''' '''
'''
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
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'''
#
# Keplerian OrbitUnit Test
#
# Purpose: Tests an object-oriented Keplerian Orbit Object
# Author: Scott Carnahan
# Creation Date: Sept 10 2019
#
import pytest
import os, inspect
from Basilisk.simulation import gravityEffector
from Basilisk.utilities import orbitalMotion, unitTestSupport
from Basilisk.simulation import keplerianOrbit
from copy import copy
import numpy as np
filename = inspect.getframeinfo(inspect.currentframe()).filename
path = os.path.dirname(os.path.abspath(filename))
[docs]def test_unitKeplerianOrbit(show_plots=False):
"""
Unit Test Keplerian Orbit object
This test covers:
1) elem to rv conversion
2) orbit energy calculation
3) orbital period calculation
4) mean motion calculation
5) changing individual orbital elements
6) copy constructor
7) constructor with arguments
8) constructor without arguments
Parameters
----------
show_plots : bool
unused. required for Basilisk test suite
Returns
-------
testFailCount : int
number of tests that failed
testMessages : str
a string of all of the failure messages
"""
testFailCount = 0
testMessages = []
# constructor without arguments
orb = keplerianOrbit.KeplerianOrbit()
assert orb.a() == 100000.
if not orb.a() == 100000.:
testFailCount += 1
testMessages.append('default constructor failure')
# constructor with arguments
oe = orb.oe()
earth = gravityEffector.GravBodyData()
earth.mu = orbitalMotion.MU_EARTH
orb2 = keplerianOrbit.KeplerianOrbit(oe, earth)
assert orb2.r_BP_P() == orb.r_BP_P()
if not orb2.r_BP_P() == orb.r_BP_P():
testFailCount += 1
testMessages.append('Argumented constructor failure')
# copy constructor
orb3 = keplerianOrbit.KeplerianOrbit(orb2)
assert orb2.v_BP_P() == orb3.v_BP_P()
if not orb2.v_BP_P() == orb3.v_BP_P():
testFailCount += 1
testMessages.append('Copy Constructor Failure')
try:
orb4 = copy(orb3)
except:
assert False
testFailCount += 1
testMessages.append('python copy not working')
# changing orbital elements
orb3.set_f(0.0)
init_r = orb3.r()
orb3.set_f(1.)
assert init_r != orb3.r()
if init_r == orb3.r():
testFailCount += 1
testMessages.append('Failure to change element')
orb3.set_f(0.0)
assert init_r == orb3.r()
if init_r != orb3.r():
testFailCount += 1
testMessages.append('Failure to change element')
# mean motion calc
expected_n = np.sqrt(orbitalMotion.MU_EARTH / orb3.a()**3)
assert orb3.n() == expected_n
if not orb3.n() == expected_n:
testFailCount += 1
testMessages.append('Bad mean motion calc')
# orbital period calc
assert orb3.P() == 2 * np.pi / expected_n
if not orb3.P() == 2 * np.pi / expected_n:
testFailCount += 1
testMessages.append('Bad period calc')
# orbital energy calc
expected_E = -orbitalMotion.MU_EARTH / 2.0 / orb3.a()
assert orb3.Energy() == expected_E
if not orb3.Energy() == expected_E:
testFailCount += 1
testMessages.append('Bad energy calc')
# rv calc
expected_r, expected_v = orbitalMotion.elem2rv(orbitalMotion.MU_EARTH, orb3.oe())
dist = np.linalg.norm(np.array(orb3.r_BP_P()).flatten() - expected_r)
assert dist == 0.0
if not dist == 0.0:
testFailCount += 1
testMessages.append('RV conversion failure')
return [testFailCount, ''.join(testMessages)]
if __name__ == "__main__":
test_unitKeplerianOrbit()