 spacecraft object to the simulation process scSim.AddModelToTask(dynTaskName, 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 spacecraft gravFactory.addBodiesTo(scObject) # setup extForceTorque module # the control torque is read in through the messaging system extFTObject = extForceTorque.ExtForceTorque() extFTObject.ModelTag = "externalDisturbance" extFTObject.extTorquePntB_B = [[0.25], [-0.25], [0.1]] scObject.addDynamicEffector(extFTObject) scSim.AddModelToTask(dynTaskName, extFTObject) # add the simple Navigation sensor module. This sets the SC attitude, rate, position # velocity navigation message sNavObject = simpleNav.SimpleNav() sNavObject.ModelTag = "SimpleNavigation" scSim.AddModelToTask(dynTaskName, sNavObject) # create arrays for thrusters' locations and directions if useDVThrusters: location = [ [ 0, 0.95, -1.1 ], [ 0.8227241335952166, 0.4750000000000003, -1.1 ], [ 0.8227241335952168, -0.47499999999999976, -1.1 ], [ 0, -0.95, -1.1 ], [ -0.8227241335952165, -0.4750000000000004, -1.1 ], [ -0.822724133595217, 0.4749999999999993, -1.1 ] ] direction = [[0.0, 0.0, 1.0], [0.0, 0.0, 1.0], [0.0, 0.0, 1.0], [0.0, 0.0, 1.0], [0.0, 0.0, 1.0], [0.0, 0.0, 1.0]] else: location = [ [ 3.874945160902288e-2, -1.206182747348013, 0.85245 ], [ 3.874945160902288e-2, -1.206182747348013, -0.85245 ], [ -3.8749451609022656e-2, -1.206182747348013, 0.85245 ], [ -3.8749451609022656e-2, -1.206182747348013, -0.85245 ], [ -3.874945160902288e-2, 1.206182747348013, 0.85245 ], [ -3.874945160902288e-2, 1.206182747348013, -0.85245 ], [ 3.8749451609022656e-2, 1.206182747348013, 0.85245 ], [ 3.8749451609022656e-2, 1.206182747348013, -0.85245 ] ] direction = [ [ -0.7071067811865476, 0.7071067811865475, 0.0 ], [ -0.7071067811865476, 0.7071067811865475, 0.0 ], [ 0.7071067811865475, 0.7071067811865476, 0.0 ], [ 0.7071067811865475, 0.7071067811865476, 0.0 ], [ 0.7071067811865476, -0.7071067811865475, 0.0 ], [ 0.7071067811865476, -0.7071067811865475, 0.0 ], [ -0.7071067811865475, -0.7071067811865476, 0.0 ], [ -0.7071067811865475, -0.7071067811865476, 0.0 ] ] # create the set of thruster in the dynamics task thrusterSet = thrusterStateEffector.ThrusterStateEffector() scSim.AddModelToTask(dynTaskName, thrusterSet) # set the integrator to a variable time step of 7th-8th order integratorObject = svIntegrators.svIntegratorRKF78(scObject) scObject.setIntegrator(integratorObject) # Make a fresh thruster factory instance, this is critical to run multiple times thFactory = simIncludeThruster.thrusterFactory() # create the thruster devices by specifying the thruster type and its location and direction for pos_B, dir_B in zip(location, direction): if useDVThrusters: thFactory.create('MOOG_Monarc_22_6', pos_B, dir_B, cutoffFrequency=1.) else: thFactory.create('MOOG_Monarc_1', pos_B, dir_B, cutoffFrequency=1.) # get number of thruster devices numTh = thFactory.getNumOfDevices() # create thruster object container and tie to spacecraft object thrModelTag = "ACSThrusterDynamics" thFactory.addToSpacecraft(thrModelTag, thrusterSet, scObject) # # setup the FSW algorithm tasks # # setup inertial3D guidance module inertial3DObj = inertial3D.inertial3D() inertial3DObj.ModelTag = "inertial3D" inertial3DObj.sigma_R0N = [0., 0., 0.] # set the desired inertial orientation scSim.AddModelToTask(fswTaskName, inertial3DObj) # setup the attitude tracking error evaluation module attError = attTrackingError.attTrackingError() attError.ModelTag = "attErrorInertial3D" scSim.AddModelToTask(fswTaskName, attError) # setup the MRP Feedback control module mrpControl = mrpFeedback.mrpFeedback() mrpControl.ModelTag = "mrpFeedback" scSim.AddModelToTask(fswTaskName, mrpControl) mrpControl.K = 3.5 * 10.0 mrpControl.Ki = 0.0002 # make value negative to turn off integral feedback mrpControl.P = 30.0 * 10.0 mrpControl.integralLimit = 2. / mrpControl.Ki * 0.1 # setup the thruster force mapping module thrForceMappingObj = thrForceMapping.thrForceMapping() thrForceMappingObj.ModelTag = "thrForceMapping" scSim.AddModelToTask(fswTaskName, thrForceMappingObj) if useDVThrusters: controlAxes_B = [1, 0, 0, 0, 1, 0] thrForceMappingObj.thrForceSign = -1 else: controlAxes_B = [1, 0, 0, 0, 1, 0, 0, 0, 1] thrForceMappingObj.thrForceSign = +1 thrForceMappingObj.controlAxes_B = controlAxes_B # setup the Schmitt trigger thruster firing logic module thrFiringSchmittObj = thrFiringSchmitt.thrFiringSchmitt() thrFiringSchmittObj.ModelTag = "thrFiringSchmitt" scSim.AddModelToTask(fswTaskName, thrFiringSchmittObj) thrFiringSchmittObj.thrMinFireTime = 0.002 thrFiringSchmittObj.level_on = .75 thrFiringSchmittObj.level_off = .25 if useDVThrusters: thrFiringSchmittObj.baseThrustState = 1 # # Setup data logging before the simulation is initialized # numDataPoints = 100 samplingTime = unitTestSupport.samplingTime(simulationTime, fswTimeStep, numDataPoints) mrpTorqueLog = mrpControl.cmdTorqueOutMsg.recorder(samplingTime) attErrorLog = attError.attGuidOutMsg.recorder(samplingTime) snTransLog = sNavObject.transOutMsg.recorder(samplingTime) snAttLog = sNavObject.attOutMsg.recorder(samplingTime) thrMapLog = thrForceMappingObj.thrForceCmdOutMsg.recorder(samplingTime) thrTrigLog = thrFiringSchmittObj.onTimeOutMsg.recorder(samplingTime) scSim.AddModelToTask(fswTaskName, mrpTorqueLog) scSim.AddModelToTask(fswTaskName, attErrorLog) scSim.AddModelToTask(fswTaskName, snTransLog) scSim.AddModelToTask(fswTaskName, snAttLog) scSim.AddModelToTask(fswTaskName, thrMapLog) scSim.AddModelToTask(fswTaskName, thrTrigLog) thrForceLog = [] for i in range(numTh): thrForceLog.append(thrusterSet.thrusterOutMsgs[i].recorder(samplingTime)) scSim.AddModelToTask(fswTaskName, thrForceLog[i]) # # create FSW simulation messages # # create the FSW vehicle configuration message vehicleConfigOut = messaging.VehicleConfigMsgPayload() vehicleConfigOut.ISCPntB_B = I # use the same inertia in the FSW algorithm as in the simulation vcMsg = messaging.VehicleConfigMsg().write(vehicleConfigOut) # create the FSW Thruster configuration message if useDVThrusters: maxThrust = 22 else: maxThrust = 1 # A `clearSetup()` should be called first to clear out any pre-existing devices from an # earlier simulation run. Next, the `maxThrust` value should be specified and used in the macro `create()`, # together with the locations and directions, and looped through a for cycle to consider all the thrusters. # The support macro `writeConfigMessage()` creates the required thrusters flight configuration message. fswSetupThrusters.clearSetup() for pos_B, dir_B in zip(location, direction): fswSetupThrusters.create(pos_B, dir_B, maxThrust) fswThrConfigMsg = fswSetupThrusters.writeConfigMessage() # an alternate method to pull un-modifed SIM Thruster configuration and create the corresponding FSW # configuration message is: fswThrConfigMsg = thFactory.getConfigMessage() # 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 = rN # m - r_CN_N scObject.hub.v_CN_NInit = 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 # connect messages sNavObject.scStateInMsg.subscribeTo(scObject.scStateOutMsg) attError.attNavInMsg.subscribeTo(sNavObject.attOutMsg) attError.attRefInMsg.subscribeTo(inertial3DObj.attRefOutMsg) mrpControl.guidInMsg.subscribeTo(attError.attGuidOutMsg) mrpControl.vehConfigInMsg.subscribeTo(vcMsg) thrForceMappingObj.cmdTorqueInMsg.subscribeTo(mrpControl.cmdTorqueOutMsg) thrForceMappingObj.thrConfigInMsg.subscribeTo(fswThrConfigMsg) thrForceMappingObj.vehConfigInMsg.subscribeTo(vcMsg) thrFiringSchmittObj.thrConfInMsg.subscribeTo(fswThrConfigMsg) thrFiringSchmittObj.thrForceInMsg.subscribeTo(thrForceMappingObj.thrForceCmdOutMsg) thrusterSet.cmdsInMsg.subscribeTo(thrFiringSchmittObj.onTimeOutMsg) # if this scenario is to interface with the BSK Viz, uncomment the following lines viz = vizSupport.enableUnityVisualization(scSim, dynTaskName, scObject # , saveFile=fileName , thrEffectorList=thrusterSet , thrColors=vizSupport.toRGBA255("red") ) vizSupport.setActuatorGuiSetting(viz, showThrusterLabels=True) # # initialize Simulation # scSim.InitializeSimulation() # # configure a simulation stop time and execute the simulation run # scSim.ConfigureStopTime(simulationTime) scSim.ExecuteSimulation() # # retrieve the logged data # dataLr = mrpTorqueLog.torqueRequestBody dataSigmaBR = attErrorLog.sigma_BR dataOmegaBR = attErrorLog.omega_BR_B dataMap = thrMapLog.thrForce dataSchm = thrTrigLog.OnTimeRequest dataThrust = [] for i in range(numTh): dataThrust.append(np.array(thrForceLog[i].thrustForce)) dataThrust = np.stack(np.transpose(dataThrust)) np.set_printoptions(precision=16) # # plot the results # timeDataFSW = attErrorLog.times() * macros.NANO2MIN plt.close("all") # clears out plots from earlier test runs plot_requested_torque(timeDataFSW, dataLr) figureList = {} pltName = fileName + "1" + str(int(useDVThrusters)) figureList[pltName] = plt.figure(1) plot_rate_error(timeDataFSW, dataOmegaBR) pltName = fileName + "2" + str(int(useDVThrusters)) figureList[pltName] = plt.figure(2) plot_attitude_error(timeDataFSW, dataSigmaBR) pltName = fileName + "3" + str(int(useDVThrusters)) figureList[pltName] = plt.figure(3) plot_thrForce(timeDataFSW, dataMap, numTh) pltName = fileName + "4" + str(int(useDVThrusters)) figureList[pltName] = plt.figure(4) plot_OnTimeRequest(timeDataFSW, dataSchm, numTh) pltName = fileName + "5" + str(int(useDVThrusters)) figureList[pltName] = plt.figure(5) plot_trueThrForce(timeDataFSW, dataThrust, numTh) pltName = fileName + "6" + str(int(useDVThrusters)) figureList[pltName] = plt.figure(6) if show_plots: plt.show() # close the plots being saved off to avoid over-writing old and new figures plt.close("all") return 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, # useDVThrusters )