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test_disturbance_1U.py
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test_disturbance_1U.py
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import numpy as np
import Disturbance_1U_02 as dist
import unittest
from satellite import Satellite
from constants_1U import m_INERTIA
from ddt import data, ddt , unpack
@ddt
class TestGravityGradient(unittest.TestCase):
#Test the data type of output
def test_gg_data_type(self):
sat = Satellite(np.array([1.,0.,0.,0.,0.,0.,0.]),13.)
sat.setPos(np.array([7070e3,0.,0.]))
result = dist.vTGgB(sat)
self.assertEqual(type(result),np.ndarray)
#Take position vector to be eigen vector of m_INERTIA along with q =[1,0,0,0] thus torque will be zero
l, w = np.linalg.eig(m_INERTIA)
@data(7070e3*w[:,0],7070e3*w[:,1],7070e3*w[:,2])
def test_inertia_eigenvec(self,value):
state = np.array([1.,0.,0.,0.,0.1,-0.02,-0.2])
mySat = Satellite(state,128.05)
mySat.setPos(value)
mySat.setVel(np.array([5.60,-5.0,0.0]))
result = dist.vTGgB(mySat)
print result
self.assertTrue(np.allclose(result,[0.,0.,0.]))
class TestAeroDrag(unittest.TestCase):
#test the data type of the output
def test_aero_type(self):
sat = Satellite(np.array([np.sqrt(0.5),-np.sqrt(0.5),0.,0.,0.1,0.23,0.]),13.)
sat.setPos(np.array([0.,0.,7e6]))
sat.setVel(np.array([0,2e3,6e3]))
result = dist.vTAdB(sat)
self.assertEqual(type(result),np.ndarray)
def test_aero_value(self):
sat = Satellite(np.array([np.sqrt(0.5),-np.sqrt(0.5),0.,0.,0.1,0.23,0.]),13.)
sat.setPos(np.array([0.,0.,7e6]))
sat.setVel(np.array([0,2e3,6e3]))
result = dist.vTAdB(sat)
print result
self.assertTrue(np.allclose(result, [2.99654080e-10,-2.57065600e-11,-7.71196800e-11]))
class TestSolarTorque(unittest.TestCase):
#test the data type of the output
def test_solar_torque_type(self):
sat = Satellite(np.array([1.,0.,0.,0.,0.,0.,0.]),13.)
sat.setPos(np.array([7070e3,0.,0.]))
v_sv_i=np.array([1.0,0.0,0.0])
sat.setSun_i(v_sv_i)
sat.setLight(0)
result = dist.vTSdB(sat)
self.assertEqual(type(result),np.ndarray)
def test_solar_torque_value(self):
state = np.array([1.,0.,0.,0.,0.1,-0.02,-0.2])
mySat = Satellite(state,128.05)
v_sv_i=np.array([1.0,0.0,0.0]) #sun vector in eci frame
mySat.setSun_i(v_sv_i)
mySat.setLight(0)
result = dist.vTSdB(mySat)
print result
self.assertTrue(np.allclose(result,[ 0.00000000e+00,-3.66624000e-11,3.17376000e-10]))
if __name__=="__main__":
unittest.main(verbosity=2)